Atlas of Stre~~-~train Curves Second Edition
The Materials
Information Society
Materials Park, OH 44073-0002 www.asminternational.org
íA L-r60 . A~~
't-oCL
Copyright © 2002 by ASM Intemational® AH rights reserved
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Prepared under (he direction of the ASM International Technical Book Committee (2001-2002), Charles A. Parker, Chair. Prepared with assistancefrom the ASM Internationai Materiais Properties Database Committee, PI Sikorsky, Chair. ASM Internationai staff who worked on this project included Charles Moosbrugger, Technical Editor; Veronica Flint, Acquisitions Editor; Bonnie Sanders, Manager of Production; Carol Terman, Production Project Manager; and Scott Henry, Assistant Director of Reference Publications. '
Library of Coogress Cataloging-in-Publication Data
Atlas of stress-strain curves.-2nd ed. p.cm. SAN: 204-586---T.p. verso. ISBN: 0-87170-739-X 1. Stress-strain curves-Atlases. 2. Metals-Testing. 1. ASM Intemational.
TA460 .A86 2002 620,I'63-dc 21 2002027674
ASM Intemational® Materials Park, OH 44073-0002 www.asminternational.org
Printed in the Uoited States of America
Contents Preface ....................................................... iv Representation of Stress-Strain Behavior .............................. 1 Ferrous Metals ................................................ 21 Cast lron (CI) ................................................. 23 Carbon Steel (CS) .............................................. 67 Alloy Steel (AS) ............................................... 93 High-Strength Steel (HS) ........................................ 129 Stainless Steel (SS) ............................................ 161 Tool Steel (TS) ............................................... 269 Nonferrous Metals ............................................ 277 Cast Aluminum (CA) .......................................... 279 Wrought Aluminum (WA) ...................................... 299 Aluminum Laminates (LA) ...................................... 503 Copper (Cu) ................................................. 515 Magnesium (Mg) ............................................. 555 Nickel (Ni) .................................................. 631 Reactive and Refractory Metals (RM) .............................. 705 Titanium (Ti) ................................................ 729 Pure Metals and Miscell
¡¡¡
Preface In this information age, mechanical property data are plentiful. However, locating needed information quickly, judging the validity of the data, and making reasoned comparisons of data can be daunting. Stress-strain curves condense much information about the mechanical behavior of metals into a convenient formo From these basic curves the engineer can extract such information as the strength, ductility, formability, elasticity, and other information useful in predicting the performance of a particular alloy under stress. ASM Intemational published the first edition of the Atlas of StressStrain Curves, a collection of over 550 curves, in 1986. This book, along with the Atlas of Fatigue Curves, Atlas of Creep and StressRupture Curves, and the Atlas of Stress-Corrosion and Corrosion Fatigue Curves, has formed a set of useful materials property resources for the engineer, materials scientist, and designer. Well over three years ago---with the encouragement, assistance, and guidance of the ASM Technical Books and Materials Properties Database Committees-ASM Intemational embarked on the project to create this updated, expanded, and improved Second Edition of the Atlas of Stress-Strain Curves. Sorne of the overriding goals of this project have been to:
Many people are involved in a project of this size, and we would like to thank those who have contributed to, or assisted, this effort. First and foremost, ASM Intemational thanks the materials researchers who created the original curves-without their efforts this volume would not exist. Donna M. Walker, FASM, Stressolvers Inc., and Veronica Flint, ASM staff, initiated the project to revise and expand this book. ASM Intemational thanks them for their efforts in helping to define the goals for this project and in acquiring many of the new curves to be added to the book. Special thanks are extended to Special Metals, Gil Kaufman, FASM, Kaufman Associates, and Bruce Boardman, FASM, Deere & Company, for their contributions of stress-strain curves. Hiro Okamoto and his associates performed the huge task of redrawing the curves to normalize their presentation, and we are gratefuI for their accurate and timely work. The organization and final quality of the data as seen in the book are my responsibility, and any errors, omissions, or misclassifications of alloys are mine. I thank Heather Lampman, the principal copy editor, and the members of the ASM Intemational production staff, who have worked diligently to keep any errors to a minimum. However, in any endeavor of this scope, there will be mistakes. Corrections, comments, and criticisms are invited. It should be noted that most of the data included in this book are not specified as being minimum, typical, or having any defined confidence level associated with them. The reader may want to refer to the source of a particular curve to find additional details. The "Introduction" in this book pro vides a review of the information that can be extracted from stress-strain curves, a clarification of terms used in describing mechanical behavior, and a guide to the limitations ofthe accuracy and precision of the information given.
• Add curves for materials that are especially useful to key industries, including aerospace, automotive, and heavy manufacturing • Seek out curves with a "pedigree" so readers can trace the source of the information and have sorne indication regarding its reliability • Include as much pertinent information as possible for each curve. Factors such as heat-treat condition, product form, thickness, specimen size, orientation, history, testing temperature, and testing rate all affect material s performance and may be helpful when interpreting the curves • Normalize the presentation of the curves to facilitate comparisons among different materials
Charles Moosbrugger Technical Editor ASM Intemational
We feel ASM Intemational has been reasonably successful in achieving these objectives in this edition.
iv
Representation of Stress-Strain Behavior Charles Moosbrugger, ASM International
IT IS APPROPRIATE that a collection of stress-strain curves is named an atlas. An atlas is a collection of figures, charts, or maps, so named because early books pictured the Greek Titan, Atlas, on the cover or title page, straining with the weight of the world and heavens on his shoulders. This concept of visualizing the reaction to mechanical stress is central to development and use of stress-strain curves. This introductory section provides a review of the fundamentals of the mechanical testing that is represented in the curves. The mathematical interpretation of aspects of the curves will aid in analysis of the curves. A list of terms common to stress-strain behavior is given at the end of this section. (Ref 1, 2).
Tensile Testing The simplest loading to visualize is a one-dimensional tensile test, in which a uniform slender test specimen is stretched along its long central axis. The stress-strain curve is a representation of the performance of the specimen as the applied load is increased monotonically usually to fracture. Stress-strain curves are usually presented as: • "Engineering" stress-strain curves, in which the original dimensions of the specimens are used in most calculations. • "True" stress-strain curves, where the instantaneous dimensions of the specimen at each point during the test are used in the ca1culations. This results in the "true" curves being aboye the "engineering" curves, notably in the higher strain portion of the curves. The development of these eurves is described in the following sections. To document the tension test, an engineering stress-strain curve is constructed from the load-elongation measurements made on the test specimen (Fig. 1). The engineering stress, S, plotted on this stressstrain curve is the average longitudinal stress in the tensile specimen. It Strain to fracture
I
Uniforrn strain
~Su
I
E=s/e!~ /
~
f\lecking begins .
!
, 1
"A":' "
1
í
,¡
"-
. . . . . . VS
Tensile strength Fracture
j
stress
1
,/
o 0.002
Fig. 1
Aa
(Eq 1)
The strain, e, plotted on the engineering stress-strain curve, is the average linear strain, which is obtained by dividing the elongation of the gage length ofthe specimen, 8, by its original1ength, Lo: (Eq 2)
Because both the stress and the strain are obtained by dividing the load and elongation by constant factors, the load-elongation curve has the same shape as the engineering stress-strain curve. The two curves frequently are used interchangeably. The units of stress are forcellength squared, and the strain is unitless. The strain axis of curves traditionally are given units of in.lin. or mm1mm rather than being listed as apure number. Strain is sometimes expressed as a percent elongation. The shape of the stress-strain curve and values assigned to the points on the stress-strain curve of a metal depend on its: • • • • • • •
Composition Reat treatment and conditioning Prior history of plastic deformation The strain rate of test Temperature Orientation of applied stress relative to the test specimens structure Size and shape
The parameters that are used to describe the stress-strain curve of a metal are the tensile strength, yield strength or yield point, ultimate tensile strength, percent elongation, and reduction in area. The first three are strength parameters; the last two indicate ductility. The general shape of the engineering stress-strain curve (Fig. 1) requires further explanation. This curve represents the fullloading of a specimen from initialload to rupture. It is a "full-range" curve. Often engineering curves are truncated past the 0.2% yield point. This is the case of many of the curves in this Atlas. Other test data are presented as a "full-range" curve with an "expanded range" to detail the initial parts of the curve.
Linear Segment of Curves
(offset yield strength)
!
¡
s=~
Fracture
f
B
is obtained by dividing the load, P, by the original area of the cross section of the specimen, Aa:
Engineering strain,
e
Engineering stress-strain curve. Intersection of the dashed line with the curve determines the offset yield strength.
From the origin, O, the initial straight-line portion is the elastic region, where stress is linearly proportional to strain. When the stress is removed, if the strain disappears, the specimen is considered completely elastic. The point at which the curve departs from the straight-line proportionality, A, is the proportionallirnit.
Modulus of elasticity, E, also known as Young's modulus, is the slope of this initiallinear portion of the stress-strain curve: E= §...
e
(Eq 3)
2 / Atlas of Stress-Strain Curves
where S is engineering stress and se is engineering strain. Modulus of elasticity is a measure of the stiffness of the material. The greater the modulus, the steeper the slope and the smaller the elastic strain resulting from the application of a given stress. Because the modulus of elasticity is needed for computing deflections of beams and other structural members, it is an important design value. The modulus of elasticity is determined by the binding forces between atoms. Because these forces cannot be changed without changing the basic nature of the material, the modulus of elasticity is one of the most structure-insensitive of the mechanical properties. Generally, it is only slightly affected by alloying additions, heat treatment, or cold work (Ref 3). However, increasing the temperature decreases the modulus of elasticity. At elevated temperatures, the modulus is often measured by a dynamic method (Ref 4). Typical values of modulus of elasticity for common engineering materials are given in Table 1 (Ref 5).
1250 Heat treated chrome-tungsten
alloy
1000 r----+-----r-&L-+-----r----+----~
150
750
a.. '"
:;; uf
"'
¡¡>
1ií
Resilience is the ability of a material to absorb energy when deformed elastically and to retum it when unloaded. This property usually is measured by the modulus of resilience, which is the strain energy per unit volume, Uo, required to stress the material from zero stress to the yield stress, Sx' The strain energy per unit volume for any point on the line is just the area under the curve: (Eq 4)
.5'1
.~
~
500 - 50
0.11% carbon
250 r--tr-r=~==~====~~--r=--_¡r---_¡
From the definition of modulus of elasticity and the aboye definition, the maximum resilience occurs at the yield point and is called the modulus of resilience, UR: UR
lISo So Eo = "2 So Ji
= "2
o "-o---0--1.0-02---0--1.0-04-:----0--1.0-06--~0--1.0-08---:-0.-'-01~O--O.-'012o
S;,
=~
(Eq 5)
This equation indicates that the ideal material for resisting energy loads in applications where the material must not undergo permanent distorTable 1
Typical values for modulus of elasticity Elastic modulus (E)
Metal
GPa
lO' psi
Aluminum Brass, 30 Zn Chromium Copper ¡ron Soft Cast Lead Magnesium Molybdenum Nickel Soft Hard Nickel-silver,55Cu-18Ni-27Zn Niobium Silver Steel Mild 0.75 C 0.75 C, hardened Tool stee1 Too] steel hardened Stainless, 2Ni-18Cr Tantalum Tin Titanium Tungsten Vanadium Zinc
70 1O1 279 130
10.2 14.6 40.5 18.8
211 152 16 45 324
30.7 22.1 2.34 6.48 47.1
199 219 132 104 83
28.9 31.8 19.2 15.2 12.0
2]1 210 201 211 203 215 185 50 120 411 128 105
30.7 30.5 29.2 30.7 29.5 31.2 26.9 7.24 17.4 59.6 18.5 15.2
Source: Ref 5
Strain
Fig. 2
Stress-strain curves for selected steels. Source: Ref 7
tion, such as mechanical springs, is one having a high yield stress and a low modulus of elasticity. For various grades of steel, the modulus of resilience ranges from 100 to 4500 kJ/m3 (14.5 to 650 lbf· in./in. 3 ), with the higher values representing steels with higher carbon or alloy contents (Ref 6). This can be seen in Fig. 2, where the modulus of resilience for the chromiumtungsten alloy would be the greatest of the steels, because it has the highest yield strength and similar modulus of elasticity. The modulus of resilience is represented as the triangular areas under the curves in Fig.3. Figure 2 shows that while the modulus of elasticity is consistent for the given group of steels, the shapes of the curves past their proportionality limits are quite varied (Ref 7).
I I I
High-carbon spring steel
Strain. e
Fig. 3
Comparison of stress-strain curves for a high-strength high-carbon spring steel and a lower-strength structural steel. Point A is the elastic limit 01 the springsteel; point B is the elastic limit 01 the structural steel. The cross-hatched triangles are the modulus 01 resilience (UR). These two areas are the work done on the materials to elongate them or the restoring lorce within the materials.
Representation of Stress-Strain Behavior / 3
Nonlinear Segmenl of Curves lo Yielding The elastic limit, B, on Fig. 1, may coincide with the proportionality limit, or it may occur at sorne greater stress. The elastic limit is the maximum stress that can be applied without permanent deformation to the specimen. Sorne curves exhibit a definite yield point, while others do not. When the stress exceeds a value corresponding to the yield strength, the spedmen undergoes gross plastic deformation. If the load is subsequently reduced to O, 1he specimen will remain permanently deformed. Measures of Yielding. The stress at which plastic deformation or yielding is observed to begin depends on the sensitivity of the strain measurements. With most materials, there is a gradual transition from elastic to plastic behavior, and the point at which plastic deformation begins is difficullt to define with precision. In tests of materials under uniaxial loading, three criteria for the initiation of yielding have been used: the elastic limit, the proportionallimit, and the yield strength.
Elongation (a)
Elastic limit, shown at point B in Fig. 1, is the greatest stress the material can withstand without any measurable permanent strain remaining after the complete release of load. With increasing sensitivity of strain measurement, the value of the elastic limit is decreased until it equals the true elastic limit determined from microstrain measurements. With the sensitivity of strain typically used in engineering studies (10-4 mm/mm or in.lin.), the elastic limit is greater than the proportional limito Deterrnination of the elastic limit requires a tedious incremental loading-unloading test procedure. For this reason, it is often replaced by the proportionallimit. The yield strength, shown at point YS in Fig. 1, is the stress required to produce a small specified amount of plastic deformation. The usual definition of this property is the offset yield strength deterrnined by the stress corresponding to the in1e:rsection of the stress-strain curve offset by a specified strain (see Fig. 1). In the United States, the offset is usually specified as a strain of 0.2% or 0.1 % (e = 0.002 or 0.001). Offset yield strength determination requires a specimen that has been loaded to its 0.2% offset yield strength and unloaded so that it is 0.2% longer than before the test. The offset yield strength is referred to in ISO Standards as the proof stress (RpO,l or R pO ,2). In the EN standards for materials that do not have a yield phenomenon present, the 0,2% proof strength (RpO,2) or 0,5% (Rpo,s) is deterrnined. The nonproportional elongation is either 0.1 %, 0.2%, or 0.5%. The yield strength obtained by an offset method is commonly used for design and specification purposes, because it avoids the practical difficulties of measuring the elastic limit or proportionallimit. Sorne materials have essentially no linear portion to their stressstrain curve, for example, soft copper or gray cast iron. For these materials, the offset method cannot be used, and the usual practice is to define the yield strength as the stress to produce sorne total strain, for example, e = 0.005. The European Standard for general-purpose copper rod, EN 12163 (Ref 8), gives approximate 0,2% proof strength (R pO,2) for information, but it is not a requirement. This approach is followed for other material fOffilS (bar and wire), but for sorne copper tubes, a maximum R pO ,2 is specified For copper alloy pressure vessel plate and sorne spring strip, a minimum RpO,2 is specified.
Materials wiith Yield Point Phenomenon. Many metals, particularly annealed low-carbon stee:l, show a localized, heterogeneous type of transition from elastic to plastic deformation that produces a yield point in the stress-strain curve" Rather than having a flow curve with a gradual transition from elastic: to plastic behavior, such as Fig. 4(a), metal s with a yield point produce a flow curve or a load-elongation diagram similar to Fig. 4(b). The load increases steadily with elastic strain,
'O
ro
.2 .!!! .¡¡;
B
e
<:
Q)
~
Elongation
lb)
Fig. 4
Idealized plots of stress-strain. (al Continuous yielding condition. (b) Discontinuous yielding with an upper yield point A and a relatively constant yieldi ng stress B to C
drops suddenly, fluctuates about sorne approximately constant value of load, and then rises with further strain. In EN standards for materials exhibiting a yield point, the upper yie1d strength, ReH may be specified. The upper and lower yield stress (R eH , ReL) are specified in sorne EN and ISO standards in units of N/mm2 (1 N/mm2 = 1 MPa). EN 10027-1 (Ref9) notes the term "yield strength" as used in this European standard refers to upper or lower yield strength (ReH or ReL)' proof strength (R p), or the proof strength total extension (R t ), depending on the requirement specified in the re1evant product standard. This serves as a caution that the detai1s on how the "yield strength" or "yield point" is defined must be known when making any comparisons or concIusions as to the materials characteristics. Typical yield point behavior of low-carbon steel is shown in Fig. 5. The slope of the initial linear portion of the stress-strain curve, designated by E, is the modulus of elasticity. The load at which the sudden drop occurs is called the upper yield point. The constant load is called the lower yield point, and the e10ngation that occurs at constant load is called the yield-point elongation. The deformation occurring throughout the yield-point elongation is heterogeneous. At the upper yie1d point, a discrete band of deformed metal, often readily visible, appears at a stress concentration such as a fillet. Coincident with the formation of the band, the load drops to the lower yield point. The band then propagates along the 1ength of the specimen, causing the yield-point elongation. In typical cases, several bands form at several points of stress concentration. These bands are generally at approximately 45° to the ten-
4 / Atlas of Stress-Strain Curves
Upper yield point
( i-... Yield point I 1- elongation-+j
I
I
...o
"C
this region, and the specimen begins to neck or thin down locally. The strain up to this point has been uniform, as indicated on Fig. 1. Because the cross-sectional area is now decreasing far more rapidly than the ability to resist the deformation by strain hardening, the actual load required to deform the specimen decreases and the engineering stress defined in Eq 1 continues to decrease until fracture occurs, at X.
...J
The tensile strength, or ultimate tensile strength, Su, is the maximum load divided by the original cross-sectional area of the specimen:
s Unyielded metal Elongation
Fig. 5
Typical yield point behavior of low-carbon steel
sile axis. They are usually cal1ed Lüders bands, Hartmann lines, or stretcher strains, and this type of deformation is sometimes referred to as the Piobert effect. They are visible and can be aesthetically undesirab1e. When several Lüders bands are formed, the flow curve during the yield-point elongation is irregular, each jog corresponding to the formation of a new Lüders bando After the Lüders bands have propagated to cover the entire length of the specimen test section, the flow will increase with strain in the typical manner. This marks the end of the yield-point elongation. The transition from undeformed to deformed material at the Lüders front can be seen at low magnification in Fig. 6. The rough surface areas are the Lüders bands in the low-carbon steel. These bands are also formed in certain aluminum-magnesium alloys.
NonJinear Segment of Continued Deformation
Strain Hardening. The stress required to produce continued plastic deformation increases with increasing plastic strain; that is, the metal strain hardens. The volume of the specimen (area x length) remains constant during plastic deformation, AL = AoLo, and as the specimen elongates, its cross-sectional area decreases uniformly along the gage length. Initially, the strain hardening more than compensates for this decrease in area, and the engineering stress (proportional to load P) continues to rise with increasing strain. Eventually, a point is reached where the decrease in specimen cross-sectional area is greater than the increase in deformation load arising from strain hardening. This condition will be reached first at sorne point in the specimen that is slightly weaker than the rest. All further plastic deformation is concentrated in
u -
P max Ao
(Eq 6)
The tensile strength is the value most frequently quoted from the results of a tension test. Actually, however, it is a value of little fundamental significance with regard to the strength of a metal. For ductile metals, the tensile strength should be regarded as a measure of the maximum load that a metal can withstand under the very restrictive conditions of uniaxialloading. This value bears little relation to the useful strength of the metal under the more complex conditions of stress that usually are encountered. For many years, it was customary to base the strength of structural members on the tensile strength, suitably reduced by a factor of safety. The current trend is to the more rational approach of basing the static design of ductile metals on the yield strength. However, because of the long practice of using the tensile strength to describe the strength of material s, it has become a familiar property, and as such, it is a useful identification of a material in the same sense that the chemical composition serves to identify a metal or alloy. Furthermore, because the tensile strength is easy to determine and is a reproducible property, it is use fui for the purposes of specification and for quality control of a product. Extensive empirical correlations between tensile strength and properties such as hardness and fatigue strength are often useful. For brittle materials, the tensile strength is a valid design criterion.
Measures of Ductility. Currently, ductility is considered a qualitative, subjective property of a material. In general, measurements of ductility are of interest in three respects (Ref 10): • To indicate the extent to which a metal can be deformed without fracture in metalworking operations such as rolling and extrusion • To indicate to the designer the ability of the metal to flow plastically before fracture. A high ductility indicates that the material is "forgiving" and likely to deform locally without fracture should the designer err in the stress calculation or the prediction of severe loads. • To serve as an indicator of changes in impurity level or processing conditions. Ductility measurements may be specified to assess material quality, even though no direct relationship exists between the ductility measurement and performance in service. The conventional measures of ductility that are obtained from the tension test are the engineering strain at fracture, er, (usually called the elongation) and the reduction in area at fracture, q. Elongation and reduction in area usually are expressed as a percentage. Both of these properties are obtained after fracture by putting the specimen back together and taking measurements of the finallength, Lr, and final specimen cross section, Af: (Eq 7)
Ao-Af
q=~
Fig. 6
Lüders bands (roughened areas), which have propagated along the length of a specimen of annealed steel sheet that was tested in tension. Unpolished, unetched. Low magnification
(Eq 8)
Because an appreciable fractíon of the plastic deformation will be concentrated in the necked region of the tension specimen, the value of
Representation of Stress-Strain Behavior / 5
will depend 0111 the gage length Lo over which the measurement was taken (see the section of this artiele on ductility measurement in tension testing). The smaller the gage length, the greater the contribution to the overall elongation from the necked region and the higher the value of ef. Therefore, when reporting values of percentage elongation, the gage length, Lo, should always be given. Reduction in area does not suffer from this difficulty. These values can be converted into an equivalent zero-gage-length elongation, eo. From the constancy of volume relationship for plastic deformation (AL = AoLo):
ef
L - Lo Ao 1 1 eo = - - = -- -1 = - - --1 = - Lo
A
I-q
I-q
for a metal strained in tension by the amount shown on the curve. Thus, if the load is removed at this point and then reapplied, the material will behave elastically throughout the entire range of reloading. The true stress,
The toughnE~ss of a material is its ability to absorb energy up to the point of fracture or rupture. The ability to withstand occasional stresses aboye the yieldl stress without fracturing is particularly desirable in parts such as freight-car couplings, gears, chains, and crane hooks. Toughness is a commonly used concept that is difficult to precisely define. Toughn(~ss may be considered to be the total area under the stress-strain curve to the point of fracture. This area, which is referred to as the modulus of toughness, UT , is the amount of work per unit volume that can be done on the material without causing it to rupture. Figure 3 shows the stress-strain curves for high- and low-toughness materials. The high-carbon spring steel has a higher yield strength and tensi1e strength than the medium-carbon structural steel. However, the structural steel is more ductile: and has a greater total elongation. The total area under the stress-strain curve is greater for the structural steel; therefore, it is a tougher mate:rial. This illustrates that toughness is a parameter that eomprises both strength and ductility.
True Stress-Strain Curves The engineering stress-strain curve does not give a true indication of the deformation characteristics of a metal, because it is based entirely on the original dimensions of the specimen and these dimensions change continuously during the test. Also, a ductile metal that is pulled in tension becomes unstable and necks down during the course of the test. Because the cross-sectional area of the specimen is decreasing rapidly at this stage in the test, the load required to continue deformation lessens. The average stress based on the original area likewise decreases, and this produces the downtum in the engineering stress-strain curve beyond the point of maximum load. Actually, the metal continues to strain harden to fracture, so that the stress required to produce further deformation should also increase. If the true stress, based on the actual crosssectional area of the specimen, is used, the stress-strain curve increases continuously to fracture. If the strain measurement is a1so based on instantaneous measurement, the curve that is obtained is known as truestress/true-strain curve. Flow Curve. The true stress-strain curve is also known as a flow curve, because it represents the basic plastic-flow characteristics of the material. Any point on the flow curve can be considered the yield stress
is expressed in terms of engineering stress, S, by:
p
a
= Ao (e + 1) =S¡(e + 1)
(Eq 10)
The derivation of Eq 10 assumes both constancy of volume (AL = AoLo) and a homogeneous distribution of strain along the gage length of the tension specimen. Thus, Eq 10 should be used only until the onset of necking. Beyond the maximum load, the true stress should be determined from actual measurements of load and cross-sectional area. p
(Eq 9)
This represents the elongation based on a very short gage length near the fracture. Another way to avoid the complications resulting from necking is to base the percentage elongation on the uniform strain out to the point at which necking begins. The uniform elongation, eu, correlates well with stretch-forming operations. Because the engineering stress-strain curve often is quite flat in the vicinity of necking, it may be difficult to establish the stfalin at maximum load without ambiguity. In this case, the method suggested in Ref 11 is useful.
(J,
A
a=
(Eq 11)
The true strain, E, may be determined from the engineering or conventional strain, e. From Eq 2:
e=
M., =
L-Lo
Lo
=1:...._ 1
(Eq 12)
Lo
Lo
To determine the true strain, the instantaneous change in length (dI) is divided by the length, 1: E= (
E=
~l =In(~)
(Eq 13)
In (e + 1)
(Eq 14)
This equation is applicable only to the onset of necking for the reasons discussed aboye. Beyond maximum load, the true strain should be based on actual area or diameter, D, measurements: Ao (n D6)/4 Do E = In A = In (n D2)/4 = 2 In D
(Eq 15)
Figure 7 compares the true-stress/true-strain curve with its corresponding engineering stress-strain curve. Note that, because of the relatively large plastic strains, the elastic region has been compressed into the y-axis. In agreement with Eq 10 and 14, the true-stress/true-strain curve is always to the left of the engineering curve until the maximum load is reached. Necking. Beyond maximum load, the high, localized strains in the necked region that are used in Eq 15 far exceed the engineering strain
True stress/true strain curve
'"'"
Q)
c5i • Maximum load o Fracture
O Strain
Fig. 7
Comparison of engineering and true-stress/true-strain curves
6 / Atlas of Stress-Strain Curves
-
b
~., VI
E
n = 1/2
K
el
.3
10 Trua strain,
Fig. 8
E
Log-Iog plot of true-stress/true-strain curve. n is the strain-hardening exponent; K is the strength coefficient.
1.0
Fig. 9 calculated from Eq 2. Frequently, the flow curve is linear from maximum load to fracture, while in other cases its slope continuously decreases to fracture. The formation of a necked region or mild notch introduces triaxial stresses that make it difficult to determine accurately the longitudinal tensile stress from the onset of necking until fracture occurs. This concept is discussed in greater detail in the section "Corrected Stress-Strain Curves" in this artiele. The following parameters usually are deterrnined from the true-stress/true-strain curve. The true stress at maximum load corresponds to the true tensile strength. For most materials, necking begins at maximum load at a value of strain where the true stress equals the slope of the flow curve. Let (Ju and Eu denote the true stress and true strain at maximum load when the cross-sectional area of the specimen is Au. From Eq 6 the engineering ultimate tensile strength can be defined as: S - Pmax u -
Ao
(Eq 16)
and the true ultimate tensile strength is:
Various forms of power curve cr = KE n
measured values of ef. However, for cylindrical tensile specimens, the reduction in area, q, is related to the true fracture strain by: Ef=ln _1_
(Eq 22)
l-q
The true uniform strain, Eu, is the true strain based only on the strain up to maximum load. It may be calculated from either the specimen cross-sectional area, Au. or the gage length, La, at maximum load. Equation 15 may be used to convert conventional uniform strain to true uniform strain. The uniform strain frequently is useful in estimating the formability of metal s from the results of a tension test: Eu=In Ao
(Eq 23)
Au
The true local necking strain, En, is the strain required to deform the specimen from maximum load to fracture: A En= In--..l!.
(Eq 24)
Af
(Eq 17)
Mathematical Expression of the Flow Curve. The flow curve of many metal s in the region of uniform plastic deformation can be expressed by the simple power-curve relation:
Eliminating P m.x yields: cru = Su -Ao Au
(Eq 18)
cr = KE n
and from Eq 15: AoJA = eE
(Eq 19)
where e is the base of naturallogarithm, so (Eq 20)
The true fracture stress is the load at fracture divided by the crosssectional area at fracture. This stress should be corrected for the triaxial state of stress existing in the tensile specimen at fracture. Because the data required for this correction frequently are not available, true fracture stress values are frequently in error. The true fracture strain, Ef, is the true strain based on the original area, A o, and the area after fracture, Af : Ao
Ef=In Af
(Eq 21)
This parameter represents the maximum true strain that the material can withstand before fracture and is analogous to the total strain to fracture of the engineering stress-strain curve. Because Eq 14 is not valid beyond the onset of necking, it is not possible to calculate Ef from
(Eq 25)
where n is the strain-hardening exponent and K is the strength coefficient. A log-log plot of true stress and true strain up to maximum load will result in a straight line if Eq 25 is satisfied by the data (Fig. 8). The linear slope of this line is n, and K is the true stress at E = 1.0 (corresponds to q = 0.63). As shown in Fig. 9, the strain-hardening exponent may have values from n = O (perfectly plastic solid) to n = 1 (elastic solid). For most metals, n has values between 0.10 and 0.50 (see Table 2).
Table 2
Values for n and K for metals at room temperature K
Metals
Condition
0.05% carbon steel SAE 4340 steel 0.6% carban steel
Annealed Annealed Quenched and tempered at 540 oc (1000 °F) Quenched and tempered at 705 oc (1300 °F) Annealed Annealed
0.6% carbon steel Copper 70/30 brass
n
MPa
ksi
Ref
0.26 0.15 0.10
530 641 1572
77 93 228
12 12 13
0.19
1227
178
13
0.54 0.49
320 896
46.4 130
12 13
Representation of Stress-Strain Behavior / 7
The rate of strain hardening do/de is not identical to the strainhardening exponent. From the definition of n: n
= d (log 01 = d (log E)
d (In a) d (In E)
=
Eda adE
or
(Eq 26)
Deviations from Eq 25 freque:ntly are observed, often at low strains (10-3) or high strains (E = 1.0) . One cornmon type of deviation is for a log-log plot ofEq 25 to result in two straight lines with different slopes. Sometimes data that do not plot according to Eq 25 will yield a straight line according to the relationship: (Eq 27)
f.o can be considered to be the amount of strain hardening that the material received prior to the tension test (Ref 14). Another cornmon variation on Eq 25 is. the Ludwik equation: (Eq 28)
The true strain term in Eq 25 to 28 properly should be the plastic strain, Ep =Etotal -
EE
Ep = Etotal -
Ji
a
(Eq 31)
where EE represents elastic strain. Graphically, this is shown on the engineering curve as a region of elastic elongation and a region of plastic elongation surnmed together to make the total elongation.
Instability in Tension. Necking generally begins at maximum load during the tensile deformation of ductile metal. An ideal plastic material in which no strain hardening occurs would become unstable in tension and begin to neck as soon as yielding occurred. However, an actual metal undergoes strain hardening, which tends to increase the load-carrying capacity of the specimen as deformation increases. This effect is opposed by the gradual decrease in the cross-sectional area of the specimen as it elongates. Necking or localized deformation begins at maximum load, where the increase in stress due to decrease in the crosssectional area of the specimen becomes greater than the increase in the load-carrying ability of the metal due to strain hardening. This condition of instability leading to localized deformation is defined by the condition that P is at its maximum, dP = O:
where 0'0 is the yield stress, and K and n are the same constants as in Eq 25. This equation may be more satisfying than Eq 25, because the latter implies that at O true strain the stress is O. It has been shown that 0'0 can be obtained from the intercept of the strain-hardening portion of the stress-strain curve and the elastic modulus line by (Ref 15):
P=aA
ao = (:" ) l/(l-n)
From the constancy-of-volume relationship:
(Eq 29)
The true-stress/true-strain curve of metal s such as austenitic stain1ess steel, which deviate markedly from Eq 25 at low strains (Ref 16), can be expressed by: (Eq30)
where eK ¡ is approximately equal to the proportionallimit, and n¡ is the slope of the deviation of stress from Eq 25 plotted against E. Other expressions for the flow curve are available (Ref 17, 18).
a!
Subtangent of unit,.
versus
(Eq 32)
dP = adA + Ada
=O
(Eq 33)
dL =_dA =dE
L
(Eq 34)
A
and from the instability condition (Eq 32): dA A
da
(Eq 35)
a
so that at a point of tensile instability: da -=a dE
(Eq 36)
E
j:='
(b)
(a)
B Engineeríng strain
Fig. 10
Graphical interpretation 01 necking criterion. The point 01 necking at maximum load can be obtained lrom the true-stress/true-strain curve by linding (a) the point on the curve having a subtangent of unity or (b) the point where dcr/ck = (j.
Fig.11
Considére's construction for the determination 01 the point 01 maximum load. Source: Rel 19
8 / Atlas of Stress-Strain Curves
Therefore, the point of necking at maximum load can be obtained from the true-stress/true-strain curve by finding the point on the curve having a subtangent of unity (Fig. lOa) or the point where the rate of strain hardening equals the stress (Fig. lOb). The necking criterion can be expressed more explicitly if engineering strain is used. Starting with Eq 36: dL
da da de da ~ da L da - = - - = - = dL = - - = - (1 +e)=a dE de dE de L de Lo de
(Eq 37)
Equation 37 permits an interesting geometrical construction for the determination of the point of maximum load (Ref 19). In Fig. 11, the stress-strain curve is plotted in terms of true stress against engineering strain. Let point A represent a negative strain of 1.0. A line drawn from point A, which is tangent to the stress-strain curve, will establish the point of maximum load, because according to Eq 37, the slope at this point is a/(l + e). By substituting the necking criterion given in Eq 36 into Eq 26, a simple relationship for the strain at which necking occurs is obtained. This strain is the true uniform strain, Eu: (Eq 38)
Although Eq 26 is based on the assumption that the flow curve is given by Eq 25, it has been shown that Eu = n does not depend on this powerlaw behavior (Ref 20).
Corrected Stress-Strain Curves Stress Distribution at the Neck. The formation of a neck in the tensile specimen introduces a complex triaxial state of stress in that region. The necked region is in effect a mild notch. A notch under tension produces radial stress, a r, and transverse stress, a¡, which raise the value of longitudinal stress required to cause the plastic flow. Therefore, the average true stress at the neck, which is determined by dividing the axial tensile load by the minimum cross-sectional area of the specimen at the neck, is higher than the stress that would be required to cause flow if simple tension prevailed.
Figure 12 illustrates the geometry at the necked region and the stresses developed by this localized deformation. R is the radius of curvature of the neck, which can be measured either by projecting the contour of the necked region on a screen or by using a tapered, conical radius gage. Bridgman made a mathematical analysis that provides a correction to the average axial stress to compensate for the introduction of transverse stresses (Ref 21). This analysis was based on the following assumptions: • The con tour of the neck is approximated by the are of a circle. • The cross section of the necked region remains circular throughout the test. • The von Mises criterion for yielding applies. • The strains are constant over the cross section of the neck. According to thls analysis, the uniaxial flow stress corresponding to that which would exist in the tension test if necking had not introduced triaxial stresses is: (Eq 39)
a=
where (ax)avg is the measured stress in the axial direction (load divided by minimum eros s section). Figure 7 shows how the application of the Bridgman correction changes the true-stress/true-strain curve. A correction for the triaxial stresses in the neck of a flat tensile specimen has been considered (Ref 22). The values of a/R needed for the analysis can be obtained either by straining a specimen a given amount beyond necking and unloading to measure a and R directly, or by measuring these parameters continuously past necking using photography or a tapered ring gage (Ref 23). To avoid these measurements, Bridgman presented an empírical relation between a/R and the true strain in the neck. Figure 13 shows that this gives close agreement for steel specimens, but not for other metals with widely different necking strains. A much better correlation is obtained between the Bridgman correction and the true strain in the neck minus the true strain at necking, Eu (Ref 25).
1.00
0.75 L-_ _.l......_ _...l-_ _....J..._ _--' 1.5 2.0 1.0 o 0.5 5train, •
Fig. 12
Stress distribution at the neck oí a tensile specimen. (a) Geometry 01 necked region. R is the radius 01 curvature 01 the neck; a IS the mlnlmum radius at the neck. (b) Stresses acting on element at point O. crx is the stress in the axial direction; cr, is the radial stress; a, is the transverse stress.
rr---,...-----,.-----,...----,
Fig. 13
Relationship between Bridgman correction factor a/(crx)avg and true tensile strain. Source: Re! 24
Representation of Stress-Strain Behavior / 9
Ductility
Compression Testing
Ductility Me~LSurement in Tension Testing. The measured elongation from a tension specimen depends on the gage length of the specimen or the dime:nsions of its cross section. This is because the total extension consists of two components: the uniform extension up to necking and the localized extension once necking begins (Fig. 1). The extent of uniform extension depends on the metallurgical condition of the material (thmugh En) and the effect of specimen size and shape on the development of the neck. The shorter the gage length, the greater the influence of localized deformation at the neck on the Ilotal elongation of the gage length. The extension of a specimen at fracltUre can be expressed by:
The compression test consists of deforming a cylindrical specimen to produce a shorter cylinder of larger diameter (upsetting). The compression test is a convenient method for determining the stress-strain response of materials at large strains (e > 0.5) because the test is not subject to the instability of necking that occurs in a tension test. AIso, it may be convenient to use the compression test because the specimen is relatively easy to make, and it does not require a large amount of material. The compression test is frequently used in conjunction with evaluating the workability of materials, especially at elevated temperature, because most deformation processes, such as forging, have a high component of compressive stress. The test is also used with brittle materials, which are difficult to machine into test specimens and difficult to tensile test in perfect alignment. There are two inherent difficulties with the compression test that must be overcome by the test technique: buckling of the specimen and barreling of the specimen. Both conditions cause nonuniform stress and strain distributions in the specimen that make it difficult to analyze the results.
(Eq 40)
where a is the local necking extension and euLu is the uniform extension. The tensile elongation is then: ef
4-Lo
IX
= ----¡;;- = Lo + eu
(Eq 41)
This elearly indicates that the total elongation is a function of the specimen gage length. The shorter Ilhe gage length, the greater the percent elongation. Numerous attempts have been made to rationalize the strain distribution in the tension test. Perhaps the most general conelusion that can be drawn is that geometrically similar specimens develop geometrically similar necked regions. Further details on the necking phenomenon can be found in the artiele "Mechanical Behavior under Tensile and Compressive Loads" in Mechanical Testing and Evaluation, Volume 8 of the ASM Handbook (Ref26).
Notch Tensil,e Test. Ductility measurements on standard smooth tensile specimens do not always reveal metallurgical or environmental changes that lead to reduced local ductility. The tendency for reduced ductility in the presence of a triaxial stress field and steep stress gradients (such as a rise al: a notch) is caBed notch sensitivity. A common way of evaluating notch sensitivity is a tension test using a notched specimen.
Buckling is a mode of failure characterized by an unstable lateral material deflection caused by compressive stresses. Buckling is controlled by selecting a specimen geometry with a low length-to-diameter ratio. UD should be less than 2, and a compression specimen with UD = 1 is ofien used. It also is important to have a very well-aligned load train and to ensure that the end faces of the specimen are parallel and perpendicular to the load axis (Ref 27). Ofien a special alignment fixture is used with the testing machine to ensure an accurate load path (Ref28). Barreling is the generation of a convex surface on the exterior of a cylinder that is deformed in compression. The cross section of such a specimen is barrel shaped. Barreling is caused by the friction between the end faces of the compression specimen and the anvils that apply the load. As the cylinder decreases in height (h), it wants to increase in diameter (D) because the volume of an incompressible material must remain constant: 1t Di
ro
!l.
4 2
200
5
ro
en ~
2
:2'
/.}
350
........-:: ~
al 300 en
/~~/8"
I(
100
1-
50
o
O
I
ID
100
::::>
¡!::
0.20
0.30
0.40
0.50
50
Comparison of true stress-true strain curves in tension and compression (various lubricant conditions) for AI-2Mg alloy. Curve 2, Molykote spray; curve 4, boron nitride + alcohol; curve 5, Teflon + Molykote spray; curve 8, tensile test. Sou rce: Ref 3 O
1
3
!i
f
f/
O O
0.20
0.40
0.60
0.80
1.00
1.20
True compressive strain
True strain
Fig. 14
~4
~~
~
o u
~ 2/
o.. 150 E
Tensile necking instability
0.10
~
-¡¡¡ 250 ID > .¡;; en 200
~
150
-¡¡¡ ID
(Eq 42)
4
~
!l.
.,
-
400
250
:2'
h¡ _ D;h2
4
Fig. 15
Flow curves for AI-2Mg alloy tested in compression for various lubricant conditions out to E = 1.0. Curve 1, molygrease; curve 2, Molykote spray; curve 3, boron-nitride spray; curve 4, boron-nitride and alcohol; curve 5, Teflon and Molykote spray; curve 6, polished dry anvils; curve 7, grooved anvils. Source: Ref 30
10 / Atlas of Stress-Strain Curves Compressive tangent modulus, GPa
o 14 28 42 56 70 84 1oo,------,------,------,------,-------,-----,7oo
Calculation of Compressive Stress and Strain. The calculation of stress and strain for the compression test is based on developing a test condition that minimizes friction (and barreling) and assumes the stress state is axial compression. When friction can be neglected, the uniaxial compressive stress (flow stress) is related to the deformation force P by:
80r-----~------T_----_+------4_----~r_----~560
Clf
420 .¡¡; -"" uf
en ~
éií 40
280
A
rtDZ
(Eq 43)
rtD ¡h¡
where the last term is obtained by substituting from Eq 42. In Eq 43, subscript l refers to the initial values of D and h, while subscript 2 refers to conditions at sorne subsequent value of specimen height, h. Equation 43 shows that the flow stress can be obtained directly from the load P and the instantaneous height (h 2), provided that friction can be neg1ected. The true strain in the compression test is given by: E
20r-____~------+_----_+------~----~_+----~140
4P 4Ph z = -P = --= ----2
=ln(~~) = 21n(~~)
(Eq44)
where either the displacement of the anvil or the diameter of the specimen can be used, whichever is more convenient. L -_ _ _ _~_ _ _ _ _ _~_ _ _ _ _ _~_ _ _ _ _ _L __ _ _ _~_L_ _ _ _~O
2
Fig. 16
4
8 6 Strain, 0.001 in./in. Compressive tangent modulus? 1O psi
10
12
Curve combining compressive stress-strain with compressive tangent modulus
As the material spreads outward over the anvils, it is restrained by the friction at this interface. The material near the midheight position is less restrained by friction and spreads laterally to the greatest extent. The material next to the anvil surfaces is restrained from spreading the most; thus, the creation of a barreled profile. This deformation pattem also 1eads to the development of a region of relatively undeformed materials under the anvil surfaces. This deformation behavior c1early means that the stress state is not uniform axial compression. In addition to the axial compressive stress, a circumferential tensile stress develops as the specimen barreIs (Ref 29). Because barreling increases with the specimen ratio D/h, the force to deform a compression cylinder increases with D/h.
Minimizing barreling of the compression specimen can be accomplished by minimizing friction between the ends of the specimen and the anvils. This is done by using an effective lubricant and machining concentric rings on the end of the specirnen to retain the lubricant and keep it from being squeezed out. An extensive series of tests have shown what works best (Ref 30). Figure 14 shows the true stress-true strain curve (flow curve) for an annealed AI-2Mg alloy. Stress and strain were calculated as described in the previous section. Note how the flow curve in compression agrees with that determined in a tensile test and how the compressive curves extend to much larger strains because there is no specimen necking. Figure 15 extends the strain over double the range of Fig. 14. Note that once beyond E > 0.5, the curves begin to diverge depending on the effectiveness of the lubrication. The highest curve (greatest deviation from uniaxial stress) is for grooved anvils (platens) that dig in and prevent sidewise flow. The least friction is for the condition where a Teflon (EJ. DuPont de Nemours & Co., Inc., Wilmington, DE) film sprayed with Molykote (Dow Coming Corporation, Midland, MI) is placed between the anvil and the specimen.
~
--
./
t
t
_/
I
/"
/ Slrain(g) _
Strain(g) _ (a)
Fig. 17
(b)
Differences between constant stress increments and constant strain increments. (a) Equal stress increments result in strains of increasing increments. (b) Equal strain increments result in decreasing stress increments.
Representation of Stress-Strain Behavior / 11
1[1'
10'
lO'
lO·
10- 8
10- 6
10-'
10-'
lO·
10- 6
10- B
10'
10'
lO'
Characteristic time Is)
rl"--,;-~-"'-"T"-"T'-"" -",r--""~--"--"--~,"'l-r,--r~--fl--¡I-,I--I~~ Strain rate Is- ) I I
~ ~ l::
;-: ~
Creep
Constant load or strnss machine
Quasi-static
~
Bar impact
~ ~
I
I I I I
: Pneumatic : Mechanical or or I mechanical I ex pi osi ve I machines I impact
Hydraulic or screw machine
I I I
Light gas gun or explosively driven plate impact
Usual method of loading
I
I U Mechanical I Constant strain rate test
I
forces
High-velocity plate impact
I
I
I
~-Inertia
~ strain rate ~ ~ ~
1
I Strain versus time or creep rate recorded
~ Intermediate ~
I
I
I
11 resonance ElasticH in specimen plastic wave 1I and Ipropagation I 11 machine I I
neglected_::~..o(e-----Inertia forces
-----sotherma
lO 11
Shock wave propagation Dynamic considerations
important _ _ _+-/
in testing
Adiabatic------~lO·1
E
_ _, - - - - - - - - - P l a n e stress ----------;o~..¡I...E;-Plane strain-;o. ~
Increasing stress levels
Fig. 18
Strain-rate ranges and associated experimental equipment, conditions, and consequences
Essentially no barreling occurs in room-temperature compression tests when Teflon film is placed between the anvil and the end of the specimen. Because the film will eventually tear, it is necessary to run the test increffil~ntally and replace the film when an electrical signal indicates that there is no longe:r a continuous film. Obviously, the need to run the test incrementally is inconvenient. A series of single-increment compression tests on a range of materials with strain-hardening exponents from n = 0.08 to 0.49 showed that lubricant conditions do not become significant until E > 0.5 so long as
Elastic range
Plastic (inelastic) range Yield-point elon9ation Increase in yield point caused by strain hardening
I
and
.1
Strain-hardening range
50 40
" ,',
/
Initial tension loading
'~---'C;=""""''''_''''__'_'"-/'/:,,/'--...8 /'A .
/--------
,
_____ :i
,Second unloading ¡ and reloading
First unloading ..
1/
n > 0.15. For strains E ~ 1.0, a grooved specimen with molybdenum disulfide (MoS 2) grease lubricant gave consistently good results. Nearly as good results are achieved with smooth anvils and a spray coat of MoS 2 (Ref 30). Another approach to minimize the effects of barreling is to remachine the specimens to their original diameter after sorne degree of deformation. This is costly and inconvenient and adds uncertainties to the results. For additional details on compression testing, see the artiele "Uniaxial Compression Testing" in Mechanical Testing and Evaluation, Volume 8 of the ASM Handbook.
reIO¡¡din~,::
/
~ eh
~ --~~~~~~--,-----~-,----~--,-~-,~~~--~--~
éiS
StrainDuctility after second reloading Residuall straln _ _ _ _ Ductility after first reloading
I
1,
'"
1 - - - - - - Ductility 01 virgin material--------.,..¡
Compression reloading
Fig. 19
Effects of prior tensile loading on stress-strain behavior; the graph is not to scale. The solid line represents the behavior of a virgin piece. The dotted line is a specimen that has been unloaded at A and then reloaded. The dashed fine represents a second unloading at B. In each case the stress is based on the cross-sectional area of the specimen measured after the unloading.
Fig. 20
¿ o -30 .~ o. -40 E
8
-50
An example of the Bauschinger effect and hysteresis loop in tension-compression-tension loading. The initial tension loading is to about 0.001 strain, followed by compression again to 0.001 strain.
12 / Atlas of Stress-Strain Curves
Tangent Modulus Curves The tangent modulus, E¡, is the slope of the stress-strain curve at any point on the curve. _ dS E¡ de
(Eq 45)
Below the proportionality limit, El has the same value as E. Figure 10 has a construction of El = 1 at the point where the strain was Eu. The slope has the same units as the stress. Many of the curves in the Atlas have the plot of the tangent modulus superimposed on the stress-strain curve. These curves have dual units along the x-axis, one set for strain and one set for El' Figure 16 is an example. The modulus of elasticity can be visually estimated on the linear segment of the stress-strain curve as slightly more than 280 MPa/4 X 0.001 = 70,000 MPa or 70 GPa (40 ksi/4 X 0.001 = 10,000 ksi, or 10 X 106 psi). This corresponds to the constant value (verticalline) on the tangent modulus curves up to the proportionality limit. At higher stress, the stress-strain curves flatten and the tangent modulus curves decrease in value.
Torsional Testing Torsion tests can be carried out on most materials to determine mechanical properties such as modulus of elasticity in shear, shear yield strength, ultimate shear strength, modulus of rupture in shear, and ductility. The torsion test can also be conducted on full-size parts (shafts, axles, and pipes) and structures (beams and frames) to determine their response to torsionalloading. In torsion testing, unlike tensile testing and compression testing, large strains can be applied before plastic instability occurs, and complications due to friction between the test specimen and dies do not arise.
Torsion tests are most frequently carried out on prismatic bars of circular cross section by applying a torsional moment about the longitudinal axis. The shear stress versus shear strain curve can be determined from simultaneous measurements of the torque and angle of twist of the test specimen over a predetermined gage length. When converted from torque (in units of newton-meters or inchpounds) and angular displacement (in degrees or radians) torsional stress-strain has the same units as engineering stress-strain, but the variance from "true" stress-strain is typically much less. On a cylindrical specimen that does not buckle, the difference is 5% or less from engineering to "true" stress-strain, even in the plastic (nonlinear) range. There is evidence that torsion testing of hollow tubes is one of the better ways to determine the effects of strain, strain rate, and temperature on the flow stress of materials over the range of these variables usually encountered in the metal working process. Details on torsional testing and analysis can be found in the articles "Fundamental Aspects of Torsional Loading" and "Shear, Torsion, and Multiaxial Testing" in Mechanical Testing and Evaluation, Volume 8 of ASM Handbook.
Mechanical Testing Details For credibility and repeatability, tests that are the basis of the stressstrain curves are conducted in accordance with sorne industry, national, or multinational standard. In the Atlas, when the source documentation cites a standard, it is so Índicated in the caption. These standards provide insight to interpret the data. Details of testing methods are found in Mechanical Testing and Evaluation, Volume 8 of ASM Handbook. Pertinent artícles include: • • • • • • • • • • •
"Testing Machines and Strain Sensors" "Accreditation of Mechanical Testing Laboratories" "Mechanical Behavior under Tensile and Compressive Loads" "Stress-Strain Behavior in Bending" "Bend Testing" "Fundamental Aspects of Torsional Loading" "Uniaxial Tension Testing" "Uniaxial Compression Testing" "Rot Tension and Compression Testing" "Tension and Compression Testing at Low Temperatures" "Shear, Torsion, and Multiaxial Testing"
1 b
Strain,E_
Fig. 21 Two types oi hysteresis stress-strain loops resulting irom Bauschinger effect in titanium alloys
Fig. 22 Stress-strain loop for constant-strain cycling
Representation of Stress-Strain Behavior / 13
()"
()"
()"
.-~v----!:--- E
Steady state hysteresis loops
Cyclic stress-strain curve
Fig. 23
Construction of cyclic stl·ess-strain curve by joining tips of stabilized hysteresis loops
Test Variables The condition of the test environment, composition, conditioning, size, shape, and history of the specimen are arnong the factors affecting the stress-sltrain data. These pararneters are given to the extent that they are available. Test Tempelrature. Relative to room-temperature (RT) tests, most materials become stronger, but less ductile, at lower temperatures, and more ductile, but weaker, at higher temperatures. There are anomalous behaviors such as blue brittleness. Carbon steels generally exhibit an increase in strength and a reduction of ductility and toughness at temperatures around 300 oC (570 °P). Because such temperatures produce a bluish temper color on the surface of the specimen, this problem has been called blue brittleness. Typically, brittleness is associated with cold-temperature behavior. Speed of Tt!St. ASTM E 8 (Ref 31) lists five ways of defining the speed of the test: • • • • •
Rate of strailning the specimen, de/dt Rate of stressing the specimen, dS/dt Rate of the separation of tlle test machine Ileads during the test Elapsed time for completing part or all of the test Pree-running cross-head slPeed (speed of machine heads when unloaded)
Strain Rate. Average strain rates for most tension tests range between 10-2 and 10-5 s-l. Greater strain rates (10- 1 and 102 s-I) are considered dynarnic tests. Por a specimen of initial gage length Lo and deformed lenglth L, the specific deformation rate is: de dt
1 d(L- J'-t!)
= Lo ----;¡¡-
(Eq 46)
If tlle deformation occurs Ilomogeneously througllout the specimen, then the specific deformation rate corresponds everywhere to the strain rateo However, if tlle deformation is nonhomogeneous, tllen tlle strain (and strain rate) varíes the specimen length, and the specific deformation rate represents the spatial average strain rateo A well-known exarnpIe of nonhomogeneous deformation is the propagation of deformation bands called Lüders bands. Stress Rate. Pigure 17 illustrates the differences in curves constructed from constant stress increments and constant strain increments. Slow Speeds. Under relatively slow straining, most materials are assumed to transfer the heat generated by plastic deformation to their surroundings; that is, the straining is assumed to be isothermal (no change of temperature). The degree to which slow tension tests remain truly isothermal has been investigated (Ref 32). The flow stress, which is the uniaxial stress needed to continue plastic deformation of the material at a given stage of a test, is then assumed to depend only on strain and strain rateo The strain-hardening pararneter n has been defined. Prom Eq 26: E da n=--
a dE
(Eq 47)
In an analogous manner, the strain-rate sensitivity pararneter m can be defined as:
E da m=-----:a dE
(Eq 48)
Both n and m are functions of strain and strain rateo m can be negative under sorne conditions. However, average values frequently are selected for these pararneters, which are then treated as constants. Values of n usually are between 0.1 and 0.5 for metals; they are determined from, but not identical to, strain-hardening rates. Values of
14 / Atlas of Stress-Strain Curves
C Monotonic
Cyclic
(a) Cyelie softening
(b) Cyelie hardening C
M
_.."e.::;...._-...
C
Slrain,
E
(e) Cyelically stable
Fig. 24
Slrain,
M
E
(d) Mixed behavior
Examples oí various types 01 cyclic stress-strain
m for metals are usually much smaller than the corresponding n values (m < 0.1). m does increase with temperature. However, fine-grained metals have relatively large rate-sensitivity parameters (m> 0.1) under specific deformation conditions. Under such conditions, these materials can be deformed to extremely large strains and are called superplastic metals. High Rafe Tesfing. For extremely high rates of testing, it is commonly assumed that deformation occurs under adiabatic (no heat transfer) conditions. Plastic work is mostly (about 90%) converted to heat. The remainder is inelastically stored as changes in defect structure. In high-speed tests, this heat raises the temperature of the material. Consequently, the material praperties are changed. This is another major complication in analyses of high-speed tests. Consequences of testing over a wide spectrum of strain rates are summarized in Fig. 18 (Ref 33).
Hysteresis. If a specimen is loaded past its yield point and then unloaded, or loaded in reverse, subsequent testing on the specimen would result in a different pattem of behavior. Figure 19 shows this effect. The specimen is loaded initially to point A. The solid line represents the behavior of the virgin sample. If instead, the sample were unloaded at point A, the path of unloading is parallel to the initialload path (dotted line). There is sorne permanent deformation (residual strain), and the area is redetermined as Az. When reloaded, the dotted line is retraced and the yield point is now higher due to strain hardening. If this unloading and reloading were done again at point B, the dashed line indicates the behavior. Figure 19 illustrates the effect of stopping and restarting a test. It also points to a consideration when a test sample is machined fram a failed
part. If the testpiece were subjected to deformation prior to the failure, the properties obtained from the test should not be equated to the original material properties (Ref 34). If the prior history of the test specimen includes compression, a hysteresis is present, know as the Bauschinger effect. This is illustrated in Fig. 20. The initial tensile loading is to about 1% strain. The specimen is unloaded and reloaded in compression to 1% strain (measured on the second scale on the x-axis). On unloading and reloading in tension, the shape of the stress-strain curve is significantly different than the original. Again the prior deformation of a test sample will affect its behavior (Ref 34). Figure 21 shows the two types of hysteresis possible in titanium alloys, one with load reversal, and one with load application, rest, and reapplication.
Nature of loading. Figure 22 illustrates a stress-strain loop under controlled constant-strain cycling in a low-cycle fatigue test. During initial loading, the stress-strain curve is O-A-B, with yielding beginning about A. Upon unloading, yielding begins in compression at a lower stress C due to the Bauschinger effect. In reloading in tension, a hysteresis loop develops. The dimensions of this loop are described by its width L'lE (the total strain range) and its height L'l0' (the stress range). The total strain range L'lE consists of an elastic strain component L'lEe = L'lO'/E and a plastic strain component L'lEp. The width of the hysteresis loop depends on the level of cyclic strain. When the level of cyclic strain is small, the hysteresis loop becomes very narrow. For tests conducted under constant L'lE, the stress range L'l0' usually changes with an increasing number of cycles. Annealed material s undergo cyclic strain hardening so that L'l0' increases with the number of cycles and then levels off after about 100 strain cycles. The larger the value of L'lE, the greater the increase in stress range. Materials that are initially cold
Representation of Stress-Strain Behavior / 15
Test data 1 .....
I
t
e
.~
Uí
Rupture I
I"'--¡--
I\L: I
I
I
I
I I
Stress
Isochronous Curves
(a)
Isochronous
Strain
~
(b)
Fig. 25
cyelically induced changes in mechanical behavior. This is illustrated in Fig. 24. Note that 50% may not always be the life fraction where steady-state response is attained. Often it is left to the discretion of the interpreter as to where the steady-state cyelic stress-strain occurS. In any event, the criteria should be noted on the cyelic stress-strain curve for the material being tested (Ref 35). The artiele "Fundamentals of Modem Fatigue Analysis for the Design" in Fatigue and Fracture, Volume 19 of ASM Handbook (Ref 35), provides more details on cyclic behavior of metals and was the basis for this section.
Creep data (a) transferred 1:0 isochronous stress-strain curve (b)
worked undergo cyelic strain softening so that b,cr decreases with increasing number of strain cyeles. Thus, through cyelic hardening and softening, sorne intermediate strength level is attained that represents a steady-state condition (in which case the stress required to enforce the controlled strain does not vary significantly). Monotonic. Sorne metals are cyelically stable, in which case their monotonic stress-strain behavior adequately describes their cyelic response. Cyclic. For other materials the steady-state condition is usually achieved in about 20 to 40% of the total fatigue life in either hardening or softening materials. The cyc1ic behavior of metals is best described in terms of a stress-strain hysteresis loop, as illustrated in Fig. 22. Changes in stress response of a metal occur relatively rapidly during the first several percent of the total reversals to failure. The metal, under controlled-strain amplitude, will eventually attain a steady-state stress response. Now, to conslruct a cyelic stress-strain curve, one simply connects the locus of the points that represent the tips of the stabilized hysteresis loops from c:omparison spe:cimen tests at several controlled-strain amplitudes (see Fig. 23). In the particular example shown in Fig. 23, it was presumed that three companion specimens were tested to failure, at three different controlled-strain amplitudes. Failure of a specimen is defined, typically, as complete separation ilnto two distinct pieces. Generally, the diameter of specirnens are approximately 6 to 10 mm (0.25 to 0.375 in.). In aCltuality, there is a "propagation" period ineluded in this definition of failure. Other definitions of failure appear in ASTM E 60. The steady-state stress response, measured at approximately 50% of the life to failure:, is thereby obtained. These stress values are then plotted at the appropriate strain levels to obtain the cyclic stress-strain curve. One woulld typically test approximately ten or more companion specimens. The cyelic stress-strain curve can be compared directly to the monotonic or tensile stress-strain curve to quantitatively assess
Isochronous curves are ineluded in this Atlas, although they are not simply stress-strain curves. The parameter of time is added to them. Mechanical tests can be performed as short-time static tests or longterm creep deformation tests. Data from the long-term tests are recorded as sets of strain as a function of time for different loads (stresses) for a given temperature. As the stress increases, this time to rupture is less as seen in Fig. 25(a). Collections of these data can be analyzed by holding one of the three variables (time, stress, and strain constant). From Fig. 25(a) (where stress is constant on each curve), values at constant time can be found in effect by constructing a vertical line, perpendicular to the time axis, that intersects the farnily of curves. Values at the intersection points form sets of stresses and strains at constant time that can be plotted on a linear coordinate system at these selected times to make the isochronous curves (Fig. 25b). These farnilies of curves are plotted at a given temperature, since temperature is so significant to the creep behavior of an alloy.
Guide to the Curves in the Atlas As much of the information about the test specimens that is available in the source and that is able to be abstracted in the caption is given with the curves that follow. The prime sources of all curves is given so further details may be gathered. Parameters affecting the stress-strain behavior are: • Composition. The compositions listed are intended as a guide to alloy identification. Nominal compositions have been added for this purpose, so this information is not necessarily from the source of the curve. If a more precise composition is given (listed to tenths or hundredths of a percent) in the source, this has been used. • Heat treatment and conditioning are given in the style cornmon to the alloy group. Temperature conversions are approximate. • Strain Rate ofTest. In sorne cases, the speed of the test head is given, which differs from the strain rateo • Temperature of the test specirnen is sometimes specified as being held for a set time prior to the test. Other times it is given in the source without qualification. At cryogenic temperatures, the stressstrain behavior of pure copper, brasses, bronzes, austenitic stainless steels, and sorne aluminum alloys exhibits a discontinuous yielding, and the curve appears serrated. Such behavior is indicated in the Atlas using a shaded envelope. • Orientation. The orientation of the specimen relative to rolling or extruding direction is illustrated in Fig. 26 (Ref 36). • Specimen size and shape information is provided to the extent found in the source documentation.
Units and Unit Conversions. The units on the left side and bottom of the curve are the units of the source document. The conversion of strain units on the curves is 1 ksi = 7 MPa. This conversion is used so that a cornmon grid can be used. The more precise conversion is 1 ksi
16 / Atlas of Stress-Strain Curves
Short transverse
Lé===-:Y tf+-I'-_'I Long transverse
Long transverse
Sheet and plate
Extruded and drawn tu be Rolled and extruded rod, bar, and thin shapes
Long
Transverse
transverse
Fig. 26
Grain orientation in standard wrought forms of alloys. Source: Ref 36
=6.894757 MPa. The converted stress in MPa can be multiplied by the correction factor of 6.89475717.000000 = 0.98497 to obtain a more precise conversion. Ramberg-Osgood Parameters. The Ramberg-Osgood Method is a method of modeling stress-strain curves. An equation (ideally a simple one) for the stress-strain curve is necessary for finding a quantitative expression for the available energy in fracture studies. The RambergOsgood equation is useful: cr cr n e=-+-
E
F
= Celastic + eplastic
knowledge of the strain-hardening capacity of the material in terms of the Ramberg-Osgood strain-hardening relationship. MIL-HDBK-5, 1998 (Ref 37) presents an explanation of the method and uses the following expression for Eplastic: eplastic =
O.002(cr/crO.2yp)n
(Eq 51)
It further explains how material behavior can be modeled for computer codes using, E, n, and CíO.2YP where the exponential relationship is applicable.
(Eq 49)
where n is (unfortunately) called the strain-hardening exponent and F is called the nonlinear modulus. This is said to be unfortunate because n is already cornmonly called the strain-hardening exponent (Eq 25), where it is, in fact the exponent of the strain. The Ramberg-Osgood parameter, n, is the reciprocal of the other n. The two can usua11y be distinguished by their values. The Ramberg-Osgood parameter, n, usually is between 2 and 40. Equation 49 separates the total strain into a linear and a nonlinear part: E
transverse transverse
(Eq50)
There are other forms of the Ramberg-Osgood equation. The total strain energy in a body (per unit thickness) equals the area under the load-displacement curve. The energy under the linear part of the stress-strain curves is discussed in the section "Resilience" in this artiele. For applications where margins against ductile fracture must be quantified or where components are subjected to large plastic strains, elastic-plastic J-integral methods can be used to predict fracture conditions. Calculation of applied J values for cracked components requires
Terms Terms cornmon to discussion of stress-strain curves, tensile testing, and material behavior under test ineluded here (Ref 1, 2). accuracy. (1) The agreement or correspondence between an experimentally deterrnined value and an accepted reference value for the material undergoing testing. The reference value may be established by an accepted standard (such as those established by ASTM), or in sorne cases the average value obtained by applying the test method to a11 the sampling units in a lot or batch of the material may be used. (2) The extent to which the result of a calculation or the reading of an instrument approaches the true value of the ca1culated or measured quantity. axial strain. Increase (or decrease) in length resulting from a stress acting para11el to the longitudinal axis of the specimen. Bauschinger effect. The phenomenon by which plastic deformation increases yield strength in the direction of plastic flow and decreases it in other directions. breaking stress. See rupture stress. brittleness. A material characteristic in which there is little or no plastic (permanent) deformation prior to fracture.
Representation of Stress-Strain Behavior / 17
chord modulus. The slope of the chord drawn between any two specific points on a stress-strain curve. See also modulus of elasticity. compressive stl'ength. The maximum compressive stress a material is capable of developing. With a brittle material that fails in compression by fracturing, the compressive strength has a definite value. In the case of ductile, malleable, or semiviscous materials (which do not fail in compression by a shattering fracture), the value obtained for compressive strength is an arbitrary value dependent on the degree of distortion that is regarded as effective failure of the material. compressive stress, Se' A stress that causes an elastic body to deform (shorten) in the direction of the applied load. Contrast with tensile stress.
creep. Time-dependent strain occurring under stress. The creep strain occurring at a diminishing rate is called primary or transient creep; that occurring at a minimum and almost constant rate, secondary or steady-rate cn!ep; that occurring at an accelerating rate, tertiary creep. creep test. A method of determining the extension of metals under a given load at a given temperature. The determination usually involves the plotting of time-elongation curves under constant load; a single test may extend over many months. The results are often expressed as Ithe elongation (in millimeters or inches) per hour on a given gage length (e.g., 25 mm, or 1 in.). cyclic loads. Loads that change value over time in a regular repeating pattem. discontinuous yielding. The nonuniform plastic flow of a metal exhibiting a yield point in which plastic deformation is inhomogeneously distributed along the gage length. Dnder sorne circumstances, it may occur in metals not exhibiting a distinct yield point, either at the onset of or during plastic flow. ductility. The ability of a material to deform plastically without fracturing. elastic constants. The factors of proportionality that relate elastic displacement of a material to applied forces. See also modulus of elasticity, shear modulus, and Poisson's ratio. elasticity. The property of a material whereby deformation caused by stress disappears upon the re:moval of the stress. elastic Iimit. The maximum stress that a material is capable of sustaining without lmy permanent strain (deformation) remaining upon complete release of the stress. See also proportionallimit. elongation. (l) A term used in mechanical testing to describe the amount of exlension of a testpiece when stressed. (2) In tensile testing, the increase in the gage length, measured afier fracture of the specimen within the gage length, ef, usually expressed as a percentage of the original gage length. elongation, pereent. The extension of a uniform section of a specimen expressed as percentage of the original gage length: Elongation, % = Lx
¿Lo x 100
where Lo is original gage length and Lx is final gage length. engineering strain, e. A term sometimes used for average linear strain or conventional strain in order to differentiate it from true strain. In tension testing, it is calculated by dividing the change in the gage 1ength by the original gage length. engineering strless, S. A term sometimes used for conventional stress in order to differentiate it from true stress. In tension testing, it is calculated by dividing the load applied to the specimen by the original cross-sectional area of the specimen. failure. Inability of a component or test specimen to fulfill its intended function. fracture strength, Sr. The normal stress at the beginning of fracture, calculated from the load at the beginning of fracture during a tension test and the original cross-sectional area of the specimen. gage length, Lo.. The original length of that portion of the specimen over which strain or change of length is determined.
Hooke's Law. The law of springs, which states that the force required to displace (stretch) a spring is proportional to the displacement. hysteresis (mechanical). The phenomenon of permanently absorbed or lost energy that occurs during any cycle of loading or unloading when a material is subjected to repeated loading. load, P. In the case of mechanical testing, a force applied to a testpiece that is measured in units such as pound-force or newton. Lüders Iines. Elongated surface markings or depressions, often visible with the unaided eye, that form along the length of a tension specimen at an angle of approximately 45° to the loading axis. Caused by localized plastic deformation, they result from discontinuous (inhomogeneous) yielding. Also known as Lüders bands, Hartrnann lines, Piobert lines, or stretcher strains. maximum stress, Smax. The stress having the highest algebraic value in the stress cycle, tensile stress being considered positive and compressive stress negative. The nominal stress is used most commonly. mechanical hysteresis. Energy absorbed in a complete cycle of loading and unloading within the elastic limit and represented by the closed loop of the stress-strain curves for loading and unloading. mechanical properties. The properties of a material that reveal its elastic and inelastic behavior when force is applied or that involve the relationship between the intensity of the applied stress and the strain produced. The properties included under this heading are those that can be recorded by mechanical testing-for example, modulus of elasticity, tensile strength, elongation, hardness, and fatigue limit. mechanical testing. The methods by which the mechanieal properties of a metal are determined. modulus of elasticity,E. The measure of rigidity or stiffness of a metal; the ratio of stress, below the proportionallimit, to the corresponding strain. In terms of the stress-strain diagram, the modulusof elasticity is the slope of the stress-strain curve in the range of linear proportionality of stress to strain. AIso known as Young's modulus. For materials that do not conform to Hooke's law throughout the elastic range, the slope of either the tangent to the stress-strain curve at the origin or at low stress, the secant drawn from the origin to any specified point on the stress-strain curve, or the chord connecting any two specific points on the stress-strain curve is usually taken to be the modulus of elasticity. In these cases, the modulus is referred to as the tangent modulus, secant modulus, or chord modulus, respectively. modulus of resilience, URo The amount of energy stored in a material when loaded to its elastie limito It is determined by measuring the area under the stress-strain curve up to the elastic limit. See also strain energy.
modulus of rigidity. See shear modulus. modulus of rupture. Nominal stress at fracture in a bend test or torsion test. In bending, modulus of rupture is the bending moment at fracture (Me) divided by the section modulus (l): Me
Sb=¡ In torsion, modulus of rupture is the torque at fracture (Tr) divided by the polar section modulus (J): Tr Ss =-T
modulus of toughness, U T • The amount of work per unit volume done on a material to cause failure under static loading. m-value. See strain-rate sensitivity. natural strain. See true strain. necking. Reducing the cross-sectional area of metal in a localized area by stretching. nominal strain. See strain. nominal strength. See ultimate strength. nominal stress. The stress at a point calculated on the net cross section by simple elasticity theory without taking into account the effect on
18 / Atlas of Stress-Strain Curves
the stress produced by stress raisers such as holes, grooves, fillets, and so forth. normal stress. The stress component perpendicular to aplane on which forces act. Normal stress may be either tensile or compressive. n-value. See strain-hardening exponent. offset. The distance along the strain coordinate between the initial portion of a stress-strain curve and a parallel line that intersects the stress-strain curve at a value of stress (commonly 0.2%) that is used as a measure of the yield strength. Used for materials that have no obvious yield point. offset yield strength. The stress at which the strain exceeds by a specified amount (the offset) an extension of the initial proportional portion of the stress-strain curve. Expressed in force per unit area. permanent seto The deformation or strain remaining in a previously stressed body after release of load. plastic instability. The stage of deformation in a tensile test where the plastic flow becomes nonuniform and necking begins. plasticity. The property that enables a material to undergo permanent deformation without rupture. plastic strain. Dimensional change that does not disappear when the initiating stress is removed. U sually accompanied by sorne elastic deformation. Poisson's ratio, V. The absolute value of the ratio of transverse (lateral) strain to the corresponding axial strain resulting from uniformly distributed axial stress below the proportional limit of the material. proof stress. The stress that will cause a specified small permanent set in a material. proportionallimit. The greatest stress a material is capable of developing without a deviation from straight-line proportionality between stress and strain. See also elastic limit and Hooke's law. reduction in area. The difference between the original cross-sectional area of a tensile specimen and the smallest area at or after fracture as specified for the material undergoing testing. secant modulus. The slope of the secant drawn from the origin to any specified point on the stress-strain curve. See also modulus of elasticity. shear mOdulus, G. The ratio of shear stress to the corresponding shear strain for shear stresses below the proportionallimit of the material. Values of shear modulus are usually deterrnined by torsion testing. AIso known as modulus of rigidity. specimen. A test object, often of standard dimensions or configuration, that is used for destructive or nondestructive testing. One or more specimens may be cut from each unit of a sample. strain. The unit of change in the size or shape of a body due to force. AIso known as nominal strain. See also engineering strain, linear strain, and true strain. strain energy. A measure of the energy absorption characteristics of a material determined by measuring the area under the stress-strain diagram. strain hardening. An increase in hardness and strength caused by plastic deformation at temperatures below the recrystallization range. AIso known as work hardening. strain-hardening coefficient, K. See strain-hardening exponent. strain-hardening exponent, n. The value n in the relationship a = KE n , where a is the true stress, E is the true strain, and K, which is called the "strength coefficient," is equal to the true stress at a true strain of 1.0. The strain-hardening exponent, also called "n-value," is equal to the slope of the true-stress/true-strain curve up to maximum load, when plotted on log-log coordinates. The n-value relates to the ability of a material to be stretched in metalworking operations. The higher the n-value, the better the formability (stretchability). strain rate, t.The time rate of straining for the usual tensile test. Strain as measured directly on the specimen gage length is used for determining strain rateo Because strain is dimensionless, the units of strain rate are reciprocal time.
strain-rate sensitivity (m-value). The increase in stress (a) needed to cause a certain increase in plastic strain rate (E) at a given level of plastic strain (E) and a given temperature (T). Lllog a ) m = ( Lllog É eT
strength. The maximum nominal stress a material can sustain. Always qualified by the type of stress (tensile, compressive, or shear). strength coefficient. See strain-hardening exponent. stress. The intensity of the internally distributed forces or components of forces that resist a change in the volume or shape of a material that is or has been subjected to external forces. Stress is expressed in force per unit area and is ca1culated on the basis of the original dimensions of the cross section of the specimen. Stress can be either direct (tension or compression) or shear. See also engineering stress, nominal stress, normal stress, and true stress. stress-strain curve. A graph in which corresponding values of stress and strain are plotted. Values of stress are usually plotted vertically (ordinates or y-axis) and values of strain horizontally (abscissas or xaxis). AIso known as deformation curve and stress-strain diagram. tangent modulus, E T • The slope of the stress-strain curve at any specified point of the stress-strain curve. See also modulus of elasticity. tensile strength, Su. In tensile testing, the ratio of maximum load to original cross-sectional area. AIso known as ultimate strength. Compare with yield strength. tensile stress, S, a. A stress that causes two parts of an elastic body, on either side of a typical stress plane, to pull aparto Contrast with compressive stress. tensile testing. See tension testing. tension. The force or load that produces elongation. tension testing. A method of deterrnining the behavior of materials subjected to uniaxialloading, which tends to stretch the metal. A longitudinal specimen of known length and diameter is gripped at both ends and stretched at a slow, controlled rate until rupture occurs. AIso known as tensile testing. transverse. Literally, "across," usually signifying a direction or plane perpendicular to the direction of working. In rolled plate or sheet, the direction across the width is often called long transverse, and the direction through the thickness, short transverse. transverse strain. Linear strain in a plane perpendicular to the axis of the specimen. true strain, E. (1) The ratio ofthe change in dimension, resulting from a given load increment, to the magnitude of the dimension immediately prior to applying the load increment. (2) In a body subjected to axial force, the naturallogarithm of the ratio of the gage length at the moment of observation to the original gage length. AIso known as natural strain. true stress, a. The value obtained by dividing the load applied to a member at a given instant by the cross-sectional area over which it acts. ultimate strength, Su. The maximum stress (tensile, compressive, or shear) a material can sustain without fracture, deterrnined by dividing maximum load by the original cross-sectional area of the specimeno AIso known as nominal strength or maximum strength. uniform strain. The strain occurrlng prior to the beginning of localization of strain (necking); the strain to maximum load in the tension test. work hardening. See strain hardening. von Mises criterion. The maximum distortion energy criterion that yielding will occur when the von Mises effective stress equals or exceeds the yield stress. a~ ayp
Representation of Stress-Strain Behavior / 19
von Mises effedive stress and strain. The effective stress (a) and effective stralln (8) are given by:
and
-
d €
v'2 = -3-
[(del - d€l)2
+ (d€2 - d€¡)2 + (d€3 - d€¡)2]l/2
where 1,2, and 3 indicate the principal axes. yielding. Evidence of plastic deformation in structural materials. Also known as plastic flow or creep. yield point. The first stress in a material, usually les s than the maximum attainable stress, at which an increase in strain occurs without an increase in stress. Only certain metals-those that exhibit a localized, heterogeneous type of transition from elastic to plastic deformation-produce a yield point. If there is a decrease in stress after yielding, a distinction may be made between upper and lower yield points. The load at which a sudden drop in the flow curve occurs is called the upper yield point The constant load shown on the flow curve is the lower yield point. yield-point elolllgation. The amount of strain that is required to complete the yielding process. It is measured from the onset of yielding to the beginning of strain hardening. yield strength, YS or Sy. The stress at which a material exhibits a specified deviation from proportionality of stress and strain. An offset of 0.2% is used for many metals. Compare with tensile strength. yield stress. The stress level of highly ductile materials, such as structural steels, all which large strains take place without further increase in stress. Young's modulus, E. See modulus of elasticity.
ACKNOWlEDGMENT Portions of this artiele are adapted from G.E. Dieter, "Mechanical Behavior under Tensile and Compressive Loads," Mechanical Testing and Evaluation, Volume 8, ASM Handbook, 2000, p 99-108.
REFERENCES 1. Glossary of Terms, Mechanical Testing and Evaluation, Vol 8, ASM Handbook, ASM International, 2000, p 939-952 2. ASM Materials Engineering Dictionary, ASM International, 1992 3. DJ. Mack, Trans. AIME, Vol 166, 1946 p 68-85 4. P.E. Armstrong, Measurement of Elastic Constants, Techniques of Metals Research, Vol V, RE Brunshaw Ed., Interscience, 1971 5. G. Carter, PrincipIes of Physical and Chemical Metallurgy, American Society for Metals, 1979, p 87 6. H. Davis, G. Troxell, and G. Hauck, The Testing ofEngineering Materials, 4th (~d., McGraw-Hill, 1982, p 33 7. H. Davis, G. Troxell, and G. Hauck, The Testing ofEngineering Materials, 4th ed., McGraw-Hill, 1982, p 314 8. "Copper and Copper Alloys-Rod for General Purposes," EN 12163, CEN, 1998 9. "Designation Systems for Steel-Part l:Steel Names, Principal Symbols," EN-l0027-1, CEN, 1992, P 4 10. G.E. Dieter, Introduction to Ductility, Ductility, American Society for Metals, 1968 11. AC. Ugnral and S.K. Fenster, Advanced Strength and Applied Elasticity, 3rd eel., Prentice Hall, 1995 12. J.R Low and E Garofalo, Proc. Soco Exp. Stress Anal., Vol 4 (No. 2), 1947, P 16--25 13. J.R Low, Properties of Metals in Materials Engineering, American Society for Metals, 1949
14. J. Datsko, Material Properties and Manufacturing Processes, John Wiley & Sons, 1966, p 18-20 15. w.B. Morrison, Trans. ASM, Vol 59, 1966, p 824 16. D.C. Ludwigson, Metall. Trans., Vol 2, 1971, p 2825-2828 17. HJ. Kleemola and M.A Nieminen, Metall. Trans., Vol 5, 1974, P 1863-1866 18. C. Adams and J.G. Beese, Trans. ASME, Series H, Vol 96, 1974, P 123-126 19. AConsidére, Ann. Ponts Chaussées, Vol 9, 1885, p 574-775 20. G.w. Geil and N.L. Carwile, J. Res. Natl. Bur. Stand., Vol 45, 1950, p 129 21. P.w. Bridgman, Trans. ASM, Vol 32, 1944, P 553 22. J. Aronofsky, 1. Appl. Mech., Vol 18, 1951, p 75-84 23. T.A Trozera, Trans. ASM, Vol 56, 1963, p 280-282 24. E.R. Marshall and M.C. Shaw, Trans. ASM, Vol 44, 1952, P 716 25. WJ.McG. Tegart, Elements of Mechanical Metallurgy, Macmillan, 1966, p 22 26. G.E. Dieter, Mechanical Behavior under Tensile and Compressive Loads, Mechanical Testing and Evaluation, Vol 8, ASM Handbook, 2000, p 99-108 27. "Standard Methods of Compression Testing of Metallic Materials at Room Temperature," E 9, Annual Book ofASTM Standards, ASTM 28. G. Sines, T. Okada, and S. Mack, Fixture for Accurate Load Path in Axial Compression, Compression Testing of Homogeneous Materials and Composites, R Chait and R Papirno, Ed., STP 808, ASTM, 1983, P 97-108 29. P. Dadras and J.E Thomas, Deformation Inhomogeneities in Upset Forging, Compression Testing of Homogeneous Materials and Composites, R Chait and R Papirno, Ed., STP 808, ASTM, 1983, P 24-39 30. M.L. Lovato and M.G. Stout, Metall. Trans. A, Vol 23, 1992, P 935-951 31. "Tension Testing of Metallic Materials," E 8, Annual Book ofASTM Standards, Vol 03.01, 1996 32. A.K. Sachdev and J.E. Hunter, Jr., Thermal Effects During Uniaxial Straining of Steels, Metall. Trans. A, Vol 13, 1982, P 1063-1067 33. S. Nemat-Nasser, Introduction to High Strain Rate Testing, Mechanical Testing and Evaluation, Vol 8, ASM Handbook, 2000, p 427 34. J.M. Holt, Uniaxial Tension Testing, Mechanical Testing and Evaluation, Vol 8, ASM Handbook, 2000, p 124-142 35. M.R. Mitchell, -Fundamentals of Modern Fatigne Analysis for the Design, Fatigue and Fracture, Vol 19, ASM Handbook, 1996, p 227-249 36. G.H. Koch, Tests for Stress-Corrosion Cracking. Adv. Mater. Process., Aug 2001, p 36 37. Metallic Materials and Elements for Aerospace Vehicle Structures, MIL-HDBK-5H, Department of Defense and Federal Airline Administration, 1998
SElECTED REFERENCES • "Standard Terrninology Relating to Methods of Mechanical Testing," E 6, Annual Book of ASTM Standards, Vol 03.01 • "Tensile Testing of Metallic Materials," E 8, Annual Book of ASTM Standards, Vol 03.01 • "Elevated Temperature Tension Tests of Metallic Materials" E 21 Annual Book of ASTM Standards, Vol 03.01 " • "Young's Modulus, Tangent Modulus, and Chord Modulus," E 111, Annual Book of ASTM Standards, Vol 03.01 • "Tensile Testing of Metallic Materials," EN 10002: 1 • "Metallic Materials-Tensile Testing at Elevated Temperature," ISO 783 • "Metallic Materials-Tensile Testing at Ambient Temperature," ISO 6892 • "Metallic Materials-Tensile Testing at Low Temperature," ISO 15579
1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1
Ferrous Metals
Cast Iron (CI)/23
Cast Iron (el) 420~-------.-------r-------'-------'-------,
CI.OOl Unclassified cast irons, influence of graphite
60
morphology on stress-strain curves Source: D.M. Stefanescu, Classification and Basic Metallurgy of Cast Iron, Properties and Selection: lrons, Steels, and High-Performance Alloys, Vol 1, ASM Handbook, 1990, p 8
350~-----~-------4--~~-+------~----~ 50
al
280
40
a.
.¡¡; -'"
'"
'"
::¡; rñ
~
rñ
210
30
~
~ .¡¡; c:
~ .¡¡; c:
~
~
140
20
70~~~~+-------~-------+------~~------4
10
~_------OL.1-------0~.2-------0~.3-------0~.4------~0.~ Strain, %
350
Yield point
250
::¡;
/
200
/
¡:f ~
Cií 150
100
50
~
2
Caststeel
/ ",/
1/ /V
I/ V
stress-strain curves
-
I
300
&.
CI.002 Unclassified cast steel and cast iron, tensile
/
3
~
Test direction: longitudinal. Cast stee1: shows definite yie1d point; stee1 test bar diameter = 12.83 mm (0.505 in.); u1timate strength = 543 MPa. Cast iron: 25.4 mm (1 in.) cast bar, iron test bar diameter = 12.83 mm (0.0505 in.); u1timate strength = 315 MPa. Gage 1ength = 51 mm (2 in.)
[::7
Source: O.NJ. Oilbert, Factors Relating to lhe Stress/Strain Properties of Cast Iron, BClRA J., Vol 6 (No. 6), April 1957, P 551
~tiron
4
Strain, 0.001 in.lin.
5
6
7
24/Cast Iron (CI)
CI.003 lron alloy casting, tensile stress-strain curves with effect of graphite
300r---,---,----r---,---,r---,---~--_r--_,
Test direction: longitudinal. In curves 1 through 5, the curvature increases as the amount of graphite in the iron increases. Curve 6 had graphite similar in quantity to curve 2, but it is coarser. Modulus of elasticity: curve 1, 145 GPa (21.1 psi x 106); curve 2, 116 GPa (16.9 psi x 106); curve 3, 123 GPa (17.9 psi x 106 ); curve 4, 103 GPa (14.9 psi x 106); curve 5,84 GPa (12.2 psi x 106); curve 6, 115 GPa (16.7 psi x 106) Source: O.NJ. Oilbert, Factors Relating to the Stress/Strmn Properties of Cast Iron, Be/RA J., Vol 6 (No. 6), ApriJ, 1957, p 553
0.1
0.2
0.3
0.4
0.5
0.6
0.7
0.8
0.9
Strain, %
80
/'
-,/
50
PL
j¡
10
r
I/
~r--- V PL
./
~/V
lil
0.2
irol
~s!eel
~
1/i.~
30
20
V
I/YS
60
~uctile
------Pearlitic
70
CI.004 Unclassified cast irons and steels, stress-strain curves
490
Behavior of several irons compared to steel. 0.2% yield strength: pearlitic ductile iron, 455 MPa (66 ksi); steel, 372 MPa (54 ksi); ferritic ductile iron, 276 MPa (40 ksi); gray iron, 220 MPa (32 ksi). PL, proportionality limits
420
V
Source: Prívate communication with Lyle Jenkins
Ferritic drti,e iron
---
560
350
&.
::::;
280 ui
'"~
_ _¿ray r--'" iron
é'ií 210
YS
140
70
0.4
0.6
0.8
Strain, %
1.0
1.2
o
1.4
Cast Iron (C1)125
3
50 I
40
V //v
/
I
I
10
~
I I
20
CI.005 Pearlitic and ferritic compacted graphite iron casting, typical tensile stress-strain curves
420
60
IT
/ 1/
/
------
~
---
2
Curve 1: as-cast pearlitic; ultimate tensile strength = 410 MPa (59.5 ksi); elongation = 1.0%. Curve 2: ferritic; ultimate tensile strength = 320 MPa (46.4 ksi); elongation = 3.5%. Dashed curve (3) indicates modulus of elasticity, 144 GPa (20.9 x 106 psi).
350
280
8:.
::a: 210
Source: C.E Walton, Ed., [ron Castings Handbook, Iron Casting Society, 1981, p 382
(/)
~ 140
70
0.1
0.2
0.3
0.5
0.4
0.6
o
0.7
Strain, %
60
/ V 1//V
50
40
If
l.
/
LJ::!% V-
-
Tenslon !-- ~t-r-
350
0.1 %,0.2%, and 0.5% yield strengths are indicated. Proportionality limits (PL) are 201 MPa (29.1 ksi) in compression and 124 MPa (18 ksi) in tension.
280
Source: G.E Seargeant and E.R. Evans, The Production and Properties of Compacted Graphite Irons, British Foundryman, May 1978. As published in C.E Walton, Ed., [ron Castings Handbook, Iron Casting Society, 1981, P 388
8:.
::a: 210
PL
140
PL
70
Ir
0.1
CI.006 4.35 carbon equivalent compacted graphite iron casting, tensile and compressive stress-strain curves
compreSSion+-
V
IV
20
10
o~
420
0.2
0.3
0.4
0.5
Strain, %
0.6
0.7
0.8
o
0.9
~
26/Cast lron (CI)
1600
CI.007 Austempered ductile iron casting, stressstrain curves showing effect of matrix structure
1400
Solid eurve for austempered ductile iron, 300 oC, 1 h, with lower bainitie matrix structures. Dashed curve for austempered ductile iron, 375 oC, 1 h, with upper bainitic matrix structures
1200
1000
'"
/
I
I
Il.
:2
en IJ)
800
/
~--
/"
-
--- - -
---
Source: P.A Blackmore and R.A. Harding, "The Effects of Metallurgical Process Variables on tbe Properties of ADI's," P 117-134; J. Heat Treat., Vol 3 (No. 4), P 320-325. As published in Structural Alloys Handbook, Vol 1, CINDASlPurdue University, 1994, p 25
~
(f)
600
400
200
O O
2
4
10
8
6 Strain, %
600
/~
550 500 /
450
and cyclic stress-strain curves
l:f'" ji ..
Casting size = 25 x 45 mm. Austempered ductile iron (ADI), BCIRA Interim Grade 1200/1, high strength. Austempered 310 oC, 3 h. Monotonic curve (solid line): strength coefficient, K = 26,425.7; strain-hardening exponent, n = 0.45. CycIic curve (dotted line): strength coefficient, K' = 11,389.7; strain-hardening exponent, n' = 0.37. Elastie line (dashed): slope (modulus of elasticity) = 173.6 GPa (25.18 x 106 psi). Composition: Fe-3.59C-2.15Si-0.29Mn-0.012S-0.010P-0.056Mg0.80Ni-O.03Cr-0.027Sn-0.09Mo
'
/
Il.
:2 ai 350 "O
:o
~ 300 E
g¡'" 250 ~
200
/
150
/
/
V
/
Source: M.J.D. Frier, "Strain Life Data and Stress/Strain Data for Austempered Ductile Irons-Tests of the High-Strengtb Grade," Report 1820, British Cast Iron Research Association (BClRA), 1991, P 3
/
100 50
CI.008 Austempered ductile iron casting, monotonic
....
~
/lT
'" 400
ro
12
/
00
- - Monotonic ........... Cyclic
- -1 - Elasti1c
/ 0.05
0.10
0.15
0.20
0.25
Strain amplitude, %
0.30
0.35
0.40
Cast Iron (CI)/27
600 550 500 450
/j
'" 400
a.
::!: al 350
//
"O
~ 300
/
E
'g¡"
250
(f)
200
CI.009 Austempered ductile cast iron bar, monotonic and cyclic stress-strain curves
/)1'
/V /7 v
Bar diameter = 22 mm. Austempered ductile iron (ADI), BCIRA Interim Grade 1200/1, high strength. Austempered 325 oC, 3 h. Monotonic curve (solid line): strength coefficient, K = 22,486; strain-hardening exponent, n = 0.42. Cyclic curve (dotted line): strength coefficient, K' = 18,588.7; strain-hardening exponent, n' = 0.40. Elastíc line (dashed): slope (modulus of elasticity) = 173.2 GPa. Composition: Fe-3.65C-2.16Si0.47Mn-0.0 15S-0.0 1OP-0.056Mg -O .58Ni-0.02Cr0.027Sn-0.07Cu
~/
/
~
Source: l.S. Matharu, M.J.D. Frier, and K. Shelby, "Strain-Life Fatigue Data and Stress/Strain Data for Austempered Ductile Irons," Report 1813, British Cast Iron Research Association (BCIRA), 1990, P 226
J/ 150
/
100 50
/
oO
- - Monotonic .•.•....... Cyclic
- - ¡- Elasti1c
/ 0.05
0.10
0.15
0.20
0.25
0.30
0.35
0.40
0.45
Strain amplitude, %
600
/' /
550
//
500
/
::!: al 350
/
"O
.a
'8. 300
I
E
en
200
~
I
150
V
Source: l.S. Matharu, M.J.D. Frier, and K. Shelby, "Strain-Life Fatigue Data and Stress/Strain Data for Austempered Ductile Irons," Report 1813, British Cast Iron Research Association (BCIRA), 1990, P 226
/
/
100 50
Casting size = 25 x 45 mm. Austempered ductíle iron (ADI), BCIRA Interim Grade 950/6, high strength. Austempered 375 oC, 2.5 h. Monotonic curve (solid line): strength coefficient, K =6049.1; strain-hardening exponent, n = 0.28. Cyclic curve (dotted line): strength coefficient, K' = 5190.4; strain-hardening exponent, n' = 0.27. Elastíc line (dashed): slope (modulus of elasticity) = 174.6 GPa. Composition: Fe-3.67C-2.08Si-0.30Mn0.014S-0.014P-0.057Mg-0.77Ni-0.03Cr-0.028Sn-0.08Cu
/V
'" 400
a.
250
V
//
450
'g¡"
CI.Ol0 Austempered ductile iron casting, monotonic and cyclic stress-strain curves
V
oO
- - Monotonic ........... Cyclic
/ 0.05
- - - Elastic
0.10
0.15
0.20
0.25
I
T
0.30
0.35
Strain amplitude, %
0.40
0.45
28/Cast Iron (CI)
CI.Oll Austempered ductile cast iron bar, monotonic and cyclic stress-strain curves
700
,. ~....
600
Bar diameter = 22 mm. Austempered ductile iron (ADI), BCIRA Interim Grade 950/6, high strength. Austempered 375 oC, 1.25 h. Monotonic curve (solid line): strength coefficient, K =28,769.7; strain-hardening exponent, n = 0046. Cyc1ic curve (dotted line): strength coefficient, K' = 12,075.7; strain-hardening exponent, n' = 0.37. Elastic line (dashed): slope (modulus of elasticity) = 173.9 GPa. Composition: Fe-3.73C-2.21Si-0047Mn-0.020S-0.011P0.059Mg-0.55Ni-0.03Cr-0.027Sn-0.08Cu
~
,." ......... 500 ro
o..
:2: ai 400
,.j
"O
:::l :t::
Ci
E
~ 300
'"~
Cñ
200
100
f/' ,.
V
00
/
0.05
/
/
v
/
.'
.'
V
Source: LS. Matharu and M.J.D. Frier, "Strain-Life Fatigue Data and Stress/Strain Data for Austempered Ductile Irons-A Preliminary Report," Report 1795, British Cast Iron Research Association (BCIRA), 1990, P 53 - - Monotonic ........... Cyclic
-10.10
E1aSr
0.15 0.20 0.25 Strain amplitude, %
0.30
0.35
0.40
CI.012 Austempered ductile cast iron bar,
700
monotonic and cyclic stress-strain curves 600
500
V
ro
o..
,.}
:2: ai 400 "O
=ªCi E
~ 300
j
200
100
,. . ~
Bar diameter = 22 mm. Austempered ductile iron (ADl), BClRA Interim Grade 950/6, high strength. Austempered 350 oC, 1 h. Monotonic curve (solid line): strength coefficient, K = 11,647.1; strain-hardening exponent, n = 0.36. Cyc1ic curve (dotted line): strength coefficient, K' = 8887.6; strain-hardening exponent, n' =0.33. Elastic line (dashed): slope (modulus of elasticity) = 174.1 GPa. Composition: Fe-3.68C-2.22Si-0040Mn-0.020S-0.012P0.056Mg-0.54Ni-0.02Cr-0.027Sn-0.07Cu
¿.:.., .....
V
oO
/
0.05
V
/
/
/
/'
Source: LS. Matharu and M.J.D. Frier, "Strain-Life Fatigue Data and Stress/Strain Data for Austempered Ductile Irons-A Preliminary Report," Report 1795, British Cast Iron Research Association (BCIRA), 1990, P 53 - - Monotonic ........... Cyclic
-1-
0.10
0.15 0.20 0.25 Strain amplitude, %
Elastr
0.30
0.35
0040
Cast Iron (CI)/29
CI.013 3.60-3.90% carbon ductile casting, tensile
875
125
stress-strain curves Modulus of elasticity varíes from the maximum 150 GPa (21.7 X 106 psi) (curve 1) to the mínimum 159 GPa (23.0 x 106 psi) (curve 3), with an average of 157 GPa (22.7 x 106 psi) (curve 2), based on 40 tests
700
100 230v 1 .¡¡;
';
525
75
Source: Nodular Iron, Properties and Selection of Metals, Vol 1, 8th ed., Metals Handbook, American Society for Metals, 1961, p 386 tU
n.
-'"
::2:
''""
''""
~
Ci5
350
50
~
25~---,~--~~---~----~-----+-----+-----i175
~----L---~2L---~3----~4----~5----~6----~70
Strain, 0.001 in.lin.
60 55 50
315
/
I
280
/ / VL/ 7 p /
2
tU
n.
245 ::2:
'"
'" 210 ~
I
'"
PL
I I
15 10 5
175 .~
140
í
105
/
I
I
~
~
A
20
70
/
35
/ 0.1
Curve 1: as-cast pearlitic, ultimate tensile strength = 745 MPa (108 ksi). Curve 2: annealed ferritic, ultimate tensile strength = 400 MPa (58 ksi). Curve 3 (dashed): 0.2% offset yield strength. PL, limíts of proportionality
350
3
i/
40
typical tensile stress-strain curves 385
/'" íi
/
45
CI.014 Pearlitic and ferritic ductile iron casting,
420
)---
0.2
0.3
0.4 0.5 S!rain, %
0.6
0.7
0.8
o
0.9
Source: O.N.J. Oilbert, Behavior of Cast Irons under Stress, Engineering Properties and Performance of Modem ¡ron Castings, British Cast Iron Research Association (BCIRA), 1970, P 41. As published in C.F. Walton, Ed., ¡ron Castings Handbook, Iron Casting Society, 1981, p 335
30/Cast Iron (CI)
450 400 350
2A/
300
i
~
'"
250
~r
c: ~
150
50
4
/// V-
200
100
.--------
31 ji
ro O::i: ui
~
~~
1I
CI.015 Ductile iron alloy casting, tensile stress-strain curves Test direction: longitudinaL Iron test specimen: 28.65 mm diam x 76.2 mm gage length (1.128 in. diam x 3 in. gage length). Steel test specimen: 37.922 mm diam x 76.2 mm gage length (1,493 in. diam x 3 in. gage length). Curve 1: as-cast pearlitic nodular iron; 0.1 % proof stress = 349 MPa. Curve 2: high-silicon nodular iron failed in elastic region at X. Curve 3: En 4 steel; yield strength = 316 MPa. Curve 4: annealed ferritic nodular iron; 0.1 % proof stress = 232 MPa. Composition: Curves 1 and 4, Fe-3.66C-1.8Si-0,41Mn-0.012S-0.025P0.76Ni-(1 = O.064Mg, 4 = 0.063Mg); curve 2, Fe-2.62C6. 14Si-0.35Mn-0.014S-0.021P-0.78Ni-0.051Mg-0.006Ce; curve 3, Fe-0.23C-0.56Mn-0.044S-0.027P Source: G.N.J. Gilbert, The Stress/Strain Properties of Nodular Cast Irons in Tension and Compression, BC/RA J., Vol 12 (No. 2), March 1964, p 179
f
I
0.1
0.2
OA
0.3
0.5
0.6
0.7
0.8
Strain, %
750 675
/
600
ro ::i:
525
O-
ui
~
450
/
1ií ~
375
Q)
o.E 8
300
/
-----
~
}~
225
--
Test direction: longitudinal. Iron test specimen: 28.65 mm diam x 76.2 mm gage length (1.128 in. diam x 3 in. gage length). Steel test specimen: 37.922 mm diam x 76.2 mm gage length (1.493 in. diam x 3 in. gage length). Curve 1: as-cast pearlitic nodular iron; 0.1 % proof stress = 398 MPa. Curve 2: high-silicon nodular iron, 0.1 % proof stress =676 MPa. Curve 3: En 4 steel; yield strength = 283 MPa. Curve 4: annealed ferritic nodular iron; 0.1 % proof stress = 264 MPa. Composition: Curves 1 and 4, Fe-3.66C-1.8Si-0,41Mn-0.012S-0.025P0.76Ni-(1 = 0.064Mg, 4 = 0.063Mg); curve 2, Fe-2.62C6. 14Si-0.35Mn-0.0 14S-0.021P-0.78Ni-0.051Mg-0.006Ce; curve 3, Fe-0.23C-0.56Mn-0.044S-0.027P
---
4
h/
150
75
V
} V--
.~
~
V
CI.016 Ductile iron casting, compressive stress-strain curves
1-
I
Source: G.NJ. Gilbert, The Stress/Strain Properties of Nodular Cast Irons in Tension and Compression, BC/RA J., Vol 12 (No. 2), March 1964,p 185
//
0.1
0.2
0.3
OA Strain, %
0.5
0.6
0.7
0.8
Cast Iron (CI)/31
----
50
/
40
) 20
10
/
I
V
/
350
¡.---
280
&.
:2
210 ui
V
/
'" ~
1/
1.0
1.5
2.0 2.5 3.0 Strain, 0.001 in.lin.
3.5
4.0
4.5
o
5.0
50
40
-"
:i ~
30
10
CI.018 Pearlitic ductile iron bar, uniaxial tensile stress-strain curve
490
60
20
Source: K.E. Metzloff, H.W. Kwon, L.Y. Fang, and C.R. Loper, Jr., Service Modulus: A Method for Accurate Determination ofYoung's Modulus and Yield Strength in Ductile Iron, AFS Trans., Vol 104, 1996, P 723
140
70
ro
Bar diameter = 12.827 mm (0.505 in.). Samples primarily ferritic with 5-10% pearlite. Test bars machined to ASTM A 536, Fig 6. Test was stress controlled at 345 MPalmin (50 ksi/min). Typical yield strength = 324 MPa (47 ksi); ultimate strength = 496 MPa (72 ksi); elongation = 16%. Composition: Fe-3.599C-2.753Si0.193Mn-0.033P-0.014S
70
0.5
'iij
CI.017 Ferritic ductile iron bar, uniaxial tensile stress-strain curve
420
60
/
/
/ J
V
/
/
/
V
-
0.5
420
350
280
ui
210
140
70
1.0
1.5
&. :2
1/
V
-
2.0 2.5 3.0 Strain, 0.001 in.lin.
3.5
4.0
4.5
o
5.0
'" ~
Bar diameter = 12.827 mm (0.505 in.). Samples primarily pearlitic with 90-95% pearlite. Test bars machined to ASTM A 536, Fig 6. Test was stress controlled at 345 MPalmin (50 ksi/min). Typical yield strength = 400 MPa (58 ksi); ultimate strength = 738 MPa (107 ksi); elongation = 7.5%. Composition: Fe-3.684C-2.422Si0.469Mn-0.028P-0.015S-0.349Cu Source: K.E. Metzloff, H.W. Kwon, L.Y. Fang, and C.R. Loper, Jr., Service Modulus: A Method for Accurate Detennination ofYoung's Modulus and Yield Strength in Ductile Iron, AFS Trans., Vol 104, 1996, P 723
32/Cast Iron (CI)
70
490
60
420
50
_/
'00 40
VV
-'"
ui UJ
// I
!!!
éñ 30
20
10
---
~
-
350
280
210
~ éñ
140
V' V 1/ / /
1.0
&
::;;:
ui
r¡ ~ JI
0.5
CI.019 Ferritic ductile iron bar, uniaxial tensile stress-strain curves Bar diameter = 12.827 mm (0.505 in.). Samples primarily ferritic with 5-10% pearlite. Test bars machined to ASTM A 536, Fig 6. Test was stress controlled at 345 MPalrnin (50 ksilrnin). Typical yield strength (YS) = 324 MPa (47 ksi); ultimate strength = 496 MPa (72 ksi); elongation = 16%. Sample loaded to 70% YS, unloaded to 91 kg (200 lb), loaded to 85% YS, unloaded to 91 kg (200 lb), loaded to failure. Composition: Fe-3.599C2.753Si-0.193Mn-0.033P-0.0 14S Source: K.E. Metzloff, H.W. Kwon, LY. Fang, and CoK Loper, Jr., Service Modulus: A Method for Accurate Determination ofYoung's Modulus and Yield Strength in Ductile Iron, AFS Trans., Vol 104, 1996, P 724
70
1.5
2.0
2.5
3.0
3.5
4.0
4.5
o
5.0
Strain, 0.001 in.lin.
60
I v: 1
50
d
'00 40 -'"
ui
}¡
~
en 30
/
20
10
CI.020 Pearlitic ductile iron bar, uniaxial tensile stress-strain curves
490
70
/
VI
./
/
V
--
~
V
0.5
280
&
210
éñ
70
If
1.0
350
140
Ij /
/¡ I
420
1.5
2.0
2.5 3.0 Strain, 0.001 in.lin.
3.5
4.0
4.5
o
5.0
::;;:
f
Bar diameter = 12.827 mm (0.505 in.). Samples primarily pearlitic with 90-95% pearlite. Test bars machined to ASTM A 536, Fig 6. Test was stress controlled at 345 MPalrnin (50 ksilrnin). Typical yield strength = 400 MPa (58 ksi); ultimate strength = 738 MPa (107 ksi); elongation = 7.5%. Sample loaded to 70% YS, unloaded to 91 kg (200 lb), loaded to 85% YS, unloaded to 91 kg (200 lb), loaded to failure. Composition: Fe-3.684C2.422Si-0.469Mn-0.028P-0.015S-0.349Cu Source: K.E. Metzloff, H.W Kwon, LY. Fang, and CoK Loper, Jr., Service Modulus: A Method for Accurate Determination ofYoung's Modulus and Yield Strength in Ductile Iron, AFS Trans., Vol 104, 1996, P 725
east Iron (el)/33
70
490
60
420
50
g¡
/
40
/"
,.,-
-
~
J
~~
gf ~
rn 30
!
"1
20
¡
JI 2
3
4
5
6
7 8 9 10 Strain, 0.001 in.lin.
I
11
,.,- V
/
50
V
V
30
20
10
---.. V
,'l
/1/ 1//
/J
IV
1/ oO
2
3
4
5
6
f
7 8 9 10 Strain, 0.001 in.lin.
11
Source: K.E. Metzloff, H.W. Kwon, L.Y. Fang, and C.R. Loper, Jr., Service Modulus: A Method for Accurate Detennination ofYoung's Modulus and Yield Strength in Ductile Iron, AFS Trans., Vol 104, 1996, p 726
o
/r/ 1//
l
I
12 13 14 15
-- --- III
(
~
:::¡;
Bar diameter = 12.827 mm (0.505 in.). Samples primarily ferritic with 5-10% pearlite. Test bars machined to ASTM A 536, Fig 6. Test was stress controlled at 345 MPalmin (50 ksilmin). Typical yield strength = 324 MPa (47 ksi); ultimate strength = 496 MPa (72 ksi); elongation = 16%. Sample loaded to 80% YS, unloaded to 91 kg (200 lb), loaded to 1% strain, unloaded to 91 kg (200 lb), loaded to failure. Composition: Fe-3.599C2. 753Si-0.193Mn-0.033P-0.0 14S
70
¡..-
60
280
140
80
70
350
210
!.
Iv
10
-
CI.021 Ferritic ductile iron bar, uniaxial tensile stress-strain curves
560
CI.022 Pearlitic ductile bar, uniaxial tensile stressstrain curves
490
Bar diameter = 12.827 mm (0.505 in.). Samples primarily pearlitic with 90-95% pearlite. Test bars machined to ASTM A 536, Fig 6. Test was stress controlled at 345 MPalmin (50 ksilmin). Typical yield strength = 400 MPa (58 ksi); ultimate strength = 738 MPa (107 ksi); elongation = 7.5%. Sample loaded to 80% YS, unloaded to 91 kg (200 lb), loaded to 1% strain, unloaded to 91 kg (200 lb), loaded to failure. Composition: Fe-3.684C2.422Si-0.469Mn-0.028P-0.015S-0.349Cu
420
350
~
:::¡;
280
'" ~
210
140
70
0 12 13 14 15
Source: K.E. Metzloff, H.W. Kwon, L.Y. Fang, and C.R. Loper, Jr., Service Modulus: A Method for Accurate Detennination ofYoung's Modulus and Yield Strength in Ductile lron, AFS Trans., Vol 104, 1996, p 726
34/Cast Iron (CI)
70
60
50
/1 )1 /
.¡¡; 40
'"
~
éií 30
IV) 20
10
l'
~
V
. . .V
--
-
VI1(1
1.0
350
140
70
1.5
2.0
2.5 3.0 3.5 4.0 Slrain, 0.001 in.fin.
4.5
5.0
5.5
50
V
.¡¡; 40
v
~
V
30
/
0.5
,lAIj
/
1.0
1.5
r¡
v
A
~V
CI.024 Pearlitic ductile iron bar, uniaxial tensile stress-strain curves
2.0
lA
350
rñ
rn
210
Ij
140
~ r¡
2.5 3.0 3.5 4.0 Slrain, 0.001 in.fin.
420
280 ~ :2
V
11)
,11
1/
-/
V /
'"~
10
o
6.0
490
60
20
Source: K.E. Metzloff, H.W. Kwon, L.Y. Fang, and C.R. Loper, Ir., Service Modulus: A Method for Accurate Determination ofYoung's Modulus and Yield Strength in Ductile Iron, AFS Trans., Vol 104, 1996, p 727
1/
70
en
Bar diameter = 12.827 mm (0.505 in.). Samples primarily pearlitic with 90-95% pearlite. Test bars machined to ASTM A 536, Fig 6. Test was stress controlled at 345 MPalrnin (50 ksi/rnin). Typical yield strength = 400 MPa (58 ksi); ultimate strength = 738 MPa (107 ksi); elongation = 7.5%. Sample loaded to 75% YS, unloaded to 91 kg (200 lb), 10aded to 75% YS, unloaded to 91 kg (200 lb), 10aded to failure. Composition: Fe-3.684C2.422Si-0.469Mn-0.028P-0.015S-0.349Cu
420
VA f 0.5
~
CI.023 Pearlitic ductile iron bar, uniaxial tensile stress-strain curves
490
70
4.5
5.0
5.5
o
6.0
~
Bar diameter = 12.827 mm (0.505 in.). Samples primarily pearlitic with 90-95% pearlite. Test bars machined to ASTM A 536, Fig 6. Test was stress controlled at 345 MPalrnin (50 ksi/rnin). Typical yield strength = 400 MPa (58 ksi); ultimate strength = 738 MPa (107 ksi); elongation = 7.5%. Sample loaded to 100% YS, unloaded to 91 kg (200 lb), loaded to 100% YS, unloaded to 91 kg (200 lb), loaded to failure. Composition: Fe-3.684C2.422Si-0.469Mn-0.028P-0.015S-0.349Cu Source: K.E. Metzloff, H.W. Kwon, L.Y. Fang, and C.R. Loper, Ir., Service Modulus: A Method for Accurate Determination ofYoung's Modulus and Yield Strength in Ductile Iron, AFS Trans., Vol 104, 1996, P 727
Cast Iron (CI)/35
300 Elaltic
I
~L
Elaltic
,....
Test specimen size = 28.651 mm diam x 76.2 mm gage length (1.128 in. diam x 3 in. gage length). Permanent strain remains when sample unloaded. Total strain is permanent plus recoverable. 0.1 % proof stress (PS) = 232 MPa; 0.2% proof stress =242 MPa. Composition: Fe-3.66C-1.8Si-0.41Mn-0.0 12S-0.025P-0. 76Ni-0.064Mg
;?'Total
otal
V
o.7%PS 0.1%PS
200
I I
P~pt
---=rrr I 1 I11
250
CI.025 Ferritic ductile iron casting, longitudinal tensile stress-strain curves (a) with lateral contraction (b)
I
Source: G.NJ. Gilbert, The Stress/Strain Properties of Nodular Cast Irons in Tension and Compression, BClRA J., Vol 12 (No. 2), March 1964, p 177 100
50
o
O 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 (a) Strain, %
280
,.
240
...-
'/~
.J.
Total jermanent _1
I I
1/\
200
1 I
1 O 0.1 0.2 0.3 0.4 (b) Slrain, %
17
CI.026 Ferritic ductile iron casting, longitudinal compressive stress-strain curves (a) with lateral expansion (b)
~J Total " Permanent Recoverable
1 10.2% PS 0.1% psi Recoverable
Test specimen size = 28.651 mm diam x 76.2 mm gage length (1.128 in. diam x 3 in. gage length). Permanent strain remains when sample unloaded. Total strain is permanent plus recoverable. 0.1 % proof stress (PS) = 266 MPa; 0.2% proof stress = 267 MPa. Composition: Fe-3.66C-1.8Si-0.41Mn-0.0 12S-0.025P-0.76Ni-0.064Mg
11
o..'"
;:¡; !Ji
~ 160 ~
Source: G.NJ. Gilbert, The Stress/Strain Properties of Nodular Cast lrons in Tension and Compression, BClRA J., Vol 12 (No. 2), March 1964, p 182
I
'iij
~ 120
c.
E
o ü
80
40
f f 1/
00 0.1 (a)
0.2
0.3 0.4 0.5 Strain, %
0.6
0.7 0.8 O 0.1 0.2 0.3 (b) Strain, %
0.4
36/Cast lron (CI)
,
300r------,-----,------~_r--~------r_._--~
/
Curves based on the first cyc1e of loading and cyc1e tests carried out at les s than 0.1 % strain. The stress values are raised by strain hardening. Modulus of elasticity = 177 GPa. Composition: Fe-3.51C-2.07Si-0.32Mn-0.022S0.017P-0.046Mg
,/'
--,~ 0.1% /
200
c..'"
proof stress
Monotonic /
,
:2 ,Ji
Source: G.N.J. Gilbert, "The Stress/Strain Properties and Fatigue Properties of a Ferritic and a Pearlitic Nodular Cast Iron Tested under Strain Control," Report 1586, British Cast Iron Research Association (BCIRA), 1984
(fJ
~
//
2
CI.027 Ferritic nodular ductile iron casting, tensile monotonic and cydic stress-strain curves
,/
'00
,
e
~ 100
,,
/
,/'
,
/ 0.10
0.05
0.15
0.20
0.25
0.30
Strain, %
,, ,, , , ,,
350
300
g¡ro
250
Cl
e
¿~ Flrst cycle
!!'! 200
16
oS CIl "C
150
/
E ro
j
100
50
Cyclic
,, ,,
,//~
ID
,gc.
,,
/
r
,
/
V
,
,
,, ,, , , ,,
,, ,,
,, ,, , ,
Curves based on the first cyc1e of loading and a cyc1e at approximately half the fatigue life using the stress amplitudes (half stress range). Composition: Fe-3.51C2.07Si-O.32Mn-0.022S-0.017P-0.046Mg
, - - ;10.1%
, ,,
, ,, ,,
offset
Source: G.NJ. Gilbert, "The Stress/Strain Properties and Fatigue Properties of a Ferritic and a Pearlitic Nodular Cast Iron Tested under Strain Control," Report 1586, British Cast Iron Research Association (BCIRA), 1984
, ,, ,,
,,
, ,, ,, 0.05
0.10
0.15 Strain, %
0.20
CI.028 Ferritic nodular ductile iron casting, stress amplitude-strain curve for monotonic and cydic loading
0.25
0.30
Cast lron (CI)/37
CI.029 Ferritic nodular ductile iron casting, log stress-Iog plastic strain curve for monotonic and cyelic loading
20~----~~----~-------+--~---+--~--~
Work-hardening behavior shown for monotonic and cyc1ic loading based on maximum stress (dashed curve) and stress amplitude (solid curve) at approximately half the fatigue life. Half fatigue life is used to define cyc1ic stress-strain curve because fatigue behavior does not stabilize for these irons. Composition: Fe-3.51C-2.07Si0.32Mn-0.022S-0.017P-0.046Mg Source: G.N.J. Gilbert, "The Stress/Strain Properties and Fatigue Properties of a Ferritic and a Pearlitic Nodular Cast Iron Tested under Strain Control," Report 1586. British Cast Iron Research Association (BCIRA), 1984
Plastic strain
I, "'" "
300
0!1%/S
r-r
250
Ir
200 ::¡; rñ
100
50
Test direction: longitudinal. Proof stress (PS): 0.1 %, 246 MPa; 0.2%, 253 MPa; 0.5%, 263 MPa. Ultimate tensile strength = 400 MPa; elongation = 26.5%; hardness = 134 HB (10/3000). Composition: Fe-3.42C2.11Si-0.31Mn-0.014S-0.007P-0.061Mg
I
,/
Source: G.NJ. Gilbert and MJ.D. Frier, "The Stress/Strain Properties of a Pearlitic and a Nodular Cast Iron Cyclically Loaded between Equal and Opposite Strain Limits in Tension and Compression," Report 1579, British Cast Iron Research Association (BCIRA), 1984
I
m
.!!1 '00 c: ~
oyoJs
11
ro
a.
~ 150 m
o.~% PSj
CI.030 Ferritic nodular ductile iron casting, tensile stress-strain curve
I I
I
0.1
0.2
0.3
0.4 0.5 Strain, %
0.6
0.7
0.8
0.9
38/Cast Iron (CI)
600r---~--'----r--~---'----r---~--'---~
Normalized 12 in. (30asecti0i
~
1
T
in. (l45 mI' keel
6t/" ,)1"" '1
45
mI' ...
Ascalst I V / '/" , , '-.1. 12¡in. (30j.8 mm) ¡section
~I
I
,r
/"
1~in.
........
-
(304.8 mm) section
I
I
1.75 in. (44.45 mm) keel
I
0.1 (a)
0.2
0.3
0.4 0.5 Strain, %
0.6
0.7
0.8
0.9 O
0.1 (b)
0.2
0.3 0.4 Strain, %
0.5
0.6
CI.031 Recarburized steel ductile casting, longitudinal tensile stress-total strain curves (a) with lateral contraction (b) Comparison is made between 44.45 mm (1.75 in.) keel test blocks and 304.8 mm diam x 50.8 mm (12 in. diam x 2 in.) castings; 50.8 mm (2 in.) square test specimens cut from the latter. As-cast pearlitic nodular iron, normalized pearlitic, and annealed ferritic nodular iron are shown for each size. Composition: Fe-3.52C-1.76Si-0.29Mn-0.026S-0.020P-0.92Ni-0.062Mg Source: O.N.J. Oilbert, The Effect of Section Size on the Stress-Strain Properties ofNodular Cast Iron, BClRA J., Vol 12 (No. 6), Nov 1964, p 766
Cast Iron (CI)/39
500 450
,.--
400
/
350
a.'"
:2
300
/
rñ 1/) ~ 'li)
250
~
200
V
L
100
/
o()
/
0.1
0.2
0.3
0.4 0.5 0.6 Strain. 0.001 inJin.
0.7
Curve 1: nodu1ar iron; ultimate strength = 695 MPa; 0.1 % proof stress = 378 MPa. Curve 2: nodular iron, ultimate strength = 402 MPa; 0.1 % proof stress = 238 MPa. Allowable design stress is significantly less than the proof stress. Source: "Stress/Strain Behaviour of Nodular and Malleable Cast !rons," Broadsheet 157-2, British Cast Iron Research Association (BCIRA), 1981
2
~V
150
50
--
~
// ~%Ps
~
·00 c:
~%Ps
1
f..--'"
CI.032 Nodular ductile iron casting, typical tensile stress-strain curves at 20 oC
0.8
0.9
40/Cast lron (CI)
500 I
450
í/
r . /tr
400 350
g¡'"
1I\3~
~
~
/ 1//1 / Iy / fj
300
gf ~ 250
'" .!!! .¡¡;
~ 200
-
~
--
-
~~/
~' «e
11
10.2% PS
~
0.1%PS
d!
I
150 100
50
-
I
fec~~
I
/
/
/
00
0.1 (a)
0.2
0.3
0.4 Strain, %
0.5
0.6
0.7
0.8
o
0.1 (b)
0.2
0.3
Strain, %
CI.033 Pearlitic nodular ductile iron casting, longitudinal tensile stress-strain curves (a) with lateral contraction (b) Test specimen size = 28.651 mm diam x 76.2 mm gage length (1.128 in. diam x 3 in. gage length). Permanent strain remains when sample unloaded. Total strain is permanent plus recoverable. 0.1 % proof stress (PS) =347 MPa; 0.2% proof stress = 374 MPa. Composition: Fe-3.66C-l.8Si-0.41Mn-0.012S-0.025P-0.76Ni-0.063Mg Source: G.N.J. Gilbert, The Stress/Strain Properties of Nodular Cast Irons in Tension and Compression, BClRA J., Vol 12 (No. 2), March 1964, p 175
Cast Iron (CI)/41
500 450 400
f-----
350
/'
lO
~ 300
{,¡t-
¡tfI'3nen
V/ ~/
~e
II
:t)
f!
J'!
,,;
g¡
7
.¡¡¡ 250 ~
'iñ
~ 200
50
v I
I
I
--
~'I.1
~ f-
¿ 1/
I 0.2%PS
!!~V -4
If
I
0.1% PS
I
150 100
~
L Reco~erable
/
/
V
0.1
0.2
0.3
0.4
Strain, %
0.5
0.6
0.7
O (b)
0.1
0.2
0.3
Strain, %
CI.034 Pearlitic ductile ¡ron casting, longitudinal compressive stress-strain curves (a) with lateral expansion (b) Test specimen size = 28.651 mm diam x 76.2 mm gage length (1.128 in. diam x 3 in. gage length). Permanent strain remains when sample unloaded. Total strain is permanent plus recoverable. 0.1 % proof stress (PS) = 377 MPa; 0.2% proof stress = 398 MPa. Composition: Fe-3.66C-1.8Si-0.41Mn-0.012S-0.025P-0.76Ni-0.063Mg Source: G.NJ. Gilbert, The Stress/Strain Properties of Nodular Cast Irons in Tension and Compression, Be/RA J., Vol 12 (No. 2), March 1964, p 180
."
42/Cast Iron (CI)
400r---,----,---.----,---,----.----r---.---~
CI.035 Pearlitic nodular ductile iron casting, tensile stress-strain curves
Test direction: longitudinal. (a) Beginning of cyc1ing in tension to 350 MPa. (b) Behavior of same sample after 128 cyc1es to 350 MPa. 0.2% proof stress = 358 MPa; ultimate tensíle strength =659 MPa. Composition: Fe3.42C-2.11 Si-0.31Mn-0.014S-0.007P-0.061Mg Source: G.N.J. Gilbert and M.J.D. Frier, "The Stress/Strain Properties of a Pearlitic and a Nodular Cast lron Cyclically Loaded between Equal and Opposite Strain Limits in Tension and Compression," Report 1579, British Cast Iron Research Association (BClRA), 1984
ro o.. :2
"' 200 en
~
150
100
50
0.05
0.10
0.15
0.45
0.20
(a)
Strain, %
400
350
/
300
ro :2
250
o..
"'~ 200 en
j
150
100
/
50
O
I 0.25 (b)
J
~
~
'/
l'
V
0.30
0.35
0.40 Strain, %
0.45
0.50
Cast Iron (CI)/43
CI.036 Pearlitic nodular ductile iron casting, tensile stress-strain curves
500 / Jlastic lit
450
~I
o
0.5~ PS
tr:
/
400
1/
350 ro [L ::;;
/~
300
Ul
~
250
~
'c;; c:
~
200 150 100 50
f.-- f.--
rr
--
V
Source: O.NJ. Oilbert and MJ.D. Frier, "The Stress/Strain Properties of a Pearlitic and a Nodular Cast Iron Cyc1ically Loaded between Equal and Opposite Strain Limits in Tension and Compression," Report 1579, British Cast Iron Research Association (BCIRA), 1984
/1 II
rñ
1ñ
a!2% PS 0.1% PsJI---
IJ
/ /
/
0.1
0.2
0.3
0.4 0.5 Strain, %
0.6
400
0.7
0.8
0.9
/
1 1 1 /1 1
ro ::;; [L
/
rñ Ul
~
1ñ ~
'c;; c: 200
1/
JI
/
0.05
/ 0.10
1
/0.1% o 1 proof Monotonic / stress
l'
/
1 1 1 1 1 1 1 1
/
0.15 Strain, %
0.20
0.25
CI.037 Pearlitic nodular ductile iron casting, tensile monotonic and cyclic stress-strain curves Curves based on the first cycle of loading and cycle tests carried out at less than O.l % strain. Strain hardening only contributes a slight increase in raising tensile stress level. Composition: Fe-3.64C-2.25Si-0.38Mn-0.010S-0.019P0.044Mg Source: O.NJ. Oilbert, "The Stress/Strain Properties and Fatigue Properties of a Ferritic and a Pearlitic Nodular Cast Iron Tested under Strain Control," Report 1586, British Cast Iron Research Association (BCIRA), 1984
1 1 1 1 1 1 1 1
/
100
CJCliC
........
(/
If
~
1
~ --~
/~
300
o
Test direction: longitudinal. Proof stress (PS): O.l %, 355 MPa; 0.2%, 358 MPa; 0.5%, 395 MPa. Ultimate tensile strength = 659 MPa; elongation = 6.5%; hardness = 219 HB (10/3000). Composition: Fe-3.42C2.11Si-0.31Mn-0.014S-0.007P-0.061Mg
0.30
44/Cast Iron (CI)
400.------r------r------r-----,,,~--_,----_.-
I
al
~ 300~----~------~----~~~~------4_/~---4~ íi) Cl
c:
-ro
CI.038 Pearlitic nodular ductile iron casting, stress amplitude-strain curves for monotonic and cyclic loading Curves based on the first cycle of loading and a cycle at approximately half the fatigue life using the stress amplitudes (half stress range). Modulus of elasticity = 183 GPa. Composition: Fe-3.64C-2.25Si-0.38Mn-O.010SO.019P-O.044Mg
['!
EQ)
"tl
::l
% 200~----~------~----~----_4~----4_----_4~ E I al
'"'" ~
/ /1/
(J)
Source: G.NJ. Gilbert, "The Stress/Strain Properties and Fatigue Properties of a Ferritic and a Pearlitic Nodular Cast Iron Tested under Strain Control," Report 1586, British Cast Iron Research Association (BCIRA), 1984
I
I
100~-----V~----~----~/-----4------4_----_4~
o
0.05
0.10
0.15
0.20
0.25
0.30
Strain, %
CI.039 Pearlitic nodular ductile iron casting, log stress-Iog plastic strain curve for monotonic and cyclic loading Work-hardening behavior shown for monotonic and cyclic loading based on maximum stress (dashed curve) and stress amplitude (solid curve) at approximately half the fatigue life. Half fatigue life is used to define cyclic stress-strain curve because fatigue behavior does not stabilize for these irons. Composition: Fe-3.64C-2.25SiO.38Mn-O.010S-0.019P-O.044Mg Source: G.NJ. Gilbert, "The Stress/Strain Properties and Fatigue Properties of a Ferritic and a Pearlitic Nodular Cast Iron Tested under Strain Control," Report 1586, British Cast lron Research Association (BCIRA), 1984
1 -5 10 Plaslic slrain
Cast Iron (CI)/45
400r---~---r---'----'---'----'----r---.---,
350~--+----r---1----+----r---±~~r1~~--~
300~--+----r---1--·--~---r---+--.HhH~~--~
250r---+----r--~T_--+_--_r--_+.~ñhr_--+_--~
150r---+-~~--~--·--+_--~~84----~--+---~
100~--+F---r---1----+'~~~-+----r---~--~
0.05
0.10
0.15
0.20
0.25
0.30
0.35
0.40
0.45
Strain, %
(a)
400
350
/
300
L7
250
1/
'"
~ 200
j
ID
~
Ci5 150
100
/
50
o
0.25 (b)
f'
/
'/
!/
l'
0.30
0.35
0.40 Strain, %
0.45
0.50
0.55
CI.040 Ductile iron casting, cyelic stress-strain curves (a) The first severa! cyc1es in tension to 350 MPa. (b) 128 cyc1es in tension to 350 MPa. Composition: Fe3.45C-2.18Si-0.33Mn-0.012S-0.004P-0.048Mg Source: G.NJ. Gilbert, ''The Cyclic Stress/Strain Properties of a Ferritic Nodular Iron Tested under Completely Reversed Loading and under Tensile LO!iding," Report 1534, British Cast Iron Research Association (BCIRA), 1983
46/Cast Iron (CI)
CI.041 Gray iron casting, tensile stress-strain curves showing effect of graphite form 16 - - - - - -
112
75% UTS
84
12
ro
.¡¡;
Il.
::¡;
~
'" ~
TS, total strain; RS, recoverable strain; UTS, 75% ultimate tensile strength. (a) Compacted graphite. (b) Type A graphite. (e) Widmanstatten graphite
56
8
~'"
en
4~~------+---------+---------~--------~28
00
0.1
0.2
O
0.3
0.4
Strain, %
(a)
84
12 75% UTS
56
8 .¡¡;
ro
Il.
::¡;
~
'"
~
~ 28
4
o
0.4
0.1 Strain,%
(b)
42
6
-----75% UTS
.¡¡; ~
28
ro
Il.
::¡;
~
~
iñ 2
14 en
0.3
0.1 (e)
Strain, %
O 0.4
Source: R.E. Maringer, "Damping Capacity of Materials," Report RSIC-508, Battelle Memorial Institute, Redstone Scientific Information Center, Redstone Arsenal, Jan 1966, AD 640465. As published in Structural Alloys Handbook, Voll, CINDAS/Purdue University, 1994, p 20
Cast Iron (CI)/47
45 40 35 30
g¡
25
~ 20
Cñ
15
./'
70°F (21 °Cy V
1//~ / WV /)V VI
315
CI.042 Gray iron casting, stress-strain curves to fracture at room and elevated temperatures
750 .)(399 OC) 280
Composition: Fe-3.19C-(CC-0.85)-1.66Si- 0.91Mn0.077P-0.089S
~ ¡""-840 o~I (449 OC)
V
L---
V
-
245
1
I--~
~
210 175
g¡'"
140
g en
ui
105
10
70
5
35
0.25
0.50
Source: C.E Walton, Gray and Ductile ¡ron Castings Handbook, Gray and Ductile Iron Founders' Society, 1965. As published in Structural Alloys Handbook, Vol 1, CINDASlPurdue University, 1994, p 20
930 °F (499 OC)
0.75
1.00
1.25
1.50
o
1.75
Strain,%
70r---~--~---'r---~---r---.----~--,---~490
60~--~----+--~~---+---~--~----~--~----
2
'c;;
.>::
350
40LL-1A~t:~~~~rLJ 280
E
30~--+-~~~~----+'~~--.4~~~--+---~ 210
Plastic strain
140
/ L---~-L-L
0.1
0.2
__
~~~~
0.3
0.4
__
~
0.5
Elongation, %
__
~
0.6
__- L__- L__
0.7
0.8
Casting thickness: curve 1, 12.7 mm (0.5 in.); curve 2, 25.4 mm (1 in.); curve 3, 152.4 mm (6 in.); curve 4, 76.2 mm (3 in.). Dashed lines indicate plastic strain.
420
ui
en
CI.043 Pearlitic gray iron casting, stress-strain curves showing effect of section size
~O
0.9
~
::¡; ui Ul ~
Cñ
Source: C.E Walton, Gray and Ductile ¡ron Castings Handbook, Gray and Ductile lron Founders' Society, Aug 1971. As published in Structural Alloys Handbook, Vol!, CINDASlPurdue University, 1994, p 20
48/Cast Iron (CI)
40,-----,------r------,-----,------.-----,--, 280
CI.044 Class 20 to 50 gray iron casting, tensile stress-strain curves
35~----4-----_+------~----+_-----+~~~--~245
Source: J.L. Herron, R.A. Flinn, and P.K. Trojan, Research for !he artiele: Mechanical Properties of Gray Iron, ¡ron Castings Handbook, C.E Walton, Ed., Iron Casting Society, 1981, p 211
30~----~-----+------r_----~~--~--~~--~210
g¡
25 ~--+---~--_btL--__7I~--+;7"'=-___/-~ 175
~ ~
m w
~ 20
140 ~
~
w
~
~
~
:;¡;
~
15
Class 20
105
~
10~----~~~~-----~----~-----+-----r_~70
~~~+_----~----_r-----+----~------r_~35
~
L-____
_ _ _ _L __ _ _ _L __ _ _ _L __ _ _ _L __ _ _ _
0.05
0.10
0.15
0.20
0.25
L-~O
0.30
Strain, %
35.-----,-----,-----,----,-----,-----,,----,245
CI.045 Class 30 gray iron casting, cyelic tensile stress-strain curves
30~----+-----+-----+---~~~~+~L++----~210
Permanent deformation results froro rerooval and reapplication of load.
25~----~--~--_r~----74+---~-+--_+----~175
Source: J.L. Herron, R.A. Flinn, and P.K. Trojan, Research for the artiele: Mechanical Properties of Gray Iron, ¡ron Castings Handbook, C.E Walton, Ed., Iron Casting Society, 1981, p 229
10~--~~~--+-~+-+-~~+-----+-----+----~70
Strain, %
Cast Iron (CI)/49
45.-----,----,-----,-----,-----,-----,-----, 315
CI.046 Class 40 gray iron casting, cyelic tensile stress-strain curves
40~----+-----+_----4_----~----~----~-----1
280
Permanent deformation results from removal and reapplication of load.
35~----+-----+-----4-~A-~AL--~----~-----4
245
Source: J.L. Herron, R.A. F1inn, and P.K. Trojan, Research for the artiele: Mechanical Properties of Gray Iron, Iron Castings Handbook, C.F. Walton, Ed., Iron Casting Society, 1981, p 229
210 ro
a. :2 ~25~----+---~~f-~~~1-~----~-----+-----1 175 rñ
~
VJ
~
~
~ 20~----+_~_h~~~~L---~----~----_+----_1 140
~
~
~
<::
VJ
<::
105 70 35
0.1
0.3
0.4 Strain, %
0.2
0.5
0.6
40
35
30
g¡
25
rñ VJ
Q)
~ 20 ~ .c;;
I
/
Plastic
/ I I
10
5
/
/
./
V 1/
V
E1a1
#
<::
~ 15
/
V/
~
O
0.7
280
CI.047 Pearlite gray iron casting, tensile stress-strain curves
245
Total strain is composed of plastic and elastic portions ..
210
Source: J.W. Grant, Comprehensive Mechanical Tests ofTwo Pearlite Gray Irons, J. Res. BCIRA, Vol 3, Apri11951, P 861-875. Adapted from C.F. Walton, Ed., Iron Castings Handbook, lron Casting Society, 1981, p 228
175 ~ :2
~ 140 ~ VJ
V
~ .c;;
<::
105 ~
A~
70
35
0.05
0.10
0.15 Strain, %
0.20
0.25
o
0.30
SO/Cast Iron (CI)
550 500
./
450 400
/
350
~ 300 ui
~
1ií
~ 40 compression
/'
250
-
70
-
60
.¡¡;
- 40
----
¡j ~' // -- --
150 100 50
If"
-----
0.4
0.2
0.6 Strain, %
70 compre 60
50
/
~ ui 40
30
20
10
/
f
30
-
20
-
10
- - C¡;ss 20 tension
/ !V
/
V
.......-
O
1.0
0.8
80
'" ~
-
.;
I!
C/)
""ui '"~
1ií
- - cÍass 20 compression
200
Souree: J.L. Herron, R.A. Flinn, and P.K. Trojan, Researeh for!he artiele: Meehanieal Properties of Gray !ron, ¡ron Castings Handbook, c.F. Walton, Ed., Iron Casting Society, 1981, p 235
50
/ / ~~-'y
ro
CI.048 Class 20 and 40 gray iron casting, tensile and compressive stress-strain curves
V--
/
~
---
560
CI.049 Class 35 gray iron casting, tensile and compressive stress-strain curves
490
Souree: J.L. Herron, RA. Flinn, and P.K. Trojan, Research for the artiele: Mechanical Properties of Gray Iron, ¡ron Castings Handbook, C.F. Walton, Ed., !ron Casting Society, 1981, p 234
420
350
ro o.. :2 280 ui
V--
~
'"~
Tension
1ií 210
140
70
0.2
0.4
0.8 0.6 Strain, %
1.0
1.2
o
1.4
Cast Iron (CI)/51
70
CI.050 Class 20, 40, and 60 gray iron casting, typical tensile stress-strain curves
60
Source: Gray Iron, Properties and Selection: lrons, Steels, and HighPerformance Alloys, Vol 1, ASM Handbook, 1990, p 20
500~------r-------.-------,-------,-------.
400~------~------+-------+-----~~----~
50
'" :2
300
a.
'" ~
40
.¡¡; -"
.;
IJ)
IJ)
30
200
~
20 100~--~~~----~~------+-------+-------4
10
2
4
3
Strairl, mm/m (0.001 inJin.)
200
Lateral strain
175
Ii
150
2/ I I 12 /
125 100
11
75 25
'" :2 a.
.; ~
¡¡j
O
II
:' :'
/"
Source: G.NJ. Gilbert, Stress/Strain Properties of Cast Iron and Poisson's Ratio in Tension and Compression, BClRA J., Vol 9 (No. 3), May 1961, p 351
l/
.'
;11
,,
-50
,~
-75 -100
"A 3~
II
-125
'ti
1
J I:-V/ U ",-
-150
-225 -0.3
#,'2
:/
,, ,,,
Progression oftest follows numbers 1-3 (solid line 1 to dashed line 1 to solid line 2 to dashed line 2, etc.). Solid lines are load applications; dashed lines are relaxations. These are relatively high stresses. Composition: Fe-3.2C2. 19Si-0.56Mn-O.031S-0.046P
,###
I / '/- 1, 13 / II /!'" 111 V3 " 1/ /3 / ::1 ./' ##
-200
A
I
-25
-175
t.-- ¡-- -2/
r/¡,,
50
CI.051 Gray iron casting, tensile and compressive longitudinal and lateral stress-strain curves
Longitudinal strain
!~ V
r
-0.2
l/:~
~
1 -0.1
o
0.1 0.2 Strain, %
0.3
004
0.5
0.6
52/Cast Iron (CI)
250r-----r----,-----,-----,----~----_,----~
CI.052 Flake graphite, gray iron casting, tensile stress-strain curves with cyelic loading lo increasing stress levels Ultimate strength = 230 MPa. Permanent deformation increases with increasing stress levels. Source: "Stress/Strain Behaviour of Flake Graphite Cast Irons," Broadsheet 157-1, British Cast Iron Research Association (BCIRA), 1977
0.7
Strain, %
280 260
/com~ressive
240
200
/
180
'"
a. 160
/
140
~
1ñ 120 100 80
t
60 40 20
/ V
/ Fracture
...... ~ ""--Te;;e
/ / // // /
l'
0.1
= 600 MPa
Source: "Stress/Strain Behaviour of Flake Graphite Cast Irons," Broadsheet 157-1, British Cast Iron Research Association (BClRA), 1977
1/
:::;
'"
Compressive strength
/V
220
In
CI.053 Flake graphite, gray iron casting, comparison of tensile and compressive stress-strain curves
/'1
0.2 0.3 0.4 Tensile and compressive strain, %
0.5
0.6
Cast Iron (CI)/53
CI.054 Flake graphite, gray iron casting, cyclic stress-strain curves
200
150
/
100
III
/
50
a. ::¡¡;
/
IJ)
~
O
/,V
-50
-100
-150
V
V
~
V
Stress-strain curves for cycles 129-132 with loads varying ±175 MPa. The hysteresis loop advances to the right as the number of cycles increase. Source: O.NJ. Oilbert and S.D. Kemp, "The Cyclic Stress/Strain Properties of a Flake Graphite Cast Iron-A Progress Report;' Report 1384, British Cast Iron Research Association (BCIRA), July 1980
!V
h~ l'
-0.15 -0.10 -0.05
O
0.05
0.10
0.15
0.20
0.25
Strain, %
CI.055 Gray iron casting, components of total stress-strain curves Considering iron as a composite, the total strain 5, can be thought of consisting of the 1, plastic matrix; 2, voids with recoverable deformation; 3, elastic matrix; 4, voids with permanent deformation. Iron can be considered having a steel-like matrix with volume changes occurring in the spaces occupied by graphite. Iron tensile strength = 213 MPa Source: O.N.J. Oilbert, ''The Cyclic Stress/Strain Properties and FatigUe Properties of a Flake Oraphite Cast Iron Tested under Strain ControlA Detailed Study," Report 1621, British Cast Iron Research Association (BCIRA), 1985
°0L---~--~~--L---~--~~--~--~--~
0.1
0.2
0.3
0.4
Strain, %
0.5
0.6
0.7
0.8
54/Cast Iron (CI)
CI.056 Gray iron casting, cyclic stress-strain curves
250 200
fnd, 3rd 6ycles 150
1st cycle,
~
100
/
50
ro
uf
'"~
úí
/
O
~
-50
/
Source: G.N.J. Gilbert, "The Cyclic Stress/Strain Properties and Fatigue Properties of a Flake Graphite Cast Iron Tested under Strain ControlA Detailed Study," Report 1621, British Cast Iron Research Association (BCIRA), 1985
V
fi ~
-100
hV
-150 -200
~
~
Curves for first three cyc1es to ±O.20% strain. Composition: Fe-3.13C-2.15Si-O.35Mn-O.025S-0.086P
V/ V
O-
:2
V/
,¿
V
-250 -0.20
~
V
-0.15
-0.10
-0.05
o
0.05
0.10
0.15
0.20
Strain, %
CI.057 Gray iron casting, cyclic stress-strain curves
250 200
./
150 2512th cycle 100
ro
~
50
O-
:2 uf
'" ~
en
O
//
-50
Source: G.N.J. Gilbert, "The Cyc1ic Stress/Strain Properties and Fatigue Properties of a Flake Graphite Cast Iron Tested under Strain ControlA Detailed Study," Report 1621, British Cast Iron Research Association (BCIRA), 1985
/'
/ // /
~V
-100
h
-150 -200
~
V
~
/
-250 -0.20
yr
~
-0.15
-0.10
-0.05
o Strain, %
0.05
0.10
0.15
Curve for 2512th cyc1e to ±O.20% strain. (Fatigue failure occurred at 3769 cyc1es.) Composition: Fe-3.13C-2.15Si0.35Mn-O.025S-0.086P
0.20
Cast Iron (CI)/55
170
CI.058 Gray iron casting, modulus of elasticity-stress curves
160
Modulus of elasticity (E) for compression of first and 2512th cycle. At maximum compressive stress (0.0020 strain controlled) first cycle, E = 144.95 GPa; 2512th cycle, E = 144.20 GPa
150
o..'"
C!l 140
~~
.......
¿.
·0 ~ Qi 130
~
'"
~~
""'" ~ ~ f;::- r---
'O
!I)
::l
S
"O
o
Source: G.NJ. Gilbert, "The Cyclic Stress/Strain Properties and Fatigue Properties of a Flake Graphite Cast Iron Tested under Strain ControlA Detailed Study," Report 1621, British Cast Iron Research Association (BCIRA), 1985
120
""'""
;¡;
110
2512th cycle 100
90
50 -250 -200 -150 -100-50 O Stress, MPa
~ 1'----.
~
r-
·0
~
~ ~
130
~~
,
Source: G.N.J. Gilbert, "The Cyclic Stress/Strain Properties and Fatigue Properties of a Flake Graphite Cast Iron Tested under Strain ControlA Detailed Study," Report 1621, British Cast Iron Research Association (BCIRA), 1985
~
!I)
::l
o
250
Modulus of elasticity (E) for tension of first and 2512th cycle. At maximum tensile stress (0.0020 strain controlled) first cycle, E = 157.62 GPa; 2512th cycle, E = 155.62 GPa.
¿.
"O
200
160
o..'"
S
150
CI.059 Gray iron casting, modulus of elasticity-stress curves
C!l 140
'" 'O
1"-"
170
150
Qi
100
------~stCYCle
120
~ First cycle
2512thc~
;¡;
110
~
~
100
90
-200
-150
-100
-50 o Stress, MPa
50
100
150
56/Cast Iron (CI)
CI.060 Pearlitic and ferritic malleable iron casting, typical tensile stress-strain curves
700
100 1
80
/ ....-
i ~
)
40
2
ro
420
V
I
20
V 0.1
g¡ ~ 1ñ
Source: L.W.L. Smith and O.N.J. Gilbert, "The Tensile Properties oI Blackheart and Pearlitic Malleable Irons-A Progress Report," Report 1363, British Cast lron Research Association (BCIRA), Jan 1980, p 49-62. As published in C.E Walton, Ed., [ron Castings Handbook, lron Casting Society, 1981, P 304
~ .¡¡;
280 ~
3
v:-
Typical curves obtained from machined cast-to-shape test bars. Curve 1, pearlitic, oil quenched; curve 2, pearlitic, air quenched; curve 3, ferritic
560
V
~ 60
~ .¡¡; e
¡..---
V /
~ 140
0.2
0.3
0.4
0.5
0.6
0.7
0.8
0.9
o
1.0
Slrain, %
CI.061 Blackheart malleable iron casting, tensile and compressive stress-strain curves
350
300 / ' -,....
250
&.
Compression
1/~ 1
I
200
1/1
:2
1
Teniion
/
1/ 1/0 .1% 0.2% PS
-
Produced at 980 oC, fast cooled to 760 oC, slow cooled to 700 oc. Specimens were as-cast to shape. Tested at strain rate of O.Ol/min. 0.2% proof stress (PS): tensile, 346 MPa; compressive, 284 MPa. Compressive PS at 0.2% is slightly less than at 0.1 %. Composition: Fe2.46C-l.40Si-0.46Mn-0.178S-0.034P-0.0032B-0.001Al0.038Cr
V
-
1/0.5% PS
Source: L.W. Smith, "The Effect of Strain Rate on tbe Compressive Stress/Strain Properties of Ma11eable lrons," Report 1508, British Cast lron Research Association (BCIRA), 1983, P 32
PS
~
1i5 150
III III
100
50
I I 1/
11 1/ 1/ OO
0.1
0.2
0.3
OA
0.5 Slrain, %
0.6
0.7
0.8
0.9
1.0
Cast Iron (CI)/57
CI.062 Blackheart malleable irán casting, compressive stress-strain curves with effect of strain rate
350
300
~~ -:::::::: %
J:t:
250
~
ro
a..
:2 .;
'"
i
200
~::::: 1;.-Slrain rale: 0.2/min 0.021 min 0.0021 min 0.00061 min
r---
Source: L.W. Smith, "The Effect of Strain Rate on the Compressive Stress/Strain Properties of Malleable Irons," Report 1508, British Cast Iron Research Association (BCIRA), 1983, p 35
I
O·I %jS
'">
·00
'" 150 i!! c.
0.2% PS
E
o
ü
Produced at 980 oC, fast cooled to 760 oC, slow cooled to 700 oc. Specimens were as-cast to shape. Tested at strain rates shown. 0.2% proof stresses (PS) vary from 236-261 MPa. Composition: Fe-2.46C-1.40Si-0.46Mn0.178S-0.034P-0.0032B-0.001AI-0.038Cr
0.5% PS
100
50
O O
I
I 0.2
0.4
0.6
0.8
1.0 1.2 Slrain, %
1.4
1.6
1.8
2.0
CI.063 Pearlitic malleable iron casting, compressive stress-strain curves with effect of strain rate
600
500
/1.. 400
¡:f i!! tí
~ ·00
300
~c.
E
8 200 100
--~t'b::::::
r¡¡ I
:2
/(o/r
//
I~i%
1// I 0.2
0.4
~
Annealed, 870 oC, air quenched, tempered, 700 oC, 6 h, 600 oC, 4 h. Specimens were as-cast to shape. Tested at strain rates shown. 0.2% proof stresses (PS) vary from 375-393 MPa. Composition: Fe-2.51 C-1.43Si-0.50Mn0.201S-0.039P-0.0031B-0.015AI-0.040Cr
-
~
~
::--1-
Slrain rale:
Source: L.W. Smith, "The Effect of Strain Rate on the Compressive Stress/Strain Properties of Malleable Irons," Report 1508, British Cast Iron ResearchAssociation (BCIRA), 1983, P 36
0.2/min
1" 0.0021 min
0.00061 min
1/
(
0.5% PS
/
0.6
0.8
1.0 1.2 Slrain, %
1.4
1.6
1.8
2.0
58/Cast Iron (CI)
CI.064 Pearlitic malleable iron casting, compressive stress-strain curves with effect of strain rate
600
-
---:;::::. ~
500
~~~
~
&.
400
:2
gf ~
1ñ
.~ 300
~o. E 8 200
Annealed, 870 oC, air quenched, tempered, 700 oC, 6 h. Specimens were as-cast to shape. Tested at strain rates shown. 0.2% proof stresses (PS) vary from 398-410 MPa. Composition: Fe-2.44C-l.54Si-0.50Mn-0.180S0.039P-0.0036B-0.020AI-0.048Cr
~~
~I 1 Il/';l 1/
Strain rate: -00.2/min ~ 0.002/min 0.0006/ min
Source: L.W. Smith, "The Effect of Strain Rate on the Compressive Stress/Strain Properties of Malleable Irons," Report 1508, British Cast Iron Research Association (BCIRA), 1983, P 36
PS
1/ t% I I111 1
0.5% PS
PS
100
oO
0.2
0.4
0.6
0.8
1.0 1.2 Strain, %
1.4
1.6
1.8
2.0
700,---,---,---,---,---,---,---,---,---,---,
600~--~--~--+---+_--+_--+_~~--~~~~~
500 1-__+--~~""'--+__----::J.¡..._s.-"1""--..p.~+Strain rate: 0.2/ min 0.005/ min a.. :2 0.0006/min gf 400 I---+lfl.-f-+l---+__+-+_--+_--_l_--+_--+_--_+_---I ~ 1ñ ro
~
"m ~
300~-+~-++---~--+---+---+---+---+---~--~
o.
E
8 2001-+-~+-+__--+_--+_--_l_--_l_--+_--+_--_+_---I
100~~~--+__-++__--+_--_l_--_l_--+_--+_--_+_---I
oo
0.2
0.4
0.6
0.8
1.0 1.2 Strain, %
1.4
1.6
1.8
2.0
CI.065 Pearlitic malleable iron casting, compressive stress-strain curves with effect of strain rate
Annealed, 870 oC, air quenched, reheated to 640 oC in 1.5 h, tempered, 640 oC, 4 h. Specimens were as-cast to shape. Tested at strain rates shown. 0.2% proof stresses (PS) vary from 439-502 MPa. Composition: Fe-2.4IC1.37Si-0.50Mn-0.192S-0.034P-0.0035B-0.041 Cr Source: L.W. Smith, "The Effect of Strain Rate on the Compressive Stress/Strain Properties of Malleable Irons," Report 1508, British Cast Iron Research Association (BCIRA), 1983, p 36
Cast Iron (CI)/59
600
..-
500
¡)7
~ 400
::iE
'/o¡Lps
i
~ 300
.~ ~
O-
~
I
200
100
~ ~train rate:
~~.2/min
~0.02/min b.. 0.005/ min _
/
"0.0006/ min
/1/ L• f,s.ps 1/ / / 1// I /
oO
0.2
0.4
0.6
0.8
1.0 1.2 Strain, %
1.4
700
600
500 III
c..
::iE ui CI) ~
400
1ií
.~ Ul Ul
~
-
=-::: :::::::
Annealed, 840 oC, oil quenched, tempered, 680 oC, 2 h. Specimens were as-cast to shape. Tested at strain rates shown. 0.2% proof stresses (PS) vary from 468-502 MPa. Composition: Fe-2.46C-l.40Si-0.51Mn-0.206S0.043P-0.0032B-0.040Cr Source: L.W. Smith, "The Effect of Strain Rate on the Compressive Stress/Strain Properties of Malleab1e Irons," Report 1508, British Cast Iron Research Association (BCIRA), 1983, P 32
PS
E
8
¡......-:
~
CI.066 Pearlitic malleable iron casting, compressive stress-strain curves with effect of strain rate
tt í"""'7
"~
I
Ir/ / / / /o¡r / /II/g·~% 10.5% // / /
1.6
1.8
2.0
CI.067 Pearlitic malleable iron casting, compressive stress-strain curves with effect of strain rate
-
'"
Annealed, 840 oC, oil quenched, tempered, 650 oC, 2 h. Specimens were as-cast to shape. Tested at strain rates of 0.0006-0.20/min; three curves shown for clarity. 0.2% proof stresses (PS) vary from 530-599 MPa. Composition: Fe-2.43C-l.35Si-0.50Mn-0.213S-0.042P0.0035B-0.040Cr
¡...---
Strain rate: 0.2/ min 0.005/ min 0.002/min
Source: L.W. Smith, "The Effect of Strain Rate on the Compressive Stress/Strain Properties of Mal1eab1e Irons;' Report 1508, British Cast Iron Research Association (BCIRA), 1983, P 37
OPS
300
O-
E o
ü
200
100
VI 1/ 0.2
0.4
I
0.6
PS
0.8
1.0 1.2 Strain, %
1.4
1.6
1.8
2.0
60/Cast lron (CI)
CI.068 Pearlitic malleable iron casting, compressive stress-strain curves with effect of strain rate
800
~
700
/ 7I
ro
o.. :¡; 500
~
110.,t.
~
tí
~ 400
.~
~
A
600
"
/
/
PS
-::
~:train rate: ~
0.2/min 0.002/min _ "0.0006/ min
/
/I I /II ./0.5% ji I / 1I I / I
Source: L.W. Smith, "The Effect of Strain Rate on the Compressive Stress/Strain Properties of Malleable Irons," Report 1508, British Cast Iron Research Association (BCIRA), 1983, P 39
1/
0.2% PS
~
Cl.
E 300
o
ü
200
100
oO
0.2
0.4
0.6
0.8
PS
1.0 1.2 Strain, %
1.4
1.6
1.8
2.0
CI.069 Malleable iron casting, typical tensile stressstrain curves at 20 oC
450 ....lII
400
/
350
tf
:¡;
V
~
¡.---
1
Curve 1: pearlitic malleable iron, ultimate strength = 564 MPa; 0.1 % proof stress (PS) = 377 MPa. Curve 2: whiteheart malleable iron, ultimate strength = 425 MPa; 0.1 % proof stress =233 MPa. Curve 3: ferritic malleable iron, ultimate strength = 324 MPa, 0.1 % proof stress = 193 MPa. Allowable design stress is significantly less than the proof stress.
0.1% PS
1/
300
/
~ ~ 250 tí
2
V ~PS
~ .¡¡; ~ 200
3
Source: "Stress/Strain Behaviour of Nodular and Malleable Cast Irons," Broadsheet 157-2, British Cast Iron Research Association (BCIRA), 1981
...lIo
-;-
I.V
150
~.1% ~S
! /
100
50
1/ oO
0.1
0.2
0.3
Air quenched and tempered malleable iron was reheated to 870 oC, oil quenched, tempered, 600 oC, 2.5 h. Specimens were as-cast to shape. Tested at strain rates of 0.0006-0.20/min; three curves shown for clarity. 0.2% proof stresses (PS) vary from 625-644 MPa. Composition: Fe-2.58C-1.45Si-0.53Mn-0.218S-0.032P0.003IB-0.043Cr
004 0.5 Strain, %
0.6
0.7
0.8
0.9
Cast Iron (CI)/61
800
700 f------
600
/
/
l1\aJ~1-
~
~ iI1
rti
.:;:
8
'1
~~I I I
~
-
I • 0.1% PS_O.2% PS
~ )
500
/
V 300
/
200
100
/
I
V
0.1
0.2
0.3
0.4 Slrain, %
0.5
0.6
0.7
0.8
°
(b)
0.1
0.2
0.3
Slrain, %
CI.070 High-silicon nodular graphite iron casting, longitudinal compressive stress-strain curves (a) with lateral expansion (b) Test specimen size = 28.651 mm diaro x 76.2 mm gage length (1.128 in. diaro x 3 in. gage length). Permanent strain remains when sarople unloaded. Total strain is permanent plus recoverable. 0.1 % proof stress (PS) = 676 MPa; 0.2% proof stress = 707 MPa. Composition: Fe-2.62C-6.14Si-0.35Mn-0.014S-0.021P-0.78Ni-0.051Mg-0.006Ce Source: G.N.J. Gi1bert, The Stress/Strain Properties of Nodu1ar CasI Irons in Tension and Compression, BClRA J., Vol 12 (No. 2), March 1964, p 183
62/Cast Iron (CI)
CI.071 Nickel alloy iron casting, tensile stress-strain curves
,---------r----r-¡-----,------¡56o
Various c1asses of nickel cast irons Source: "Engineering Properties and Applications of Nickel Cast Irons," International Nickel Co. As published in Structural Alloys Handbook, Vol 1, CINDASlPurdue University, 1994, p 7
~--------~--+---~-+--~~----+---------~420
'"
.¡¡;
"'rñ" (j)
~
(L
:2'
40
rñ 280 (j)
m
~
30
Ci5
L---------~--------~----------~--------~O
0.2
0.4
0.6
0.8
Slrain, %
400
350
/ //
300
250
Ji
'"
(L
:2' rñ 200 (j) ~
Ci5
150
100
50
/
/
/
r
1/~
----
CI.072 Pearlitic and ferritic compacted graphite iron casting, typical stress-strain curves
- 40
~
~
Ferrilic .¡¡;
- 30 "": (j)
~ m - 20
- 10
0.1
0.2
Modulus of elasticity = 144 GPa. Pearlitic iron: tensile strength = 410 MPa (59.5 ksi); e1ongation = 1%. Ferritic iron: tensile strength = 320 MPa (46.5 ksi); elongation = 3.5%
- 50
0.3
0.4
Slrain, %
0.5
0.6
o
0.7
Source: E. Nechtelberger, H. Puhr, J.B. von Nesselrode, and A. N akayasu, Paper presented at the 49th International Foundry Congress, International Comrnittee of Foundry Technical Associations, Chicago, 1982. As published in D.M. Stefanescu, Compacted Graphite Irons, Properties and Selection: Irons, Steels, and High-Performance Alloys, Vol 1, ASM Handbook, ASM International, 1990, p 57
Cast Iron (CI)/63
CI.073 Alpha (a) iron alloy forging, true compressive stress-strain curves
700
Tested at 500 oC (932 °P) at strain rates indicated. Specimens were forged at 900 oC (1652 °P) and annealed at 750 oC (1382 °P) for 2 h. Alpha iron has a bodycentered-cubic crystal structure. Composition: Pe0.007C-0.03Mn-0.005S-0.003P
600 Strain rate: 500
100/5
~
ro
D.
:2 400
F V--
en
al
~
300
f?
100
o
0.1/50.01/5 0.001/5
~
0.2
0.1
O
1.0/5
~
-~ ----
200
Source: O.S. Avadhani, Indian Institute of Science, Bangalore, India. As pub1ished in Rot Working Guide, Y.V.R.K. Prasad and S. Sasidhara, Ed., ASM Intemational, 1997, p 263
10/5
V-- r--
i
l---
~
0.4 0.3 True pla5tic 5train
0.5
0.6
CI.074 Alpha (a) iron alloy forging, true compressive stress-strain curves
250
200
&.
:2
~
150
en ~
1il al
~ 100
50
/ V /
100/5
-10/5
Source: O.S. Avadhani, Indian Institute of Science, Bangalore, India. As published in Rot Working Guide, Y.V.R.K. Prasad and S. Sasidhara, Ed., ASM Intemational, 1997, p 263
Strain rate:
-----------
V
1.0/5
~
~
-
--
--....i'
Tested at 800 oC (1472 °P) at strain rates indicated. Specimens were forged at 900 oC (1652 °P) and annealed at 750 oC (1382 °P) for 2 h. Alpha iron has a bodycentered-cubic crystal structure. Composition: Pe0.007C-0.03Mn-0.005S-0.003P
0.1/5
0.01/5 0.001/5
0.1
0.2
0.3 0.4 True pla5tic 5train
0.5
0.6
64/Cast Iron (CI)
CI.075 Gamma (y) iron alloy forging, true compressive stress-strain curves
300
Tested at 950 oC (1742 °P) at strain rates indicated. Specimens were forged at 900 oC (1652 °P) and annealed at 750 oC (1382 °P) for 2 h. Above 910 oC (1670 °P) pure iron has a face-centered-cubic crystal structure and is called gamma iron. Composition: Pe-0.007C-0.03Mn0.005S-0.003P
250
200
//~
i1.
:2
~ 150
U; al
~
100
50
--
Strain rate: ~10.(fS 100/s
Source: O.S. Avadhani, Indian Institute of Science, Bangalore, India. As published in Hot Working Guide, Y.V.R.K. Prasad and S. Sasidhara, Ed., ASM International, 1997, p 267
;;v
V-
1.0/5
1é-~ V 0.1
0.1/5 0.01/5 0.001/5
0.2
0.3
0.5
0.4
0.6
True plastic strain
CI.076 Gamma (y) iron alloy forging, true compressive stress-strain curves
150
120
Strain rate:
V / V" 60
30
-
Tested at 1150 oC (2102 °P) at strain rates indicated. Specimens were forged at 900 oC (1652 °P) and annealed at 750 oC (1382 °P) for 2 h. Above 910 OC (1670 °P) pure iron has a face-centered-cubic crystal structure and is called gamma8 iron. Composition: Pe-0.007C-0.03Mn0.005S-0.003P
V (¡ -
----
- 100/5 1015
Source: O.S. Avadhani, Indian Institute of Science, Bangalore, India. As published in Hot Working Guide, Y.V.R.K. Prasad and S. Sasidhara, Ed., ASM International, 1997, p 267
~ V¿
1.0/5
0.1/5 0.01/5
V"
0.001/5
0.1
0.2
0.4 0.3 True plastic strain
0.5
0.6
Cast Iron (CI)/65
CI.077 Steel preform powder metal forged cylinder, compressive stress-strain curves
Axial compression, %
20
40
60
70
150r---,,---r--~r---'---rr----rr--'----r---.1050
840
630 as a.
90 ~ .;
::¡;; .;
U)
U)
~
~
420
Test direction: longitudinal. Five steel powder compositions used: A, Fe-0.27C-2.0Ni-0.5Mo; N2, Fe0.17C-2.7Ni-0.8Cr; N7, Fe-0.24C-0.6Ni-0.5Cr-0.2Mo; SI, Fe-O.OIC; S3, Fe-0.33C. Preforms compacted to 785 MPa (114 ksi), sintered at 1199 oc (2190 °F), 30 min, and spheroidized (heating three times aboye and below eutectoid point). The sintered and annealed preforms are compared. Source: Source Book on Cold Fonning, American Society for Metals, 1975, p 208
iñ
~~4----+----~---+----+----~--4----+---1210
- - Annealed - - - Sintered
°0~--0~.2----0.~4---0~.6--~0.-8---1~.0--~1.-2---1~.4---1~.6--~1.R Axial strain, in.lin.
CI.078 Steel preform annealed powder metal, comparison of compressive stress-strain curves
r---,,---r--,,----,--T,----rr--,----,-~1050
Test direction: longitudinal. Three annealed powders (A, SI, and S3) are compared to wrought 0.35% C steel and plain iron. Compositions: A, Fe-0.27C-2.0Ni-0.5Mo; SI, Fe-O.OIC; S3, Fe-0.33C
~--4----+----r_--~7S~----+---_r~~--~840
Source: Source Book on Cold Fonning, American Society for Metals, 1975, p 208
630 as a.
.¡¡; -'"
::¡;; .;
.; U)
~
U)
iñ 420
rt~+_---r--_+----r_--+_---r--_+----r___4210
- - Annealed - - - Wrought material
°0L---~0.-2---0~.4~~0~.6---0~.~8---1~.0----1~.2----1L.4---J1.-6--~ 1.R Axial strain. in.lin.
~
Carbon Steel (CS)/67
Carbon Sleel (es) CS.OOl Annealed low-carbon steel, load-elongation curve showing Lüders bands Upperyield point
1 y
x
Laders band
Typieal yield point behavior of low-earbon steel. The slope of the initiallinear portion of the stress-strain curve (E = y/x) is the modulus of elastieity. Many metals, pirrtieularly annealed low-earbon steel, show a loealized, heterogeneous type of transition from elastie to plastie deformation that produces a yield point rather than a curve with a gradual transition from elastie to plastie behavior. The load inereases steadily with elastie strain, then drops suddenly. After the upper yield point, several diserete bands of deformed metal, ealled Lüders bands, appear at stress eoneentrations, usually at about 45° to the tensile axis. Load fluetuates about sorne approximately eonstant value, and then rises with further strain. Source: G.E. Dieter, Mechanical Behavior under Tensile and Compressive Loads, Mechanical Testing and Evaluation, Vol 8, ASM Handbook, ASM Intemational, 2000, p lOO
Unyielded metal
Elongation _ _
CS.002 Carbon steel, various alloys, load-extension curves showing yield strength Load-extension curves for steel sheet having the same yield strength (YS) but different eharaeteristie behavior. (a) Annealed dead soft rirnmed or alurninum-killed steel. The YS is the average stress measured during yield point elongation. (b) Lightly temper rolled rirnmed steel. The stress at the jog in the curve is reported as the YS. (e) and (d) Temper roUed low-earbon steel. May be rirnmed, alurninum-killed, or interstitial-free steel with no detectable yield point. The YS is ealeulated from the load at 0.2% offset (e) or from the load at 0.5% extension (d). (e) Rirnmed steel with a yield point elongation due to aging at room temperature for several months. The YS is the average stress measured during yield point elongation.
I
I I
I I I
I I I I
I I I I I I I I I
I I I I
I
(a)
(b)
0.2%
: (e)
(e)
--11-- ---1 f-- 0.5% extension Extension
Source: W.G. Granzow, Sheet Formability of Steels, Properties and Selection: lrons, Steels, and High-Performance Alloys, Vol 1, ASM Handbook, ASM Intemational, 1990, p 574
68/Carbon Steel (CS)
CS.003 Annealed and normalized low-carbon steel, stress-strain curves showing effects of aging
Strain aged lower yield extension
y is upper yield point, A is point of initial prestrain. Curve 1: specimen is unloaded and immediately restrained. Curve 2: specimen unloaded, aged, and restrained. Aay is the change in yield stress due to aging. Aau is the change in ultimate strength due to aging. Ae is the change in elongation. Similar aging effects can be achieved with various combinations of time and temperature.
t
Source: W.T. Lankford, Jr. et aL. The Making, Shaping, and Treating of Steel, USS, 10th ed., 1985, p 1286
Initiallower yield extension (Lüders strain)
Prestrain
Strain ~
350,----,-----,-----,----,-----,-----,----,
CS.004 Rimmed carbon (0.03 % C) steel, true stress-true plastic strain curves
50
Effect of aging at 60 oC (140 °F): curve 1, no aging; curve 2, 15 min; curve 3,30 min; curve 4,4 h; curve 5, 500 h; 6, 126 h
45
40 .¡¡; ~ 250~--~-----tr_~~~---r----~----t---~ 35""'. :2
g
"'"' ~al
~
Oí al
~ 200~--~--~-tr_---r-----r----~----t---~
30~
25 150r_--~-----tr_---r-----r----~----t---~
20
6
8
True plastic strain, %
10
12
15 14
Source: W.T. Lankford, Jr. et al., The Making, Shaping, and Treating of Steel, USS, 10th ed., 1985, p 1286
Carbon Steel (CS)/69
es.oos Rimmed low-carbon (0.03 % e) steel, engineering stress-strain curves
400
350
- 50 1
300
&. ::;:
250
l,¿f
.;
'" ~ ~ 200
~
Irf ./
--
~
40
~
.;
"
e
~
- 30 ~ e .~ e
./
2
'g> 150 ~ .~
e
';:;,
- 20
w
Curve 1: Dynamic strain aging, also called blue brittleness. Straining at 200 oC (390°F) yields serrated stress-strain curve and is more effective than straining at room temperature. Curve 1 was unloaded and restrained at 25 oC (77 °F). Curve 2 was strained at 25 oC (77 °F) and unloaded, aged for 2 h at 200 oC (390°F), and restrained at 25 oC (77 °F). Souree: W.T. Lankford, Jr. et al., The Making, Shaping, and Treating of Steel, USS, 10th ed., 1985, p 1286
e
W
100
- 10 50
2
3
4
5
7
6
8
9
Strain, 'lo
es.006 1007 and 1008 carbon steel, von Mises effective true stress-von Mises true strain curves
1.50
Curve 1: 1008 alloy deformed by plane-strain compression; data source, Ford. Cunre 2: 1007 alloy deformed by torsion; data source, G. Sevillano. Curve 3: 1007 alloy deformed by wire drawing plus torsion; data source, G. Sevillano. UNS G 10080
1.25
~
1ñ 1.00
~ ..",/
Q)
.5 ~
~ 0.75
'al ~
:iE e
~
0.50
0.25
p.
Ir
~
0.5
V
Souree: G. Krauss, Ed., Deformation, Processing, and Structure, papers presented at the ASM Materials Seienee Seminar, 23 Oet 1982 (St. Louis, MO), American Society for Metals, 1984, p 9
-;;;;;;; ~ '2
1.0
1.5
2.0
2.5
von Mises true strain
3.0
3.5
4.0
70/Carbon Steel (CS)
CS.007 1008 carbon steel, true stress-true strain curves
1000 900
Comparison of stress-strain curves. Curve 1: monotonic plane-strain compression. Curve 2: rolling prestrain followed by plane-strain compression. Stress states are very similar, and yet the rolling-plus-plane-strain compression curve is different. This difference can be explained on the basis of redundant work; the curvature of the roUs causes sorne redundant shearing (not contributing to thickness reduction) and extra hardening. UNS G10080
800 700
rf.
::;:
600
ui
~ 500 1ií ID
~ 400 300
11
~
~
-;::::::::. :::---
1
·f v
Source: G. Krauss, Ed., Deformation, Processing, and Structure, papers presented at the ASM Materials Science Seminar, 23 Oct 1982 (St. Louis, MO), American Society for Meta1s, 1984, p 10
200 100
00
0.25
0.50
0.75 1.00 1.25 True strain, %
1.50
80
/
/
75
compre~
./
70
/,
y
~
,/
/"
1.75
jo"
2.00
-
-
ro
o.. ::;:
g¡ 450 ~ ID
~
-
l'
400
5
500
Niobium-stabilized (+0.02Nb), air cooled from 1200 oc. Widmanstlitten ferrite-pearlite. Composition: Fe-0.17C0.96Mn-0.014P-0.026S-0.040Si-0.044Ni-0.028Cr0.008Mo-0.006AI-0.025Cu-0.020Nb. UNS G10150 Source: G.c. Rauch and w.c. Leslie, The Extent and Nature of
,,"SiOn
1/
55
CS.008 1015 carbon steel, tensile and compressive true stress-plastic strain curves
...
/; /
60
550
10
15 20 Plastic strain x 0.001
25
30
350 35
the Strength-Differentia1 Effect in Stee1s, Metall. Trans., Vol 3, Feb 1972, p 378
Carbon Steel (CS)/71
50
40
I
To
,.J"""
1'-
fraCI~re ~
----~.
V
----
V
350
eS.009 Annealed low-carbon (0.18% e) steel, engineering stress-strain curve
Curve shows a welI-defined yield point. For such cases the 0.2% offset yield strength is not used to define yielding.
280
........-
&.
:::;:
Source: C.R. Brooks, Heat Treatment, Structure, and Properties of Nonferrous Alloys, American Society for Metals, 1982, p 4
210 gf
~
g>
.~
140 .c, ~
"
w
70
10
0.25
0.50
0.75
1.00
1.25
o
1.50
1.75
Engineering slrain, %
80
560
60
420
40
V
~
lIi ~
30
"lE
~
¡.....-¡r'
~
eS.Ol0 Fully aluminum-killed deep-drawing carbon steel 20-gage sheet, logarithmic true stress-strain curve
Test direction: longitudinal. This figure was a typical result from a series of reproducibility tests conducted on 50 adjacent specimens. Linearity is very good. n = 0.250, k= 71.67.
¡...... 280
8:
:::;:
../
210 rñ
~
"lE
ID
ID
::l
F
::l
F 20
10 0.01
140
70 0.02
0.03 0.04
0.06 0.08 0.1
True slrain
0.2
0.3
Source: Source Book on Forming of Steel Sheet, American Society for Metals, 1975,p 217
72/Carbon Steel (CS)
60
,
comptssion , 50
(\
, "
-
1-',,,-
,..-
----
...... ~
-
CS.011 1015 carbon steel, tensile and compressive true stress-total strain curves. UNS G10150
420
r-
Samp1es equiaxed ferrite-pear1ite 350
Source: Metall. Trans., Vol 3, 1972, P 379
k:ion
280
40
o..'"
~
:2
:i
210 ~
~ 30
üí
CIl
CIl
~
~ 20
140
10
70
5
10
15 20 Tolal slrain x 0.001
25
30
CS.012 1020 carbon steel, tensile stress-elongation curves at room and elevated temperatures
r-------------------------------------~630
~--------------~r_------------------~560
Strain rate = 0.000175/s. Composition: Fe-0.20e. UNS Gl0200
~----------~--4_--~----r_----------~490
Source: W.C. Leslie, The Physical Metallurgy of Metals, McGraw-Hill and Hemisphere Publishing, 1981, p 92
ro
~~~~~~_j~_Td_--~--~r_--------~350~
~--~--~--_+--_+----~--~----_?~--~280~'" ~--~--~--_+--_+--~----+_--~------~210
~--~--~--_+--_+--_i--_;----~--~~~140
70
Carbon Steel (CS)/73
/
60 Casi SAE '1030 Monolonic ~
,:
1\
50
g¡
CS.013 1020 wrought and 1030 normalized-andtempered cast carbon steel, monotonic and cyclic stress strain curves
490
70
40
~
V
~
[AE1030 Cyclic
~
en 30
V'
20
The cyc1ic stress-strain characteristics show a reduction of the strain-hardening exponent of the normalized-andtempered cast carbon steel (SAE 1030) from n =0.3 in monotonic tension to n' = 0.13 under cyc1ic-straincontrolled tests. UNS G 10200
350
>L/
280 ~
¡-~ /
uf
420
::;;
210
Source: P.E Wieser, Ed., Steel Castings Handbook, 5th ed., Steel Founders' Society of America, 1980, p 14-15
~
éií
Wroughl SAE 1020 Cyclic 140
70
10
I 2
4
8
6
10 Slrain. 0.001 inJin.
12
14
o
16
CS.014 Hot-rolled 1020 carbon steel, static and dynamic engineering shear stress-strain curves
600 80 500
ro a. ::;;
70
60 400
Ul Ul
50
~ (¡j
O; 300 Ql
Ul
Ol
c:
c:
"55
'c,
Ql
.<::
Ul
el Ql
Ul Ul
~
O;
40
.<::
c:
~
1
-!::.
30
200
c:
'c, c: w
c:
W
20 100 Slalic
O
"aiQl
ID
l'
ce
í
N
N
~ ce
'"
~
~
~
ID ID
'"en
~
Engineering shear slrain, y
10
O
Static and dynamic shear stress-shear strain curves for hot rolled 1020 steel. To obtain the shear strain in the specimen, the elastic rotation of the bar between the two differential transformers is subtracted from the total rotation. This elastic rotatíon is measured by cementing the loading bars together without a specimen and loading them quasi-statically. Typical test results obtained at a variety of temperatures using the Kolsky bar to test 1020 steel at a quasi-static strain rate of 5 x lO-4/s and dynamic strain rate of 103/s are given .. Source: A. Gilat, Torsional Kolsky Bar Testing, Mechanical Testing and Evaluation, Vo18, ASM Handbook, ASM Intemational, 2000, p 513
74/Carbon Steel (CS)
-
80
70 (
/
-
.............
"""-
Ullimale tensile Slrenglt, 77.500 ksi (534 MPa)
60
'\
Fracture slress, 52 ksi (358 MPa) --....
~
I I I
I I I I I I
20
I I I
10 Elongalion al ~raelur~, 19% 0.02
0.04
0.06
0.08 0.10 0.12 Engineering slrain
0.14
0.16
80
70
r-- 0.2% yield llrenglh'
----- ---;;;¡ ~ 66 ksi (455 MPa)
60
I
V
20
10
/ / 1/
I I I
I
",,1
0.18
490
Definitíon of mechanical property tenns
420
Source: c.R. Brooks, Heat Treatment, Structure, and Properties of Nonferrous Alloys, American Society for Metals, 1982, p 2 ro
350 ~
gf ~
280 ro
'"r::
-~
ID
210.§, r::
w 140
70
o
0.20
560
CS.016 Cold-worked carbon (0.2 % C) steel, engineering stress-strain curve (expanded range)
490
Definítion of mechanical property tenns
420
Source: e.R. Brooks, Heat Treatment, Structure, and Properties of Nonferrous Alloys, American Society for Metals, 1982, p 2 ro
n. 350 ::;:
!
!
I
~
280 ~ r::
I
"ai
/
~ I
! 10.2%
ID
r::
210 Slope gives elaslie (Young's) modulus, 30 x 10' psi (207 GPa)
4 6 Engineering slrain, x 0.001
'g> w
140
70
I I 2
CS.015 Cold-worked carbon (0.2% C) steel, engineering stress-strain curve (fuI! range)
560
8
Carbon Steel (CS)/75
120
_....p .....
....
100 /"
f>
80
40
20
::::-,,"
~ I/.,f r¡'
~
...¡.-----........ ........
.""..,.",.-~
~
~
....
t:::==
---
eS.017 AAR grade A and B high-carbon steel casting
840
wheels, stress-strain curves
~
Constant-amplitude strain-controlled test (open circ1es, grade A; "plus" symbols, grade B). Curve 1, monotonic tension test; curve 2, incremental step test. AAR, Association of American Railroads. Compositions: grade A, Fe-0.52C-O.78Mn-O.014S-0.009P-O.26Si; grade B, Fe-O.65C-O. 83Mn-O.038S-0.0 15P-O.21 Si
700
560 C\l
Il.
:2
420
~
)
Source: D.H. Stone and Y.J. Park, Cyclic Plasticity of Class A and B Heat-Treated Wheel Steels. As published in "The General Problem of Rolling Contact," AMD-VoI40, ASME, 1980
280
/
- - Grade A wheel - - - Grade B wheel
140
1/ 0.2
0.4
0.6
1.0
0.8
1.2
1.4
o
1.6
Strain, %
150
Monotonic
125
100
I
#
~c
v---
--:::::::::::
eS.0l8 AAR grade e high-carbon steel casting
1050
wheels, stress-strain curves
~
Monotonic and cyc1ic loading curves. AAR, Association of American Railroads. Composition: Fe-O.68C-O.83MnO.038S-0.015P-0.33Si
875
Source: Courtesy of !be Transportation Technology Center, Inc. subsidiary of Association of American Railroads
700 C\l
Il.
:2
525
f
~
50
350
25
175
0.01
0.02
0.03 Strain
0.04
o
0.05
76/Carbon Sfeel (CS)
140
CS.019 Standard grade nonresulfurized carbon steel rails, stress amplitude-strain amplitude curves
980
11
120
840
I
100
I
Static compression
"-
Incremental steg
BIOCk~ Block 1 .....-:::: ~
I~ ~
700 ro a. ::¡;
~
~ ~ ' " Static tension
..-:: ~
560
=ª
15. 420 E ro
(/)
i
280 en
I
20
o
140
/
0.2
O
0.4
0.6 0.8 1.0 1.2 1.4 Strain amplitude (!l.e/2), %
1.6
1.8
0 2.0
CS.020 High-strength nonresulfurized carbon steel rails, load-extension diagram
Extension, mm
20,000
0
254
508
762
10.16
12.70
17,500
/
15,000
"...---
15.24
17.78
-
-g 10,000
5670
4536
V
.3
3402
/
5000
/
2268
/
1134
0.1
0.2
0.3
-ª' ai
.3
/
7500
Test curve for one specimen 12.751 mm diam x 50.8 mm gage length (0.502 in. diam x 2 in. gage length). Ultimate tensile strength = 1106 MPa (160.5 ksi); 0.2% yield strength = 644 MPa (93.4 ksi). Typical composition for high-strength raíl: Fe-0.74C-0.99Mn-O.005S(max)O.015P-O.17Si
6804
L
,Q
20.32 9072
7938
V
12,500
2500
Source: B.N. Leis, Cyclic Deformation and Fatigue Resistance Characteristics of a Raíl Steel, Rail Steels, STP No. 644, ASTM, Nov 1977
al ""O
jv
40
S
Test direction: longitudinal. Static and incremental step loading. Modulus of elasticity = 199 GPa (28.85 x 106 psi). Composition: Fe-0.82C-0.87Mn-0.032S0.035P-0.21Si
0.4 Extension. in.
0.5
0.6
0.7
o
0.8
Source: Courtesy of the Transportation Technology Center, Inc. subsidiary of Association of American Raílroads
Carbon Steel (CS)/77
100
í
75 -'" ui !I)
-
700
525
ui !I)
350
I
I 4
6
8 10 12 Strain x 0.001
~
14
16
20
CS.022 AAR specification M101 grade e austenitic manganese steel casting, monotonic tensile stressstrain curve
1050
1"
120
840
90
630
Quenched and tempered. Strain rate = 0.0002/s. Ultimate strength = 986 MPa (143 ksi); 0.2% yield strength = 909 MPa (132 ksi); elongation = 19.6%; elastic modulus = 217 OPa (31.474 X 106 psi). AAR, Association of American Railroads. Composition: Fe-0.28C-l.35Mn0.025S-0.012P-0.44Si-0. 17Ni-0.25Cr-0. 17Mo
'00 -'"
ui !I)
¡z
ffl
~
Cií 60
420
I
210
2
4
6
8 10 12 Strain x 0.001
Souree: Courtesy of the Transportation Teehnology Center, Ine. subsidiary of Assoeiation of Ameriean Railroads
o
18
150
30
Normalized and tempered. Strain rate = 0.0002/s. Ultimate strength = 696 MPa (101 ksi); 0.2% yield strength = 605 MPa (87.8 ksi); elongation = 33%; elastic modulus = 204 OPa (29.575 X 106 psi); strain-hardening exponent = 0.097475; strength coefficient = 1059 MPa (153.674 ksi). AAR, Association of American Railroads. Composition: Fe-0.31 C-l.50Mn-0.027S-0.007P-0.49Si0.14Ni-0.20Cr-0.17Mo
175
!
2
a.
::¡;:
/
~
25
~ f.---
¡...-- ~ f--
1/
'00
50
CS.021 AAR specification M101 grade e austenitic manganese steel casting, monotonic tensile stressstrain curve
875
125
14
16
18
o
20
Souree: Courtesy of the Transportation Teehnology Center, Ine. subsidiary of Assoeiation of Ameriean Railroads
78/Carbon Steel (CS)
CS.023 AAR specification M101 grade E austenitic manganese steel casting, monotonic tensile stressstrain curve
875
125
100
I I I
75
~
~
50
25
700
'-
525
c..
::;¡;
~
(J)
350
Quenched and tempered. Strain rate = 0.0002/s. Ultimate strength = 730 MPa (106 ksi); 0.2% yield strength = 655 MPa (95 ksi); elongation = 27.8%; elastic modulus = 210 GPa (30.43 x 106 psi); strain-hardening exponent = 0.93697; strength coefficient = 1086 MPa (157.661 ksi). AAR, Association of American Railroads. Composition: Fe-0.29C-1.03Mn-0.026S-0.0 14P-0.49Si-0.60Ni-0.47Cr0.15Mo Source: Courtesy of the Transportation Technology Center, Ine. subsidiary of Association ofAmerican Railroads
175
1/ 4
2
6
o
8
10
Slrain x 0.001
1500
1400
V
1300
~ 1100
g¡
~ ~ 1000
~
900
800
As-quenched
As-quenched martensite quenched in NaOH-NaCl solution and quenched-and-tempered lath martensite with packet size of 8.2 ~m was tempered in lead at 400 oC (750°F) for 1 mino Work-hardening rate for as-quenched is quite high compared to tempered sample. Composition: Fe-0.2C
1/
1200
el':
---
CS.024 As-quenched and quenched-and-tempered carbon (0.2 % C) steel, true stress-strain curves
-l.
.;..---
/
Quenchedand-Iempered
I Ir I
Souree: T. Swarr and G. Krauss, The Effeet of Strueture on the Deformation of As-Quenehed and Tempered Martensite in an Fe-O.2% C Alloy, Metall. Trans. A, Vol 7A, 1976, P 41-48
700
5
10
15 20 25 True strain x 0.001
30
35
40
Carbon Steel (CS)179
CS.025 Carbon steel, Bauschinger effect on stressstrain curves !l, Bauschinger strain
t
The elastic limit of a metal is lowered after reverse loading. The area Ep is the energy expended in prestrain, and Es is the energy saved in reverse loading. Source: C.-C. Lí, J.D. Flasck, J.A. Yaker, and w.c. Leslie, On Minimizing the Banschinger Effect in Steels by Dynamic Strain Aging, Metall. Trans. A, Jan 1978, p 86
Tension
r----- Prestrain,
Compression
0.2% offset Strain---,
80/Carbon Steel (CS)
80
CS.026 1020 carbon steel, true stress-strain curves
560
70
v- --~
60
/V"
L 50
/ /
Tension
--
~-
v /:
420
350 lO
o..
~
280 ui
'"
~ en
Compression
f¡
30
210
20
140
10
70
0.5
1.0
1.5
2.0
(a) Bauschinger effect shown for test sequence of tension to 2% strain followed by compression of another 2%. (b) The sequence is compression-tension. Tested at 25 oC, Composition: Fe-O.21 C-O.64Mn-O.030S-0.0 18P-O.23SiO.007N. UNS G10200
490
2.5
3.0
3.5
4.0
o
4.5
Slrain, %
(a)
80
560
_... -- --
70
..........
60
I\...
L
I
Compression
30
420
,........-f-
/
50
490
/
350
V
al
o.. ~
280 ui
'" ~
en
Tension
210
11 20
140
10
70
00
0.5 (b)
1.0
1.5
2.0
2.5 Slrain, %
3.0
3.5
4.0
o
4.5
Source: c.-c. Lí, J.D. Flasck, lA. Yaker, and w,c. Leslie, On Minimizing !he Bauschinger Effect in Sleels by Dynamic Strain Aging, Metall. Trans. A, Jan 1978, p 86
Carbon Steel (CS)/81
70
60
;:;
~
50
g¡
!
20
--
/i-
420
350
/
40
en 30
1..--
/
280
/
210
& ::;:
i
Curve 1: specimen is prestrained in tension at 250 oC to 2% strain and tested in compression at room temperature. Curve 2: the specimen is prestrained in tension at room temperature to 2% strain and tested in compression at room temperature. The Bauschinger effect is reduced. Composition: Fe-0.21C-0.64Mn-0.030S-0.018P-0.23Si0.007N. UNS G10200 Source: c.-c. Li, lO. Flasck, J.A. Yaker, and W.C. Leslie, On Minimizing the Bauschinger Effect in Stee1s by Oynamic Strain Aging, Metal/. Trans. A, Jan 1978, p 88
140
1/
70
10
0.5
1.5 Slrain. %
2.5
2
3
o
560
80
.-- --'
70
60
eS.027 1020 carbon steel, true stress-strain curves
490
./
I\.
/
/'
50
/
30
/
20
V
Tension lo 2% al 25 oC
/'
I--~
..... 490
420
V
350
Compression lo 2% al 25 oC 210
140
10
70
0.5
1.0
1.5
'!.O 2.5 3.0 Slrain, 0.001 in./in.
3.5
4.0
o
4.5
eS.028 1035 carbon steel, true stress-strain curves Bauschinger effect shown with test sequence of tension to 2% strain followed by compression of another 2%. Tested at 25 oC. Composition: Fe-0.34C-0.65Mn-0.007S0.003P-0.17Si-0.021AI-0.006N. UNS G10350 Source: c.-c. Li, J.O. Flasck, J.A. Yaker and w.c. Leslie, On Minimizing the Bauschinger Effect in Stee1s by Oynamic Strain Aging, Metal/. Trans. A, Jan 1978, p 86
82/Carbon Steel (CS)
70
¡.-
~
60
50 .¡¡;
-'" 40
li ~
20
ro o.. 280 ::;; oí
~ 210
1/
140
70
1.5 1.0 True strain. %
2.0
1095-283 _ _ 1095-158 200
~~
180
ui
~
120
80 60 40
eS.030 1020, 1040, and 1095 carbon steel plate, true stress-strain curves showing effects of shock loading
1400
1095-0
1260
~~
fP. V
1120
1040-283 980 ro o..
1020-283
::;; 840 ui
1
f
ID
~ 100
o
2.5
1540
220
11>
Minimizing the Bauschinger Effect in Steels by Dynamic Strain Aging, Metal!. Trans. A, Jan 1978, p 88
ID
0.5
~ 140
Curve 1: specimen is prestrained in tension at 250 oC to 2% strain and tested in compression at 25 oC. Curve 2: the specimen is prestrained in tension at 25 oC to 2% strain and tested in compression at 25 oC. Composition: Fe-0.34C-0.65Mn-0.007S-0.003P-0.17Si-0.021Al0.006N. UNS Gl0350 Source: C.-c. Li, J.D. Flasck, J.A. Yaker and w,c. Leslie, On
~
10
160
420
350
/
ID
~ 30
/
/
~
Y
¡.~ V
eS.029 1035 carbon steel, true stress-strain curves
490
f/
10~0-158 ./
V/
1040-158
v-: ~ V
¡---
700
1040-0
560 1020-0
V...,.... J...---
280
r- - -O - - -158 - - -1283
20
0.02
0.04
420
=Unshocked =158 kbar shock =283 ~bar shock
0.06 Strain, in.lin.
0.08
0.10
140
o
0.12
i
ID
~
Preshock normalizing: 1020, 927 oC (1700 °F), 45 min; 1040,899 oC (1650 °F), 45 min; 1095,899 oC (1650 °F), 45 min, austenitizing 802 oC (1475 °F), 45 min, oil quenched, tempered 204 oC (400°F), 1 h. Shocked at 158 and 283 kbar (peak) .. UNS G10200, G10400, Gl0950 Source: B.G. Koepke, R.P. Jewett, W.T. Chandler, and TE. Scott, Effects of Initial Microstructure and Shock Method on the Shock Induced Transformation Strengthening of Carbon Steels, Metal/. Trans., Vo12, ASM, 1971, P 2045
Carbon Steel (CS)/83
(a) Longitudinal. (b) Transverse. Composition: O.23C0.39Mn-O.009P-O.024S-0.03Si-O.02Cr-O.OlNi-O.OlMo. UNS G10230
420
60
~
/ 20
CS.031 1023 carbon steel sheet, tensile stress-strain curves
560
80
-
Source: Structural Alloys Handbook, Vol 1, Battelle Columbus Laboratories, Columbus, OH, 1980, P 28
rf.
:2: 280 rñ
~
/
140
4
8
12 16 Strain, 0.001 in.lin.
20
(a) 80
560
60
420
/'
20
¡.....---
~
I
140
4 (b)
al
a.
:2: 280 rñ
8
16 12 Strain, 0.001 in.lin.
20
84/Carbon Steel (CS)
;;
100
~ ~
80
~ ~-
~
r---
¿ '" 2.5/8 """- 12
"""-
1.1
- 10
r-......
~'-
o
"'"
-
0.14
8
0.035
-0.017 0.0069
1U) U)
Temperature (n = 1100 oC (2012 °P). Stress-strain curves show that at higher strains the flow stress is approximately constant. This is increasingly true at smaller strain rates (e). Curves were obtained in hot torsion experiments. UNS GI0250 Source: K. Lange, Ed., Handbook of Metal Forming, McGraw-Hill, 1985, p 16.11
~
0.065 6
~ u:
0.0037 0.0020 0.0011/8
0.5
O
'00
0.40
~
20
CS.032 1025 carbon (0.25 % C) steel, flow stress-strain curves at various strain rates
14
1.5
1.0
2.0
2.5
-
4
-
2
O
Natural strain (8), %
800
'" :2 a.
:i
CS.033 1040 carbon steel, engineering stress-strain curves with effect of strain rate
_.
1000
/: ~ ',./ /¿,
V
........
"'
Effect of different strain rates on the tensile response. The yield stress and flow stresses at different values of strain increase with strain rateo The work-hardening rate (m), on the other hand, is not as sensitive to strain rateo This illustrates the importance of correctly specifying the strain rate when giving the yield stress of a metal. Not all metals exhibit a high strain-rate sensitivity. Alurninum and some of its alloys have either O or -m. In general, m varíes between 0.02 and 0.2 for homologous temperatures between O and 0.9 (90% of melting point in K). Therefore, one would have, at the most, an increase of 15% in the yield stress by doubling the strain rateo UNS G10400
-~
~ "'<
600
l'!
V;
el
c
'55
.~ 400 el C
=10-1/5 " =10-'/5 3 1Í3 =10- /5 IÍ,
W
200
Source: M.A. Meyers and K.K. Chawla, Mechanical Metallurgy: PrincipIes and Applications, Prentice-Hall, 1984, p 572
0.02
0.04
0.06 Engineering strain
0.08
0.10
0.12
Carbon Steel (CS)/85
CS.034 1045 carbon steel, flow stress-natural strain curves
400 r-----,------,------,-----,------,------, 2800
2100
300
as
o..
'00
:::¡;
""
Ul
1400 ~
~ 200 Ul
1ií
S: o ¡¡:
~ ¡¡:
100
Strain-rate hardening for 1045 steels with different treatments. Curve 1: quenched and spheroidized. Curve 2: as roUed. Curve 3: quenched and tempered. For most of the curve the relationship is linear. The greater the initial hardness, the greater the rate of strain hardening throughout the range of possible deformation. UNS G10450 Source: J.v. Russell, Steels for Cold Forrning, Sourcebook on Cold Forming, American Society of Metals, 1975, p 106
700
0.5
1.5
2
2.5
Natural strain (In Aa/A)
CS.035 10846 carbon steel, true stress-plastic strain curves in tension and compression
26or----,-----,-----,-----,----,-----,-----,182o
Curves for lower, intermediate, and upper bainite in AISI lOB46 steel. Composition: Fe-O.44C-l.OOMn-O.025PO.026S-0.27Si-O.05Ni-O.08Cr-O.OlMo-O.OlCu-O.0013B
240r---~-----f-----t-----r----~----~--__11680
Source: a.c. Rauch and W.C. Leslie, The Extent and Nature of the Strength-Differential Effect in Steels, Metall. Trans. A, Feb 1972, p 377
~
200
o
1+'-'F-7""--"j~--__+-----t-----+-----+-----+---___11400 ~
~
i
~
~
400 oc
~ 180
1ií
1260 !g
160 I"-A:tr""-i-----f-----t-----+-----~__:=n---__11120 450°C 140~--~--~~~--~--~~-----+-----+---___1980
1200~--~5~---1~0~--~1~5----~2~0----~25~---3~0~--~35~0 Plastic strain x 0.001
.=
86/Carbon Steel (CS)
CS.036 1060 carbon steel rod, true stress-strain curves
300 275 250 225 200
/
ro
~ 175 150
::J ¡::" 125
100 75 50
---
//
Rod diameter = 5.6 mm (0.22 in.). Flow curves for steel compres sed at 780 °e at various strain rates. Letters A, B, e, and D represent the interruption strains used in the experiments. eomposition: 0.68% e. UNS G 10600
1.0/s
Source: R.A.P. Djaic and J.J. Jonas, Recrystallization of High Carbon Steel between Intervals of High Temperature Deformation, Metall. Trans. A, Feb 1973, p 622
............
./"'
1//
'" ~
V
/'
..........
/
0.1/s
.".-- -.......
f/
0.01/s
..........
//B
e
3
D
1.3 x 10 /s
lIlA 11
25 0.1
0.2
0.3
0.6
0.4 0.5 True strain, %
0.7
----
S7
r-',
60
""
iií
--"
40
20
V
,
1
e+ T
I I 1
V
_ .Q~9!OX
DualPhas~ -.....
I
.¡¡;
CS.037 Carbon and high-strength low-alloy (HSLA) steels (SAE 950X, SAE 980X, and GM 980X), stress-strain curves
700
100
80
0.8
SAE950X
\
-,\
-'\"
560
Dual phase plus
420
"\
rí?
::;:
:i ~
~
~
280
140
30 20 10 Strain in 2 in. (50 mm) gage lenglh, %
iií
The GM 980X has been intercritically annealed and dualphase microstructures produced. The two dashed ellipses indicate reported ranges of elongation for dual-phase steels. The basis for three stages in the development of ferritic low-carbon steels is shown. The lower stressstrain curve represents the deformation behavior of mild steel with ferrite-pearlite microstructures. The yielding is discontinuous and yield strengths are typically 30 ksi (207 MPa). SAE 950X and SAE 980X are HSLA steels with yield strengths of 50 ksi (345 MPa) and 80 ksi (562 MPa), respectively. The microstructures still consist of ferrite and pearlite, but the ferrite grain size is highly refined because of controlled rolling and microalloying with vanadium. GM 980X is similar to SAE 980X, but has been intercritically annealed to convert the pearlite to martensite. The resulting microstructure is termed "dual phase" to distinguish the ferrite-martensite microstructure from the ferrite-pearlite microstructure of conventionally treated mild steels of HSLA steels. Source: G. Krauss, Principies of Heat Treatment of Steel, American Society for Metals, 1980, p 242
Carbon Steel (CS)/87
160
140
V /'
120
'00 100
-'"
:g: "'"'~
80
Oí
~"
60
40
/
f r;
~
V ~ ~9\S
V
/'
1120
CS.038 1112 carbon steel, true stress-strain curves with effect of strain rate
980
True stress-strain curves for 1112 steel at different strain rates at 21°C (70 °P). When metals are tested in tension at different strain rates, the flow stress corresponding to a given strain is found to increase with strain rateo The following equation is frequently used to relate flow stress and strain rate at a given strain and temperature: a = al ¿ID, where ¿ = dfldt and al and m are material constants. The exponent m (strain-rate sensitivity) is found to increase with temperature, especially aboye the strain recrystallization temperature. In the hot-working region, metals tend to approach the behavior of a Newtonian liquid for which m = 1.
840
700 ~ ::;
~
]: 560 g¡
~
"
420 ~
280
Source: M.C. Shaw, Metal Cutting Principies, Clarendon Press, Oxford, 1984, p 69 20
140
0.2
0.6
0.4
0.8
O
1.0
1.2
True strain, "
150
CS.039 1112 carbon steel, relationship of engineering, true, and corrected stress-strain curves
1050
J
Ultimate [tress X Fracture stress
100
~ ui
"' ~
t
50
~r::
~
V
V 700
j.A< d
'"
ca¡l'ec\e
c..
::; ui
"'~
iií
.ro..
Engineering
If
o
O
""'"
0.2
0.4
0.6
0.8 Strain
1.0
1.2
350
O 1.4
Re1ationship between engineering, true, and corrected tensile stress-strain curves for AISI 1112 steel. The figure aboye shows the relationship between the so-called engineering stress-strain curve based on the original area, the true stress-strain curve, and the corrected true stressstrain curve where the stress plotted (ac) is the uniaxial tensile stress in the absence of the hydrostatic component introduced by curvature of the neck. It is evident that interpretation of tensile test results is really quite involved despite the apparent simplicity of the test. Source: M.e. Shaw, Metal Cutting Principies, Clarendon Press, Oxford, 1984, p 67
88/Carbon Steel (CS)
8oo,-----,------,------,-----,------,-----,
600~~--~--~~------~----~-----t----~
CS.040 Carbon steel, true stress-strain curves showing effect of different cooling rates Specimens annealed at 810 oC, 10 mino Cooling rate: curve A, 1000 oC/s; curve B, 300 oC/s; curve C, 60 oC/s; curve D, 32 oC/s; curve E, 5 oC/s. Composition: Fe0.063C-l.29Mn-0.24Si Source: G. Krauss, Ed., Deformation, Processing, and Structure, papers presented at the ASM Materials Science Seminar, 23 Oct 1982 (St. Louis, MO); American Society for Metals, 1984, p 70
'"
Il.
::;;:
:i
~ 400~~--~?6~-+------~----~-----+----~
~"
200~----~-----t------~----~-----t----~
f::,.
True uniform strain
°0L-----OJ.0~4----~~--~~--~OJ.1~6----~0.~20~--~0~.24
True strain
800
Fe-13Mn-1.2C '" 600
.' '" ~
Fe-21 Ni-1.0C"".
'"
::;;:
.,.,#
400
I b
.,' / " ,,.,# .".'tt'
#
./'
,/'
~/
/""
",,/
.' ~'"
.~ ,," .'
.' .'.'
",'"
'
Il.
J-
,.#
.'. ~ '"
~ .'
/
~ Co~33Ni-0.02C
k.F'" 0.05
0.10
..
0.15
0.20
0.25
Tested at room temperature. Plate thickness = 6.35 mm (0.25 in.). Comparison of work-hardening curve of Hadfield steel (Fe-13Mn-l.2C) with that of austenites deformed by slip (Fe-21Ni-1.0C) or twinning (Co-33Ni0.02C). The three have the same yield strength and similar deformation below strain of 0.05 . Source: F. Maratray, High Carbon Manganese Austenitic Stee/s, International Manganese Institute, Paris, 1995, p 28
,.,',,/'"
200
CS.041 Carbon steel plate, true tensile stress (O') minus yield stress (O') versus true plastic strain (E) curves at room temperature
0.30
Carbon Steel (CS)/89
2500
True
2000
ro :2 !Ji
1000
500
~
/
/ ¡.........
V
1/
1500
a.
'" ~
CS.042 A128-E2 carbon steel bar, true and engineering tensile stress-strain curves
- 350
300
-
250
-
200 ~
g¡
Engineering
......
_...
- ------1---,
---
Molybdenum-modified Hadfield steel heat treated 1030--1040 oC, for 1 h. Engineering curve is drawn to fracture. True curve drawn to uniform strain at maximum load. Composition: Fe-12.5Mn-2.0 lMo-1.15C-0. 73Si0.33Cr
-
-=
150
-
100
-
50
~
Source: J.F. Chinella, Mechanical Properties and Microstructure of Thermomechanically Processed, High Manganese Steel, High Manganese High Nitrogen Austenitic Steels, Conf. ProC., ASM International, 1992, p 145
."..'"
0.2
0.4
0.6
0.8
o
1.0
Strain
CS.043 A128-E2 carbon steel bar, engineering tensile stress-strain curves showing effect of thermomechanical treatment
2000r---------~--------~--------~------__,
1.00
. . . . . . . . . .~~ ~======:..
0.75
Ir"'--- ___ -~---t'""'\0~6
- 250
1500 H;ril----~----=:b_""""''-----+-----+-------1 - 200 ro
~.
w
~
~
e
¡
~
a Ji
~ 00
i 1000~----r-----r-----r------4-150 ~ e Ie 500~----~----~----~-----4
- 50
°0L---------OL.l---------0L.2---------0L.3---------lo.1 Engineering strain
!
100 w
Molybdenum-modified Hadfield steel heat treated 1030--1040 oC, for 1 h. Thermomechanical treatment (TMT) at 454 oC. 1.00, 0.75, 0.46 are the effective strains, corresponding to 61, 50, and 35% thickness reduction. Strength increased with increased effective strain, but uniform strain in tension decreased. Composition: Fe-12.5Mn-2.01Mo-l.15C-0.73Si-0.33Cr Source: lF. Chinella, Mechanical Properties and Microstructure of Thermomechanically Processed, High Manganese Steel, High Manganese High Nitrogen Austenitic Steels, Conf. ProC., ASM Intemational, 1992, p 148
90/Carbon Steel (CS)
CS.044 A 128-E2 carbon steel bar, engineering tensile stress-strain curves showing effect of thermomechanical treatment
- 200
~
:::!:
W
W
~
!c:
~
~
1000 H----+----+---t----+----+----j- 150
¡
Q)
i
.TI
-
100
!c: Ic:
~
UJ
Molybdenum-modified Hadfield steel heat treated 1030-1040 oC, for 1 h. Therrnomechanical treatment (TMT) at similar effective strains at the temperatures noted. Thickness reduction at 343 oC, 49%; at 399 oC, 48%, at 454 oC, 50%. Temperature had little effect on strength, but uniforrn strain increased with temperature. Composition: Pe-12.5Mn-2.01Mo-l.15C-0.73Si-0.33Cr Source: lE Chinella, Mechanical Properties and Microstructure of Thennomechanically Processed, High Manganese Steel, High Manganese High Nitrogen Austenitic Steels, Conf. Proc., ASM Intemational, 1992, p 148
500~--4---_+---~--4---_+--~
- 50
°OL---O~.0~5---0~.1-0--~O.L15~--O~.2~O----~O~.2~5----~O.3g Engineering slrain
600r--------------------------------------,
CS.045 Fe-O.08C-l.45Mn-O.21 Si carbon steel, engineering stress-strain curves showing effect of aging
500~-----~~-~~--------~~
Cold-rolled 50% and intercritically annealed 760 oC, 2 min, water quenched, aged at 120 oC (248 °P) for the times given. Yield strength and discontinuous yielding increase with aging time.
~ 400~-~_.~-_?--~-_I--~-~-~~
:::!:
Source: G. Krauss, Steels: Heat Treatment and Processing PrincipIes, ASM Intemational, 1990, p 130
li
~
~300~~-+---?-~~-~--~--~-~~c:
"lB Q)
c: '0>
~ 200~-~~-~-~~-~--~-~--_1--
o
0.5
5
10
22
40
88
112 h
OUL--~----~--~----~--~L----L---J--~
Engineering slrain, %
Carbon Steel (CS)/91
80
CS.046 1522 carbon steel, true stress-strain curves
560
70
*
¡--_.
Bauschinger effect shown with test sequence of tension to 2% strain followed by compression of another 2%. Tested at 25 oC. Composition: Fe-0.21C-1.lOMn-0.016S0.011P-0.05Si-0.007 AI-0.004N. UNS G 15220
490
****** 60
/'"
.........
'\.. ¡ - -
/
50
V
350 ro
V I
1/
Tension to 2% at25 oc 30
420
o..
::
Source: c.-c. Li, J.O. Flasck, J.A. Yaker, and W.C. Leslie, On Minimizing the Bauschinger Effect in Steels by Oynamic Strain Aging, Metal/. Trans. A, Jan 1978, p 87
280 ~ tí
Compression 2% at25°c
Q)
2
210 1-
11 20
140
10
70
0.5
1.0
1.5
2.0
2.5
3.0
3.5
4.0
0 4.5
True strain, %
80
70
60
50
'" CI)
~ 40 Q)
~
30
20
CS.047 1522 carbon steel, true stress-strain curves
560
/
.J~ V/ ~
1/ /1
~
¡-
~
490
420
350 ro
V
o..
::
280
.,
2 210 1-
r/
140
10
70
0.5
g¡ -5;
1.0
1.5
True strain, %
2.0
o
2.5
Curve 1: specimen is prestrained in tension at 250 oC to 2% strain and tested in compression at room temperature. Curve 2: the specimen is prestrained in tension at 25 oC to 2% strain and tested in compression at room temperature. The Bauschinger effect is reduced. Composition: Fe-0.21C-1.lOMn-0.016S-0.011P-0.05Si0.007AI-0.004N. UNS G15220 Source: c.-c. Li, J.O. Flasck, J.A. Yaker, and w.c. Leslie, On Minimizing the Bauschinger Effect in Steels by Oynamic Strain Aging, Metal/. Trans. A, Jan 1978, p 88
92/Carbon Steel (CS)
420 0.24
560
True stress at 0.2 true strain ("0.2)' MPa 700 640 980 1120
1260
Variations in strain-hardening exponents (n) for various plain carbon (lOxx) and molybdenum alloy (4xxx) coldforming steels. 5140 is a chromium alloy and 8640 is a Ni-Cr-Mo alloy steel.
,"4023 0.22
o:: 0.20
-E Q)
e
O
~ 0.18
Q)
C>
·ce
1018_
\
~030 1040
J.
'"
"E 0.16 ro ..c: e
.~
en
Source: R.R. Crawford, R.G. Dunn, J.H. Humphrey, Influence of Alloying Elements on the Cold Deformation of Steel, Sourcebook on Cold Forming, American Society of Metals, 1975, p 142
4f1~ 4027-
4440~
- 5140
~
1340
4140-~640
0.14
4340
1041-"-...
0.12 - 3140 60
80
CS.048 Various carbon steels, strain-hardening exponent versus true stress curve at 0.2 true strain
140 160 100 120 True stress at 0.2 true strain ("0.2)' ksi
180
Alloy Steel (AS)/93
Alloy Steel (AS) 300
200
-'"
rñ
'"~
é'ií 150
100
50
V
/
250
.¡¡;
AS.OO1 52100 chromium alloy steel rod, tensile stress-strain curve
2450
350
V
V
0.2
/
V
/
V
-
Heat treatment: 835 oC (1535 °F), oil quenched and tempered 160 oC (320°F), 20 mino Hardness = 65 HRC. Composition: Fe-1C-1.45Cr. UNS G52986
2100
1750
/
14008:. ~
g¡
Source: G. Sachs. R. Sell, and w.F. Brown, Jr., Tension, Compression and Fatigue Properties of Several Steels for Aircraft Bearing Applications, Proc. ASTM, Vol 59, 1959. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1207, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 5
~
1050 é'ií
700
350
OA
0.6
1.0
0.8
o
1.2
Strain, %
250
1750
200
150
~ rñ
"'
~
100
50
/
V
/
0.2
/ /
/
V
/
V
1050
ca
a. ~
ui
'"
700
0.6 Strain, %
Heat treatment: 835 oC (1535 °F), oil quenched and tempered 160 oC (320°F), 0.5 h, 274 oC (525°F), 1 h. Hardness = 58 HRC. Composition: Fe-1C-1.45Cr. UNS G52986
1400
350
OA
AS.002 52100 chromium alloy steel rod, compressive stress-strain curve
0.8
o
1.0
~
Source: G. Sachs, R. Sell, and W.F. Brown, Jr., Tension, Compression and Fatigue Properties of Several Steels for Aircraft Bearing Applications, Proc. ASTM, Vol 59, 1959. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1207, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 6
94/Alloy Steel (AS)
8or----r----,----,----,----,----,-----r---~560
AS.003 2.25Cr-1 Mo annealed chromiummolybdenum alloy steel plate, tensile stress-strain curves at room and elevated temperatures
420
~ ~ gf 40 1-__--ur-__+----=-1'=-__--t-_--t_ _1_O,50,"_F-.-:(_56_6,"_C'--)--1 280 :-
~
~
Test direction: longitudinal. ASME SA-387 grade D plateo Test specimens machined from 25.4 mm (1 in.) thick plateo Specimens 6.40 mm diam x 50.8 mm gage length (0.252 in. diam x 2 in. gage length). Nominal strain rate = O.Ol/min. Mill composition: Fe-0.12C2.19Cr-0.93Mo-0.46Mn-0.24Si-0.0 14P-0.014S Source: l.E. Bynum, EY. Ellis, and B.W. Roberts, Tensile and Creep Properties for an Annealed Versus Normalized and Tempered 2!1.i-lMo Steel Plate, Chrome Moly Steel in 1976, The American Society of Mechanical Engineers, 1976, p 5
1200"F (649 OC) 20~~-+--+---+--+----t--~--~-~140
°0~---0.~01----0.~02----0~.0-3---0~.0-4---0~.0-5---0~.0-6---0-.0~7---0~.oR Strain, in./in.
80
~75 "F (~02 OC) "-
750"F(399~
~e~
60
AS.004 2.25Cr-1 Mo normalized-and-tempered chromium-molybdenum alloy steel plate, tensile stress-strain curves at room and elevated temperatures
560
~
~ """ ~
-::-:.. .1 70"F (21 OC) I
900 "F (482 OC)
~
420
1;V ,.--
1050 "F (566 OC) ca
c..
::¡;
280 <ñ
~
I(
iií 1200"F (649 OC) 140
20
0.01
0.02
0.03
0.04 Strain, in./in.
0.05
0.06
0.07
Test direction: longitudinal. ASME SA-387 grade D plateo Test specimens machined from 25.4 mm (1 in.) thick plateo Specimens 6.40 mm diam x 50.8 mm gage length (0.252 in. diam x 2 in. gage length). Nominal strain rate = O.Ol/min. MilI composition: Fe-O.l2C2. 19Cr-0.93Mo-0.46Mn-0.24Si-0.0 14P-0.014S Source: l.E. Bynum, EV. Ellis, and B.W. Roberts, Tensile and Creep Properties for an Annealed Versus Normalized and Tempered 2!1.i-1Mo Steel Plate, Chrome Moly Steel in 1976, The American Society of Mechanical Engineers, 1976, p 5
Alloy Steel (AS)/95
200~----.------'------r-----'------'------'
1400
200
1400
180~----~-----+------+------r-----+----~
1260
180
1260
160~----4------+----~~--~~
1120
160
1120
980
140
980
120
840 ro
100
::¡: 700 rñ
120~----4-----~~~~f-~--~-----+----~
840
~
t\l
Il.
.¡¡;
.,
""~
::¡: ~1001------4----f~L-----~~~~~~~~~~ 700 rñ
~
560
~
~
Il.
., ~
560
80 1000 °F (538 OC)
420
60
280
40
280
140
20
140
1i
00
2
4
6
(b)
8
iií
420
10
O
12
Slrain, 0.001 in.lin.
,-----,------,------,-----,------,------,14oo r-----~-----+------+------r--~~~~~1260
r-----~-----+------t7~~~~---+~--~1120
980 r-----4-----_+-,~~~----4_-----+----~840
8'..
r-____4-____~'-7I-'----t:-:~""""+8c:.00.::.......:.°F-'("'42=r7-o..:.C!...)__--1 700 : r-____4-__~~~--~~---=~9~00~O~F~(4~8~2~O~C)~~560
~
r-----,.~~~------r-----4_-----+----~420
1000 °F (538 OC) ~--~~~~~------r------r-----+------4280
r-~~4_----_+------r-----4_-----+----~140
L-----~----~4------6L-----~8------1~0----~1i
Slrain, 0.001 in.lin.
AS.005 4130 chromium-molybdenum alloy steel sheet, tensile stress-strain curves at room and elevated temperatures
Test direction: longitudinal. Sheet thickness = 1.626 mm (0.064 in.). Families of curves for different heat treatments. Left, 857 oC (1575 °F), oil quenched and tempered 538 oC (1000 °F); nominal strength = 1034 MPa (150 ksi). Center, 857 oC (1575 °F), oil quenched and tempered 443 oC (830°F); nominal strength = 1241 MPa (180 ksi). Right, 857 oC (1575 °F), oil quenched and tempered 399 oC (750 °F); nominal strength = 1379 MPa (200 ksi). Specimens were held at temperature for 0.5-100 h. Composition: Fe-0.3C-0.95Cr-0.2Mo. UNS 041300 Source: J.V. Melonas and J.R. Kattus, "Deterrnination of Tensile, Compressive, Bearing, and Shear Properties of Ferrous and Non-Ferrous Structural Sheet Metals at Elevated Temperatures;' WADC TR56-340, ASTIA Document No. AD 131 069, Southem Research Institute, Sept 1957. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1201, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 29
96/Alloy Sfeel (AS)
1400
200
1400
180r-----+-----~----~----_+----~----~ 1260
180
1260
160 f------t------j----f-:b_-t4-
1120
160
1120
980
140
980
120
840
200r-----~----,_----_r----_,----_,----~
120f------+-----~~~~~--_+----_+----~ 840
"
o.
:;;
700 <ñ
'"
560
~
.¡¡;
:;; 700 <ñ
¡i 100
'"
~
Iií 80
560
60f------~~~~----~----_+----_4----~
420
60
420
40f----~~----+----~----_+----_4----~
280
40
280
140
20
140
2 (a)
4
6 8 Strain, 0.001 in.!in.
O 12
10
"
o.
.>:
00
4
2 (b)
6 8 Strain, 0.001 in.!in.
10
~
O 12
1680
240 75"F (24 "C)
220
1540
200
1400
180
1260
160
1120
._ 140
¡i 120
980 o. " :;; 840 ¡i
Iií
700 (/)
'"
.>:
~
~
100 80
560
60
420
40
280 140 4
6 8 Strain, 0.001 in.!in.
10
0 12
AS.006 4130 chromium-molybdenum alloy steel sheet, compressive stress-strain curves at room and elevated temperatures
Test direction: longitudinal. Sheet thickness = 1.626 mm (0.064 in.). Families of curves for different heat treatments. Left, 857 oC (1575 °F), oil quenched and tempered 538 oC (1000 °F); nominal strength = 1034 MPa (150 ksi). Center, 857 oC (1575 °F), oil quenched and tempered 443 oC (830°F); nominal strength = 1241 MPa (180 ksi). Right, 857 oC (1575 °F), oil quenched and tempered 399 oC (750 °F); nominal strength = 1379 MPa (200 ksi), Specimens were held at temperature for 0.5-100 h. Composition: Fe-0.3C-0.95Cr-0.2Mo. UNS G41300 Source: J.v. Melonas and J.R. Kattus, "Determination of Tensile, Compressive, Bearing, and Shear Properties of Ferrous and Non-Ferrous Structural Sheet Metals at Elevated Temperatures," WADC TR56-340, ASTIA Document No. AD 131 069, Southern Research Institute, Sept 1957. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1201, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 33
Alloy Steel (AS)/97
-
150
150
r ~
150
1-----"\
gf 150
1050
X
0.5 h
1050 200°F (93°C) 1050
~
/'
150
:2
1050 gf
:\:
......
150
150
'"
a.
V-- ",0.5h
;r
AS.007 4130 chromium-molybdenum alloy steel sheet, stress-strain curves (full range) at various exposure times to elevated temperatures
75°F (k4 OC)
100 h
~
iií
\
400°F (204 OC)
~
1050 iií
)( 100 h
- -
,,\.5h
..........,
/'
Hot roUed and normalized, austenitized 857 oC (1575 °F), oil quenched, tempered at 538 oC (1000 °F) for 1034 MPa (150 ksi) ultimate tensile strength. Composition of heat: Fe-0.31 C-0.50Mn-0.014P-0.015S0.92Cr-0.19Mo. UNS G41300 Source: J.Y. Melonas and J.R. Kattus, "Detennination ofTensile, Compressive, Bearing, and Shear Properties of Ferrous and NonFerrous Structural Sheet Metals at Elevated Temperatures," WADC TR56-340, ASTIA Document No. AD 131 069, Southem Research Institute, Sept 1957. As published in Structural Alloys Handbook, Vol 1, CINDAS/Purdue University, 1994, p 22
1050 600°F (316 OC) 1050
["xl00 h
f
-.-2S
~0.05~
li5
Strain, in.lin.
175
1225
\~
150
1050 200°F (93°C)
..-0.5\
175
AS.008 4130 chromium-molybdenum alloy steel sheet, stress-strain curves (full range) at various exposure times to elevated temperatures
75°F (k4 OC)
"\
r""""\
1225
100h~
'"
a.
400°F 204°C)
:2
1400 gf
, ""--0.5
~
"---1\
\
/
\
100 h
1225 iií
1*
600°F 316 OC) 175 ,;'
150
0.5
~
/
100 h
1225
~
1050
\, f
25
..... 0.05~ Strain, in.lin.
H5
Hot roUed and normalized, austenitized 857 oC (1575 °F), oil quenched, tempered at 443 oC (830°F) for 1241 MPa (180 ksi) ultimate tensile strength . Composition of heat: Fe-0.31 C-0.50Mn-0.014P-0.015S0.92Cr-0.19Mo. UNS G41300 Source: J.Y. Melonas and J.R. Kattus, "Deterrnination of Tensile, Compressive, Bearing, and Shear Properties of Ferrous and NonFerrous Structural Sheet Metals at Elevated Temperatures," WADC TR56-340, ASTIA Document No. AD 131 069, Southem Research Institute, Sept 1957. As published in Structural Alloys Handbook, Vol 1, CINDAS/Purdue University, 1994, p 24
98/Alloy Steel (AS)
Compressive tangent modulus, GPa 70 105 140 175 210
35
180
-
160
--
_
100
'~ ....
ii5 80
......
60
~
-...
180
....
160
600 °F (316 oC)
840
C\l
a.
----
::;:
~
700 vi
"'~ en~"'
600 °F 1(316 OC)
900 °F (482 oC)
I-=:--°9~
r--+-....
100 80
(a)
15
60
25
30
-..........
1260 1120
-........::
..............
980 ro
a. ::;:
~
840 vi
"'"
700
~
en
560
r---..
420
1--r-
280
20
1400
...............
~
28~680 1540
o~ (204 OC)
............
900 °F (482 oC
420
40
10
400
-..............
120
800 °F 1(427 oC)
20
-..............
800 °F (427
ii5
560
r-- r---.
140
'00
-'" vi
245
200 °F (93 oC)
980
140
5
--
200 1120
1000°F(5~ 1'-.......
40
Compressive tangent modulus, GPa 70 105 140 175 210
35
75 °F 1(24 oC)
200 °F (93 oC
'-
o
220
1260
~~OC
120
~
240
75 °F (21 oC)
140
:i
------:: --- --
245
280
1000°F(538°~
140
20 10
5
35
Compressive tangent modulus, 106 psi
15
20
25
30
35
Compressive tangent modulus, 106 psi (b) Compressive tangent modulus, GPa 70 105 140 175 210
35
75
220 200
~
180 160 -600 °F (316 '00
-'" vi
"'~
ii5
_
o~
200
1540
lF (93 oC
1400 1260
~
80~ °F (~I°C)
120 90d °F
100 80
1~00
40
........
r-............
..........
60
--
1120
~o °F (204 OC)
"'-
(482Io~ ...............
°F (538 OC)
28~680
(24 OC)
1 'K
140
245
" ¡-............. '---
...............
F:::::::r--...
980 ro
a. ::;:
--.....
840 vi 700
...."
~
en
560
r-......
420 280 140
20
5
10
15
20
25
30
35
Compressive tangent modulus, 106 psi (e)
AS.009 4130 chromium-molybdenum alloy steel sheet, compressive tangent modulus curves at room and elevated temperatures
Test direetion: longitudinal. Sheet thiekness = 1.626 mm (0.064 in.). Pamilies of curves for different heat treatments. (a) 857 oC (1575 °P), oil quenehed and tempered 538 oC (1000 °P); nominal strength = 1034 MPa (150 ksi). (b) 857 oC (1575 °P), oi1 quenehed and tempered 443 oC (830 °P); nominal strength = 1241 MPa (180 ksi). (e) 857°C (1575 °P), oi1 quenehed and tempered 399 oC (750 °P); nominal strength = 1379 MPa (200 ksi). Speeimens were he1d at temperature for 0.5-100 h. Composition: Pe-0.3C-0.95Cr-0.2Mo. UNS G41300 Source: J.v. Melonas and J.R. Kattus, "Determinatiou of Tensile, Compressive, Bearing, and Shear Properties of Ferrous and Non-Ferrous Structural Sheet Metals at Elevated Temperatures," WADC TR56-340, ASTIA Document No. AD 131 069, Southern Research Institute, Sept 1957. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1201, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 44
Alloy Steel (AS)/99
AS.010 4130 chromium-molybdenum alloy steel sheet, compressive stress-strain curves at various elevated temperatures
~---r----,---~----'----'-----r----,----,700
Sheet thickness = 1.575 mm (0.062 in.). Reat treated for 862 MPa (125 ksi) nominal tensile strength. Strain rate = O.Ol/min. Composition of heat: Fe-0.30C-0.60Mn0.019P-0.034S-1.05Cr-0.20Mo. UNS G41300 420
ro
a.
·00
""
:2
'"~
ro
280
20
40
60
80 120 100 Strain, 0.0001 in.lin.
ro
140
120.-------,-------,--------.-------,-------,MO
100
r-----+----7'4~==+=----t----
80
~
AS.011 4130 chromium-molybdenum alloy steel sheet, compressive stress-strain curves at room and elevated temperatures
700
560 ro
·00
""gf
a.
:2
60
420 rn
~
(f)
40
280
°0~------~2------~4------~6L-------8L-----~1J
Strain, 0.001 in.lin.
Source: D.E. Miller, "Determination of Tensile, Compressive, and Bearing Properties of Ferrous and Non-Ferrous Structural Sheet Materials at Elevated Temperatures;' WADC AFTR 6517, Part V, AD 142218, Arrnour Research Foundation, Dec 1957. As published in Structural Alloys Handbook, Vol 1, CINDASlPurdue University, 1994, p 34
Test direction: transverse. Sheet thickness = 1.626 mm (0.064 in.). Reat treated to 862 MPa (125 ksi) nominal tensile strength. Strain rate = O.Ol/min. Curve 1: Room temperature, modulus of elasticity = 205 GPa (29.8 x 106 psi). Curve 2: 204 oC (400°F), modulus of elasticity = 189 GPa (27.4 x 106 psi). Curve 3: 316 oC (600°F), modulus of elasticity = 178 GPa (25.8 x 106 psi). Composition: Fe-0.30C-0.60Mn-0.019P-0.034S-1.05Cr0.20Mo. UNS G41300 Source: R.J. Favor, W.P. Archbach, and W.S. Hyler, "Material-PropertyDesign Criteria for Metals, Part 7, The Conventional Short-Time Elevated Temperature Properties of Selected Low-and-Medium-Alloy Steels," WADC TR 55-150, Part 7, AD 142064, Oct 1957. As published in Structural Alloys Handbook, Vol 1, CINDASlPurdue University, 1994, p 34
100/Alloy Steel (AS)
300
......
... -:%
250 /
1)
200 .l<
rñ
'"
150
Q)
~ 100
50
F
CC MC "'CT MT
1750
1400
,f
.¡¡;
~
AS.012 4140 chromium-molybdenum alloy steel bar, monotonic and cyelic true stress-strain curves
2100
&.
:¡; rñ
1050 ~
I /
1ií Q)
~
Reat treatment: austenitized 999 oC (1830 °P), 1 h, oil quenched. Gage section size =5.08 mm diam x 7.62 mm long (0.2 in. diam x 0.3 in. long). Strain rate = 0.5/min. Test condition: MT, monotonic tension; MC, monotonic compression; CT, cyc1ic tension; CC, cyc1ic compression. Composition: Pe-0.4C-ICr-0.2Mo. UNS G41400 Source: P.N. Thielen, M.E Fine, and RA. Fournelle, Cyclic Stress Strain Relations and Strain-Controlled Fatigue of 4140 Steel, Acta Metal/., Vol 24 (No. 1), Jan 1976, pI-lO. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1203, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 18
700
350
/
2
3
True strain, %
......-:: ~ ...... ......
250
0~ ..... ......
~ "" ...
200
1750
~..,
1400
f'
&.
:¡; rñ
"1
rñ
'~"
MC MT ... CC CT
,,',//
~ 1ií
150
Q)
:::J
¡!:
100
50
AS.013 4140 chromium-molybdenum alloy steel bar, monotonic and cyelic true stress-strain curves
2100
300
1050 ~
/ /
1ií Q)
:::J
¡!:
700
350
/
2 True strain, %
3
Reat treatment: austenitized 999 oC (1830 °P), 1 h, oil quenched, tempered 199 oC (390 °P), 1 h, water quenched. Gage section size = 5.08 mm diam x 7.62 mm long (0.2 in. diam x 0.3 in. long). Strain rate = O.5/min. Test condition: MT, monotonic tension; MC, monotonic compression; CT, cyc1ic tension; CC, cyc1ic compression. Composition: Pe-0.4C-ICr-0.2Mo. UNS G41400 Source: P.N. Thielen, M.E Fine, and RA. Foumelle, Cyclic Stress Strain Relations and Strain-Controlled Fatigue of 4140 Steel, Acta Metall., Vol 24 (No. 1), Jan 1976, pI-lO. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1203, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 18
Alloy Steel (AS)/101
CC
l ,~
150
i.,
#
1400
V
(
ui
~
_MC MT
--=::::--
200
~
AS.014 4140 chromium-molybdenum alloy steel bar, monotonic and cyclic true stress-strain curves
1750
250
;
.........'"
"""-":--CT ."..---.,:;
1050
;
ui
In
"" # ""
~
r
100
50
8:.
:;
700
~
Heat treatment: austenitized 999 oC (1830 °F), 1 h, oH quenched, tempered 399 oC (750°F), 1 h, water quenched. Gage section size = 5.08 mm diam x 7.62 mm long (0.2 in. diam x 0.3 in. long). Strain rate = 0.5/min. Test condition: MT, monotonic tension; MC, monotonic compression; CT, cyc1ic tension; CC, cyc1ic compression. Composition: Fe-0.4C-1Cr-0.2Mo. UNS G41400 Source: P.N. Thielen, M.E Fine, and R.A. Fournelle, Cyclic Stress Strain Relations and Strain-Controlled Fatigue of 4140 Steel, Acta Metall., Vol 24 (No. 1), Jan 1976, pi-lO. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1203, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 18
350
1/ 2
3
4
o
True strain, %
150
125
¡..--
I 100
" ""
.¡¡;
"'ui" rJl
~
.,
"lií
75
AS.015 4140 chromium-molybdenum alloy steel bar, monotonic and cyclic true stress-strain curves
1050
I
.'
--
... ... ...
MC
!----!---- CT,CC- 875 ;;
;
--- 1-----
700
a.
:;
"
ui
525
In
~
.,
"lií
~
::J
t= 50
350
25
175
00
2
3
True strain, %
4
Heat treatment: austenitized 999 oC (1830 °F), 1 h, oil quenched, tempered 649 oC (1200 °F), 1 h, water quenched. Gage section size = 5.08 mm diam x 7.62 mm long (0.2 in. diam x 0.3 in. long). Strain rate = 0.5/min. Test condition: MC, monotonic compression; CT, cyc1ic tension; CC, cyc1ic compression. Composition: Fe-O.4ClCr-0.2Mo. UNS G41400 Source: P.N. Thielen, M.E Fine, and R.A. Fournelle, Cyclic Stress Strain Relations and Strain-Controlled Fatigue of 4140 Steel, Acta Metall., Vol 24 (No. 1), Jan 1976, pi-lO. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1203, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 18
102/Alloy Steel (AS)
o
10
20
30
Reduclion in heighl, % 40 50
1260
180
160
t::..
.~e(!.
eC'
~
~
Re¡O
100
1120
980 ro
'¡,).'lI
iñ :::l
........... B..l.Y=
a
.~s~
.¡¡;
en
~-
~~i¡oen ac\\\ned s
140
-"'- 120
AS.016 4140 chromium-molybdenum alloy steel bar, true compressive stress-strain curve
70
60
\(!., 1",
a. 840 :2
-/~
rñ en
700
f
~
~'"
Specimens taken from hot-worked 57.15 mm (2.25 in.) diam bar, test specimen 20 mm diam x 40 mm long, nonnalized and annealed. After compression of about 40%, specimens remachined to 14 mm diam x 21 mm long. The discontinuity of results was typical. True yield stress at 0.2% offset = 813 MPa (118 ksi); strainhardening exponent n = 0.145. Composition: Fe-0.39C1.00Cr-0.82Mn-0.26Si-0.21Mo-0.025S-0.012P. UNS G41400 Source: J.D. Crawford, R.G. Dunn, and J.H. Humphrey, The Influence of Alloying Elements on the Cold Deformation of Steel, Source Book on Cold Forming, American Society for Metals, 1975, p 142
560
80 t::..SpecimenA o Specimen B
420
60
0.2
0.4
0.6 True slrain
0.8
1.0
1.2
280
120.-------,-------,-------,-------,-------.840
AS.017 A286 nickel-chromium-molybdenum alloy steel sheet, tensile stress-strain curves (expanded range) at room and elevated temperatures
100~------~------+---~--~------~------~700
Sheet thickness = 1.575 mm (0.062 in.). 0.5-1000 h exposure. Heat treated: 982 oC (1800 °F), 1 h, argon, oil quenched, 718 oC (1325 °F), 16 h, air cool. Composition: Fe-25Ni-15Cr-2Ti-1.5Mn-1.3Mo-0.3Y. UNS S66286 ro
a.
:2
.--.'------.<+---+-----+--------1 420
+r-------r------~280
Strain, 0.001 in.lin.
ui
~ en
Source: J.R. Kattus, J.B. Preston, and H.L. Lessle, "Determination of Tensile, Compressive, Bearing, and Shear Properties at Elevated Temperatures," WADC TR 58-365, Nov 1958. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1601, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 19
Alloy Steel (AS)/103
1120
AS.018 A286 nickel-chromium-molybdenum alloy steel sheet, tensile stress-strain curves (full range) at room and elevated temperatures
140
980
120
840
Sheet thickness = 1.575 mm (0.062 in.). Heat treated: 982 oC (1800 °P), 1 h, argon, oil quenched, 718 oC (1325 °P), 16 h, air cool. Composition: Pe-25Ni-15Cr2Ti-l.5Mn-l.3Mo-0.3Y. UNS S66286
160 Room temperature
'"
'w .><
11.
rñ 100
700
80
560
60
420
'"
!
40
O
0.05
0.10
0.15
0.20
::2: rñ
'" ~
Source: J.R. Kattus, J.B. Preston, and R.L. Lessle, "Determination of Tensile, Compressive, Bearing, and Shear Properties at Elevated Temperatures," WADC TR 58-365, Nov 1958. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1601, CINDAS/USAF CRDA Randbooks Operation, Purdue University, 1995, p 19
280 0.30
0.25
Strain, in./in.
AS.019 4330, 4340, 4350 nickel-chromiummolybdenum alloy steel hot-rolled plate, tensile engineering stress-strain curves
2500
V 4340 435~ / 2000
'"
11.
:
1500
'" ~
~
¡..--
----
~
Test direction: long transverse. Specimen size = 6.25 mm diam x 38 mm long, austenitized in salt bath at 936 oC, 20 min, oil quenched. Tested as-quenched with Instron machine with crosshead velocity of 8.5 mmJs, which corresponds to strain rate of 0.0033/s
4330
Source: M. Saeglitz and G. Krauss, Deformation, Fracture, and MechanicaI Properties of Low-Temperature-Tempered Martensite in SAE 43xx Steels, Metal!. Mater. Trans., Vol 28A (No. 2), Feb 1997, p 382
Cl
<:
.~
.~ 1000 Cl
<: W
500
3
6 9 Engineering strain, %
12
15
104/AIIoy Steel (AS)
AS.020 4330, 4340, 4350 nickel-chromiummolybdenum alloy steel hot-rolled pi ate, tensile engineering stress-strain curves
2500
¡;
al
o..
~
~
/-
2000
1500
~
~
4350
Test direction: long transverse. Specimen size = 6.25 mm diam x 38 mm long, austenitized in salt bath at 936 oC, 20 min, oil quenched, tempered 10 h in 150 oC oil bath. Tested with lnstron machine with crosshead velocity of 8.5 mm/s, which corresponds to strain rate of 0.0033/s
~4340 ~4330
~
Source: M. Saeglitz and G. Krauss, Defonnation, Fracture and Mechanical Properties of Low-Temperature-Tempered Martensite in SAE 43xx Steels, Metall. Mate/: Trans., Vol 28A (No. 2), Feb 1997, p 379
el
e
.~
.~ 1000 el
e
UJ
500
o
10
5
O
15
20
Engineering strain, %
AS.021 4330, 4340, 4350 nickel-chromiummolybdenum alloy steel hot-rolled plate, tensile engineering stress-strain curves
2500
/" -~
t- ~
2000
al
o..
~ '" ~
1500
V
1ií
el
"
Test direction: long transverse. Specimen size = 6.25 mm diam x 38 mm long, austenitized in salt bath at 936 oC, 20 min, oil quenched, tempered 10 h in 175 oC oil bath. Tested with lnstron machine with crosshead velocity of 8.5 mmls, which corresponds to strain rate of 0.0033/s
4350
~4340
~30
Source: M. Saeglitz and G. Krauss, Defonnation, Fracture and Mechanical Properties of Low-Temperature-Tempered Martensite in SAE 43xx Steels, Metall. Mater. Trans., Vol 28A (No. 2), Feb 1997, p 379
e
.~
.~ 1000 el
e
UJ
500
o
O
5
10 Engineering strain, %
15
20
Alloy Steel (AS)/105
AS.022 4330, 4340, 4350 nickel-chromiummolybdenum alloy steel hot-rolled plate, tensile engineering stress-strain curves
2500
2000
o..'" :
1500
'"~
-
f; ~ I
...............
1ñ
C>
e
.~
Test direction: long transverse. Specimen size = 6.25 mm diam x 38 mm long, austenitized in salt bath at 936 oC, 20 min, oil quenched, tempered 10 h in 200 oC oil bath. Tested with Instron machine with crosshead velocity of 8.5 mm/s, which corresponds to strain rate of 0.0033/s
i'- 4350 ......... "
4340
Source: M. Saeglitz and G. Krauss, Deformation, Fracture and Mechanical Properties of Low-Temperature-Tempered Martensite in SAE 43xx Steels, Metall. Mater. Trans., Vol 28A (No. 2), Feb 1997, p 379
~4330
.~ 1000 C>
e
W
500
5
200
-'"
120
Cií 80
40
/
/
AS.023 4335V nickel-chromium-molybdenum alloy steel bar, compressive stress-strain curve
Bar thickness = 31.75 mm (1.25 in.). Vanadium-modified version of the standard 4335 steel. Austenitized 829 oC (1525 °P), 1 h, oil quenched, room temperature, tempered 241°C (465 °P), 2 h, air cooled. Composition: Pe-0.35C1.8Ni-0.8Cr-0.35Mo-0.2Y. UNS K33517
1400
1120
1/
.¡¡;
20
1680
/
160
u)
15
IV
240
'"~
10 Engineering strain, %
&.
:2
840
/
u)
'" ~
Ul
560
280
4
8 12 Strain, 0.001 in.lin.
16
Source: R.C. Jones, "Materials-SAE 4335 (Modified) Steel 260,000 to 280,000 psi Heat Treatment-Development of Process Control and Mechanical Properties for," Convair Division-General Dynarnics, 24 Oct 1962. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1205, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 17
106/Alloy Steel (AS)
200
AS.024 4340 nickel-chromium-molybdenum alloy steel sheet, tensile stress-strain curves at room and elevated temperatures
1400 Room temperature
160
1120
120
840
'00 -"
Heat treated: 829 oC (1525 °P), 10 min, air cooled, tempered 427 oC (800 °P), 1 h, to ultimate tensile strength = 1379 MPa (200 ksi). Composition: Pe-004C1.8Ni-0.8Cr-0.25Mo. UNS G43400 ro
a.
::2
'"~
'"~
i'ií
80
560
i'ií
Source: P.J. Hughes, J.E. Inge, and S.B. Prosser, "Tensile and Cornpressive Stress-Strain Properties of Sorne High Strength Sheet Alloys at Elevated Ternperatures," NACA TN 3315, 1954. As published in Aerospace Structural Metals Handbook, Vo11, Code 1206, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, P 28
1000 °F (538 OC)
40
280
L-------L-----~------~------~
2
4 6 Strain, 0.001 in.lin.
300
A
250
UJ
~.
--"
......
10
AS.025 4340 nickel-chromium-molybdenum alloy steel sheet, tensile stress-strain curves
......
"
~
Test direction: solid curves, transverse; dashed curves, longitudinal. Specimen size = 2.54 x 2504 x 101.6 mm (0.1 x 1 x 4 in.) gage tempered at 177 oC (350 °P). Composition: Pe-004C-l.8Ni-0.8Cr-0.25Mo. UNS G43400
1750
1400
r!
I 1
'00 -'"
~
----
______~O
2100
l'
200
~".:",;
8
ro
a.
::2
1050 gf
150
~ 100
700
50
350
O
O
2
4
6
Strain, %
8
Source: D.P. Fitzgibbon, "Semiannua1 Report on Pressure Vessel Design Criteria," TR-59-0000-00714, Space Technology Laboratories, Air Force Ballistic Missile Division, June 1959, AD 607630. As published in StructuralAlloys Handbook, Vo11, CINDAS/Purdue University, 1994, p 42
Alloy Steel (AS)/107
-¡(
250
"'-
~l
200
150
100
50
1400
&.
I I
-'"
Test direction: solid curves, transverse; dashed curves, longitudinal. Specimen size = 2.54 x 25.4 x 101.6 mm (0.1 x 1 x 4 in.) gage tempered at 232 oC (450°F). Composition: Fe-0.4C-1.8Ni-0.8Cr-0.25Mo. UNS G43400
1750
tí
.¡¡; ",-
,-,
\\
,,~
,,'1
'" ~
AS.026 4340 nickel-chromium-molybdenum alloy steel sheet, tensile stress-strain curves
2100
300
g :2
1050
I I I I I
Source: D.P. Fitzgibbon, "Semiannual Report on Pressure Vessel Design Criteria," TR-59-0000-00714, Space Technology Laboratories, Air Force Ballistic Missile Division, June 1959, AD 607630. As published in Structural Alloys Handbook, Vol 1, CINDAS/Purdue University, 1994, p 42
700
I I I I I
350
I
O O
4
2
8
6 Strain, %
250
200
.¡¡; -'"
AS.027 4340 nickel-chromium-molybdenum alloy steel sheet, tensile stress-strain curves
1750
~
~----
...=~~-"~. ~,
V"
Test direction: solid curves, transverse; dashed curves, longitudinal. Specimen size = 2.54 x 25.4 x 101.6 mm (0.1 x 1 x 4 in.) gage tempered at 371°C (700°F). Composition: Fe-0.4C-1.8Ni-0.8Cr-O.25Mo. UNS G43400
1400
\
150
1050 as [l. :2
g
'"
~
100
700
50
350
2
4
6 Strain, %
8
o
10
Source: D.E Fitzgibbon, "Semiannual Report on Pressure Vessel Design Criteria," TR-59-0000-00714, Space Technology Laboratories, Air Force Ballistic Missile Division, June 1959, AD 607630. As published in Structural Alloys Handbook, Vol 1, CINDAS/Purdue University, 1994, p 42
108/Alloy Steel (AS)
250
200
~~
-;
'" Uí ~
"
1050
''\
I I I I
U)
Test direction: solid curves, transverse; dashed curves, longitudinal. Specimen size = 2.54 x 25.4 x 101.6 mm (0.1 x 1 x 4 in.) gage tempered at 510 oc (950°F). Composition: Fe-0.4C-1.8Ni-0.8Cr-0.25Mo. UNS G43400
1400
150
~
AS.028 4340 nickel-chromium-molybdenum alloy steel sheet, tensile stress-strain curves
1750
,,;
U)
100
700
50
350
2
4
6
8
'" :2 Il.
~
Source: D.P. Fitzgibbon, "Semiannual Report on Pressure Vessel Design Criteria," TR-59-0000-00714, Space Technology Laboratories, Air Force Ballistic Missile Division, Iune 1959, AD 607630. Adapted from Structural Alloys Handbook, Vol 1, CINDASlPurdue University, 1994, p 42
o
10
Strain, %
AS.029 4340 nickel-chromium-molybdenum alloy steel bar, tensile stress-strain curves at room and low temperatures
36or-----.------.------,------.------r-----~2520
320~----~----~------+---~~~~~~----~2240
Bar thickness = 25.4 mm (1 in.). Heat treated to ultimate tensile strength of 1862 MPa (270 ksi). Composition: Fe0.4C-1.8Ni-0.8Cr-0.25Mo. UNS G43400
280~----~----~------+------+~~~~~F-~1960
240~----~----~------+---_7~--~~~----~1680
g¡
200 ~----~----~------__f_>!j~,"+----'-=='-"--'f"_"'-='-''-=-=-J 1400
'"
~
w
00
~
00
1120 ~
Uí 160
120~----4-----~~----+------r------r-----~840
80~----~~~~------+------r------r-----~560
40~~~~----~------+_----_r------r_----~280
Strain, 0.001 in.lin.
Source: "Design Properties as Affected by Cryogenic Temperatures," Battelle Memorial Institute, DMIC Memorandum 81, Jan 1961. As published in Structural Alloys Handbook, Vol 1, CINDASlPurdue University, 1994, p 41
Alloy Steel (AS)/109
200
1400
V)
150
/
~
¡g 100 !!!
ro
50
200-ksi l¡vel 180-ksi level
~
Source: MIL-HDBK-5H, Dec 1998, p 2-40
140-ksi level
V 2
4
Heat treated to the levels indicated. Composition: PeOAC-l.8Ni-0.8Cr-0.25Mo. UNS G43400
1050
J
V
AS.030 4340 nickel-chromium-molybdenum alloy steel (all products), typical tensile stress-strain curves
350
6
8
10
Strain, 0.001 in./in.
300r-·----~----~----_r----~------~--__,
2100
AS.031 4340 nickel-chromium-molybdenum alloy steel bar, tensile stress-strain curves at room and low temperatures
250~----+_----~----_+----_4--~~~~~
1750
Test direction: longitudinal. 0.5 h exposure. RambergOsgood parameters: n(room temperature) = 7.0, n(-110 °P) = 8.2, n(-312 °P) = 8.9. Composition: PeOAC-l.8Ni-0.8Cr-0.25Mo. UNS G43400
1400
'"
[l. ~ :2 ~ 150~----+_----~~~_+----_4------~--~ 1050
~
~ 700
350
2
4
6
Strain, 0.001 in./in.
8
10
O
12
Source: MIL-HDBK-5H, Dec 1998, p 2-40
110/Alloy Steel (AS)
250
o
35
Compressive langenl modulus, GPa 70 105 140
-...........
1---
'-r
200
150
/
'¡ji
-"
ui (f)
~
/
(f)
100
50
/
/
/
/ ...............
/
175
..-
'\
AS.032 4340 nickel-chromium-molybdenum alloy steel bar, compressive stress-strain and compressive tangent modulus curves
210 1750
Ramberg-Osgood parameters: n(room temperature) = 13. Composition: Fe-OAC-L8Ni-0.8Cr-0.25Mo. UNS G43400
1400
Source: MIL-HDBK-5H, Dec 1998. p 2-41 1050
"'
[L
:2 ui (f)
I
700
~
350
2
4
5
10
6 8 Slrain, 0.001 inJin.
o
10
12
25
30
I
o
15
20 6
Compressive langenl modulus, 10 psi
240
200
'¡ji
/
160
e 120
80
40
/
V
/
/
V
l---
/ /
1120 rf :2 ui
840
560
280
2
4
Austenitized, oil quenched, tempered to ultimate tensile strength of 1793 MPa (260 ksi). Tested at 24 oC (75 °F). Composition: Fe-OAC-l.8Ni-0.8Cr-0.25Mo. UNS G43400
1680
1400
/
-" ui
Uí
AS.033 4340 nickel-chromium-molybdenum alloy steel bar, compressive stress-strain curve
1960
280
6 Slrain, 0.001 inJin.
8
10
o
12
E (f)
Source: MIL-HDBK-5C, Vo11, 15 Dec 1978. As published in Aerospace Structural Metals Handbook, Vo11, Code 1206, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 21
Altoy Steel (AS)/lll
AS.034 4340 nickel-chromium-molybdenum alloy steel tu be, tensile stress-strain curves at room and elevated temperatures
140~--·----~------~-------.-------.-------.980
75°F (24 OC) 120~------+-----~A-------~-------+~----~MO
Tube size = 57.15 mm OD x 22.275 mm ID (2.25 in. OD x 0.875 in. ID). Hot roUed, air cooled, tempered at 538 oC (1000 °P), air cooled. Composition: Pe-O.4CL8Ni-0.8Cr-0.25Mo. UNS G43400
100 ~------+----I-~~_=-~=oJ--==-----t--------j 700
~ 80~------+'~~--4-------~------~-------1560~
~
rñ
~
~
mOO
~m
Source: "Properties of High-Strength Low-Alloy Steels at Slightly Elevated Temperatures," Timken Co., Resume of Investigations on Steels for High-Temperature High-Pressure Applications, 1960-1962. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1206, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 29
40~---&~+-------~------~-------+------~280
~~----+-------4-------~-------+------~140
2
4 6 Strain, 0.001 in.lin.
8
AS.035 4340 nickel-chromium-molybdenum alloy steel tube, tensile stress-strain curves at room and elevated temperatures
,-------.-------.-------.-------.------.1120
Tube size = 57.15 mm OD x 22.275 mm ID (2.25 in. OD x 0.875 in. ID). Heat treatment 843 oC (1550 °P), oil quenched, tempered at 566 oC (1050 °P), air cooled. Composition: Pe-O.4C- L8Ni-0.8Cr-0.25Mo. UNS G43400 ro
a.
1--------hfll..+----l-----------l-----------l------------l560
::i: ui
'"
~ ~--~~~------~------~------~----~280
~~----~------~------~------~----~140
2
4
6
Strain, 0.001 in.lin.
8
Source: "Properties of High-Strength Low-AlIoy Steels at Slightly Elevated Temperatures," Timken Co., Resume of Investigations on Steels for High-Temperature High-Pressure Applications, 1960-1962. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1206, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 29
112/Alloy Steel (AS)
150
120
90 '0;
1050
/
...-
--.........
-V
K ~
840
~" r'\.
-'"
rñ
630
l1l
o..
:2 rñ
'"
~
'" ~
(f)
60
420
30
210
0.04
0.16
0.12
0.08
0.20
AS.036 4340 nickel-chromium-molybdenum alloy steel tube, tensile stress-strain curves (full range) at elevated temperature
Tube size = 57.15 mm OD x 22.275 mm ID (2.25 in. OD x 0.875 in. ID). Comparison at 350 oC (662 °P) test temperature. Curve 1: hot roUed, air cooled, tempered 538 oC (1000 °P), air cooled. Curve 2: 843 oC (1550 °P), oil quenched, tempered 566 OC (1050 °P), air cooled. Composition: Pe-OAC-l.8Ni-0.8Cr-0.25Mo. UNS G43400 Source: "Properties of High-Strength Low-Alloy Steels at Slightly Elevated Temperatures," Timken Co., Resume of Investigations on Steels for High-Temperature High-Pressure Applícations, 1960-1962. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1206, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 29
o
0.24
Strain, in.lin.
1680
AS.037 4340 nickel-chromium-molybdenum alloy steel sheet, compressive stress-strain curves at room and elevated temperatures
200
1400
160
1120
Sheet thickness = 1.626 mm (0.064 in.). Reat treated: 829 oC (1525 °P), 10 min, air cooled, tempered 427 oC (800 °P), 1 h, to ultimate tensile strength of 1379 MPa (200 ksi). Composition: Pe-OAC-l.8Ni-0.8Cr-0.25Mo. UNS G43400
240
Room temperature
l1l
o..
'0;
-'"
:2 840 rñ
rñ 120
'"~
'"~
éñ
éñ 560
80 1000 °F (538 OC)
280
40
00
2
4
6
Strain, 0.001 in./in.
8
O
10
Source: P.J. Hughes, J.E. Inge, and S.B. Prosser, "Tensile and Compressive Stress-Strain Properties of Sorne High Strength Sheet Alloys at Elevated Temperatures," NACA TN 3315, 1954. As publíshed in Aerospace Structural Metals Handbook, Vol 1, Code 1206, CINDAS/USAF CRDA Handbooks Operatíon, Purdue University, 1995, P 32
Alloy Steel (AS)/113
12or-----,------r-----,------~----_r----_.MO
AS.038 8630 nickel-chromium-molybdenum alloy steel (all products), typical tensile stress-strain curves at elevated temperatures
100~----~----~r7~--1_----~------+_----~700
Heat treated to ultimate tensile strength of 862 MPa (125 ksi). 0.5 h exposure. Ramberg-Osgood parameters: n(500 °F) = 9.0, n(850 °F) = 19, n(1000 °F) = 4.4. Composition: Fe-0.3C-O.55Ni-O.5Cr-O.25Mo. UNS G86300
80~----~--+_~------+-----_+------T_----~560
1000 "F (538 "C)
tU
~ ~ gf 60 ~----___+.f_+--__j--~"--_+_----~------+_----~ 420 rñ
Source: MIL-HDBK-5H, Dec 1998, p 2-31
E en
E
en
40~--_+~~--__j------_+_----_+------+_----~280
20~~L-~----~------+------+------+-----~140
°0L------2L-----~4------~6------~8------1~0----~1f
Strain, 0.001 in.lin.
AS.039 8630 nickel-chromium-molybdenum alloy steel sheet, tensile stress-strain curves at room and elevated temperatures
120 ,----------.,----------,-----------,---------, MO Room temperature
Sheet thickness = 1.626 mm (0.064 in.). Quenched and tempered to u1timate tensile strength of 862 MPa (125 ksi) (at room temperature). Composition: Fe-0.3C-0.55Ni0.5Cr-0.25Mo. UNS G86300
100~--------+-----~~+---------~--------~700
tU
a.
~
::¡;
gf 60~--------~~L-----~~~~
420 rñ en
~
~
éií 40~----~~~~------+_--------~--------~280
20~_h~----+---------+_--------~--------~140
1200 "F (649 "C)
2
4 Strain, 0.001 in.lin.
6
Source: D.D. Doerr, "Determination of Physical Properties of Ferrous and Non-Ferrous Structural Sheet Materials at Elevated Temperatures," WADC AF TR 6517, Pt 2, Armour Research Foundation, April 1954. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1208, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 14
114/Alloy Steel (AS)
160 I---T---I----::]::::::=::::=:~q 1120
140
r---------+---------~----~---1--~~~__1980
120
Sheet thickness = 1.626 mm (0.064 in.). Quenched and tempered to ultimate tensile strength of 1103 MPa (160 ksi) (at room temperature). Composition: Fe-0.3C-0.55Ni0.5Cr-0.25Mo. UNS G86300
840
100 ro a. ::;¡; rñ
'00
"'rñ"
'"
~
80
r---------+---.h~~~---------1--------__1560
'" ~
1ií
en 60
420
40
~----~~+---------~---------+--------~280
AS.040 8630 nickel-chromium-molybdenum alloy steel sheet, tensile stress-strain curves at room and elevated temperatures
Source: D.D. Doerr, "Deterrnination of Physical Properties of Ferrous and Non-Ferrous Structural Sheet Materials at Elevated Temperatures," WADC AF TR 6517, Pt 2, Armour Research Foundation, Apri11954. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1208, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 14
1200 °F (649 OC) 20 ~-J.~--_+=-~~~+===~:=~~~~--~140
O O
2
4 Strain, 0.001 in./in.
6
1540
220
-
200
V
180 160
[ V
140
~ 120 rñ
'"
~ 1ií 100
80 60 40 20
/ V
/
/ V
L~
/
1400
690°F 366 OC) 1260 840°F 449 OC)
1120
990°F 532 OC)
980
1170 °F (632 OC)
ro 840 ~ rñ '" 700 ~
en
560
Normalized 1600 °F (871°C) 420 280 140
0.2
0.4
0.6
0.8 Strain, %
1.0
1.2
1.4
o
1.6
AS.041 8630 nickel-chromium-molybdenum alloy steel sheet, tensile stress-strain curves for various tempering temperatures
Test direction: longitudinal. Sheet thickness = 1.575 mm (0.062 in.). Heat treatrnent: 857 oC (1575 °F), oil quenched, tempered at indicated temperature, lowest curve norrnalized as indicated. Composition: Fe-0.3C0.55Ni-0.5Cr-0.25Mo. UNS G86300 Source: L.R. Jackson and N.A. Crites, "Development of Mechanical Properties Inforrnation on Carbon and Alloy Steels at Various Strength Levels," Battelle Memorial Institute Report to AISA, 1 Feb 1951. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1208, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 9
Alloy Steel (AS)/115
980
140
100
'"
80
60
/
40
20
Bar diameter = 25.4 mm (1 in.). Heat treatment: 857 oC (1575 °F), oil quenched, tempered at indicated temperature, lowest curve normalized as indicated. Composition: Fe-0.3C-0.55Ni-0.5Cr-O.25Mo. UNS G86300
840
1190 'F (643 'C)
/
'iij .><
~
1000 'F (538 'C)
V )
120
ui
AS.042 8630 nickel-chromium-molybdenum alloy steel bar, tensile stress-strain curves for various tempering temperatures
1120
160
700
~
:2 560 ui
g
't-
en
Normalized 1600 'F (871 'C) 420
Source: L.R. Jackson and N.A. Crites, "Development of Mechanical Properties Information on Carbon and Alloy Steels at Various Strength Levels," Battelle Memorial Institute Report to AISA, 1 Feb 1951. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1208, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 9
280
/
140
1/
0.2
0.4
0.6
0.8
1.0
1.2
1.4
o
1.6
Strain, %
160
--+-
AS.043 8630 nickel-chromium-molybdenum alloy steel bar, compressive stress-strain curves for various tempering temperatures
1120
1---
/"'-
140
1/
120
100
/
'iij .><
ui
'"
~
80
60
40
20
1000 'F (538 'C)
I
l/
f /
V
I
1
Bar diameter = 25.4 mm (1 in.). Heat treatment: 857 oC (1575 °F), oil quenched, tempered at indicated temperature, lowest curve normalized as indicated. Composition: Fe-O.3C-O.55Ni-O.5Cr-O.25Mo. UNS G86300
840
1190 'F (643 'C) 700
¡..---
---
V-l.---
ro
a.
:2
560 ui
'" ~
Normalized 1600 'F (870 'C)
420
280
140
1/ 0.2
980
0.4
0.6
0.8 Strain, %
1.0
1.2
1.4
o
1.6
Source: L.R. Jackson and N.A. Crites, "Development of Mechanical Properties Information on Carbon and Alloy Steels at Various Strength Levels," Battelle Memorial Institute Report to AlSA, l Feb 1951. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1208, CINDAS/USAF CRDA Handbooks Operation, Pnrdue University, 1995, p 12
116/Alloy Steel (AS)
160
IV ---
140
120
/ /-::
100 '00
-'"
vi
UJ
~
80
~;:'
¡..---
60
-'
-'
,.J--==- ----
/
(-50°F) (b)
840
700 ro
o..
:;¡; 560 vi UJ
~
1i5 420
/ /
40
AS.044 8630 nickel-chromium-molybdenum alloy steel casting, monotonic and cyclic stress-strain curves at room temperature (a) and -46 oC
980
Il
1i5
20
~.-~
--:"'"
1120
-
280
140
2
4
(a)
6 8 Slrain x 0.001
10
12
o
14
160,...----,----,----,----,----,----,.--....., 1120
./V-
:-+--- 980
140 1---+---1--/.".c.+---+--_-.1---:..-----. -, 1
11
;;:-:.
~::::---
120~--+--_,~--_\__~;~'~-+--+--+---840
I
'" .'" 100~--+--,~~"'--+_--+_--+_--r_---700 :1 ~
. /f~/
~
80 1 - - - h P - - - P - t - - - r _ - - r _ - - r _ - - r _ - - - 560 vi
~
1 /
1/
1i5
1i5
601---f---+---+---+---+---+--~420
40
20
/
/
280
/
140
°0L---2L---4L---6L---8L---1LO---1~2--~1; (b)
Slrain x 0.001
Reat treatment: Nonnalized 900 oC (1652 °F), austenitized 885 oC (1625 °F), water quenched, tempered 510 oC (950°F), 1.5 h. Solid curve, monotonic loading; dashed curves, cyclic loading. Composition: Fe-0.3C0.55Ni-0.5Cr-0.25Mo. UNS 113042, UNS 113050 Source: R.1. Stephens, J.H. Chung, A. Fatemi, H.W. Lee, S.O. Lee, C. Vaca-Oleas, and C.M. Wang, Constant and Variable Amplitude Fatigue Behavior of Five Cast Steels at Room Temperature and -45C, J. Eng. Mater. Technol., Vol 106 (No. 1), Jan 1984, p 25-37. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1208. CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 14
Alloy Steel (AS)/117
~20
/
150
!
50
AS.045 8630 nickel-chromium-molybdenum alloy steel (all products), typical stress-strain curves for various heat treatments
1400
200
I
1/
11
~ 2
35
l.---
ksi
(1379~Pa)
180 k i (1241 Mr) level
Curves for heat treatments to various strength levels. Composition: Fe-O.3C-O.55Ni-O.5Cr-O.25Mo. UNS G86300
1050 150 ksi 1034 MP11eVel
Source: MIL-HDBK-5H, Dec 1998, p 2-30 125 ksi (8 2 MPa) leVr
r--
Normalized
350
4
6 8 Strain, 0.001 in.lin.
10
Compressive tangent modulus, GPa 70 105 140
150
level
175
AS.046 8630 nickel-chromium-molybdenum alloy steel (all products), typical compressive tangent modulus curves at room temperature for various heat treatments
210 1400
Heat treatments indicated by ultimate strength levels. Composition: Fe-0.3C-0.55Ni-O.5Cr-O.25Mo. UNS G86300
1050
150 ksi (1034 MP ) level
Source: MIL-HDBK-5H, Dec 1998, p 2-31 125 ksi (862 MPa level
'"
a.
:2 700 ui In
r----
~
~alized
t----
50
5
----
350
~
10 15 20 25 Compressive tangent modulus, 106 psi
118/Alloy Steel (AS)
140 r - - - - - , - - - - - , - - - - - - - - - , - - - - - - - - , 980
AS.047 8630 nickel-chromium-molybdenum alloy steel sheet, compressive stress-strain curves at room and elevated temperatures
Room temperature
120r----------r--------~--~~~~~--------4MO
Sheet thickness = 1.626 mm (0.064 in.). Reat treatment: quenched and tempered to room temperature ultimate tensile strength of 827 MPa (120 ksi). Composition: Fe0.3C-0.55Ni-0.5Cr-0.25Mo. UNS G86300
400°F (204 OC) 100r----------r----~_7~----_=~~
700
Source: D.D. Doerr, "Determination of Physical Properties of Ferrous and Non-Ferrous Structura1 Sheet Materia1s at E1evated Temperatures;' WADC AF TR 6517, Pt 2, Armour Research Foundation, April1954. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1208, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 15
20~~~----~--------_+----------+_--------~140
°0L---------~2----------~4----------~6--------~80
Strain, 0.001 in.lin.
1260
180
AS.048 8630 nickel-chromium-molybdenum alloy steel sheet, compressive stress-strain curves at room and elevated temperatures
Room temperature
.¡¡;
"'
160
1120
140
980
120
MO
100
700
Sheet thickness = 1.626 mm (0.064 in.). Reat treatment: quenched and tempered to room temperature ultimate tensile strength of 1102 MPa (160 ksi). Composition: Fe0.3C-0.55Ni-0.5Cr-0.25Mo. UNS G86300
~
80
'" 560 ~
60
420
40
280
20
140
en
2
4 Strain, 0.001 in.lin.
6
8
O
Source: D.D. Doerr, "Determination of Physical Properties of Ferrous and Non-Ferrous Structural Sheet Materia1s at E1evated Temperatures," WADC AF TR 6517, Pt 2, Armour Research Foundation, Apri1 1954. As pub1ished in Aerospace Structural Metals Handbook, Vol 1, Code 1208, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 16
Alloy Steel (AS)/119
AS.049 9310 nickel-chromium-molybdenum alloy steel gears, true plastic stress-strain curves
2500
Uncarburized 9310 at 230 oC after quenching from 900 0e. 0.2% yield strength = 1000 MPa. Workhardening rate, n = 0.17. Composition prior to carburizing: Fe-O.ll C-3 AONi-l.26Cr-0.13Mo-0.56Mn0.26Si-0.04AI-0.03Cu-0.OlS. UNS G93106
2000
0.2% offset =1000 MPa 11
,f 1500
11
:lE ui
'"
~
V
Q)
~ 1000
~
~
---
Souree: U.J. De Souza and M.F. Amateau, Deformation of Metastable Austenite and Resulting Properties During the Ausform-Finishing of lpet CarburizedAISI 9310 Steel Gears, Metall. Mater. Trans. A, Vol30A (No. 1), Jan 1999, p 186
500
o
~
O
0.1
0.2
0.3
0.4
0.5
0.6
True strain
25oor-------.-------,--------,-------,------~
2000~------+_------4__.+_--~~~~_+------~
,f 1500r-------+---~~~-------r-------r------~ :lE
¡i ~
1ií Q)
~ 1000r---~~~~----~-------r-------r------~
500~~----+-------~-------r-------r------~
°0L-------OL.2-------0~.4------~0.~6-------0L.8------~1.0 True strain, %
AS.050 9310 nickel-chromium-molybdenum alloy steel gears, compressive true plastic stress-strain curves Compressive flow properties of metastable austenite at 230 oC in 1% carburized steel. Strain rate = 0.005/s. Steep and continuous increase in flow stress is sign of high work-hardening rates (n). Type A, n = 0.56; type B, n = 0.55. Type A specimen 10 mm diam x 2.2 mm thick (004 in. diam x 0.086 in. thick), vacuum carburized to 1.06 wt% e. Type B stacked disks 10 mm diam x 15 mm high (004 in. diam x 0.6 in. high), carburized in atmosphere to 1.1 wt% prior to stacking. Composition prior to carburizing: Fe-0.llC-3AONi-1.26Cr-0.13Mo0.56Mn-0.26Si-0.04AI-0.03Cu-0.OlS. UNS G93106 Souree: U.J. De Souza and M.F. Amateau, Deformation of Metastable Austenite and Resulting Properties During the Ausform-Finishing of lpet Carburized AlSI 9310 Steel Gears, Metall. Mater. Trans. A, Vol30A (No. 1), Jan 1999, p 186
120/Alloy Steel (AS)
1600r------r-----,------,------.------,-----~
ro
a. :2:
Compressive flow properties of metastable austenite in 1% carburized steel (type A). Type A specimen 10 mm diam x 2.2 mm thick (0.4 in. diam x 0.086 in. thick), vacuum carburized to 1.06 wt% C. Samples were ausformed at different temperatures with the following 0.2% yield strengths: curve 1, 85 oC, 425 MPa; curve 2, 110 oC, 425 MPa; curve 3, 160 oC, 431 MPa; curve 4, 232 oC, 327 MPa. UNS G93106
1000
ui
'"
~
800
ID ::J
Souree: U.J. De Souza and M.E Amateau, Deformation of Metastable Austenite and Resulting Properties During the Ausform-Finishing of lpet Carburized AISI 9310 Steel Gears, Metal!. Mater. Trans. A, Vol30A (No. 1), Jan 1999, p 189
t= 600 400
200
00
AS.051 9310 nickel-chromium-molybdenum alloy steel gears, compressive true plastic stress-strain curves
0.05
0.10
0.15 True strain
0.20
0.25
0.30
Alloy Steel (AS)/121
AS.052 HNM nickel alloy steel sheet, isochronous stress-strain curves at 482 oC (900 °F) (a) and 649 oC (1200 °F) (b)
8o.-------------,------------~------------~560
200 h 300 h
Solution treated 2050 °P, 15 min, oil quenched, aged 732 oC (1350 °P), 15 h. Composition: Pe-0.3C-9.5Ni18.5Cr-3.5Mn
60~--------.6~~----------_+------------~420
~ ~'" ¡i 40 1-------+--------1--------------1-------------____1 280 '"
~
~
20~_r--------~------------_+------------~140
°0L-----------~4~----------~8-------------"1~
Strain, 0.001 in./in.
(a)
80r------------,------------~------------_;560
601----------------1------------__1_------------____1420
~
rf.
100h
::¡;
¡i 40 1---------------1-r---~"--"C::7''''---__I_--------____1 280 '"
~
~
20~----~~-~------------+--------4140
4 (b)
8 Strain, 0.001 in./in.
Saurce: "Crucible HNM," Preliminary Data Sheet, Crucible Steel Ca., Issue No. 2, lune 1960. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1506, CINDAS/USAF CRDA Handbooks Operation, Purdue University, p 3
122/Alloy Steel (AS)
200
1400
160
1120
120
840
·00
AS.053 HY-TUF nickel alloy steel plate, tensile stress-strain curves at room and elevated temperatures
Plate thickness = 6.35 mm (0.25 in.). Silicon-modified steel treated 871 oC (1600 °F), 25 min, oi1 quenched, 316 oC (600°F), 0.5 h to ultimate tensile strength of 1517 MPa (220 ksi). Composition: Fe-0.25C-l.8Ni-l.5Sil.3Mn-OAMo. UNS K32550
a.
::;;;
"'
'"~
éíí
560
80
'" ~
Source: P.J. Hughes, J.E. Inge, and S.R Prosser, "Tensile and Cornpressive Stress-Strain Properties of Sorne High-Strength Sheet Alloys at Elevated Ternperatures," NACA TN 3315, Nov 1954. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1214, CINDAS/USAF CRDA Handbooks Operation, Purdue University,
1995, P 7
1000 'F (538 'C)
280
40
ooL------2~-----L4------~6------~8------~10------~120
Strain, 0.001 in.lin.
240 , . - - - - - - , , - - - - - - ¡ - - - , - - - , - - - , - - - . , 1680
AS.054 HY-TUF nickel alloy steel plate, compressive stress-strain curves at room and elevated temperatures
200
P1ate thickness = 6.35 mm (0.25 in.). Silicon-modified steel treated 871°C (1600 °F), 25 min, oi1 quenched, 316 oC (600°F), 0.5 h to u1timate tensile strength of 1517 MPa (220 ksi). Composition: Fe-0.25C-1.8Ni-1.5Sil.3Mn-OAMo. UNS K32550
160
1120
·00
"'
120
éíí
80
1000 'F (538 'C)
560
40
00~-----L------4L------6L------8L------1LO----~1~ 2 Strain, 0.001 in.lin.
Source: P.J. Hughes, J.E. Inge, and S.B. Prosser, "Tensile and Cornpressive Stress-Strain Properties of Sorne High-Strength Sheet Alloys at Elevated Ternperatures," NACA TN 3315, Nov 1954. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1214, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 8
Alloy Steel (AS)/123
AS.055 HY-TUF nickel alloy steel tu be, tensile stressstrain curves at room and elevated temperatures
240r-------r-------r-------~------,_----__¡1680
Tube diameter =53.975 mm (2.125 in.). Hollow section with a diameter-to-thickness ratio of 5 to 40. Ultimate tensile strength of 1496-1703 MPa (217-247 ksi). Data' based on 30 tests. UNS K32550
200~------~------~------+_--~~~77~~1400
160 ~------~------+_--__;P-.H~----+_----______l1120 ro
a.
::¡¡; ~------~------~------+_------+_----______l840
~
~
Source: "Stress-Strain Curves for High-Strength Alloy Steel," Rep. No. 732, The Cleveland Pneumatic Tool Co., 25 Feb 1955. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1214, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 4
éñ ~------~~----+_------+_------+_----______l560
~--~~+_------+_------+_------+_----______l280
4
2
8
6
Strain, 0.001 in./in.
700
100
80
V
~
1ií el
e
.~
al
.§, e
560
(
40
W
140
20
0.05
0.10
0.2% yield strength, 324 MPa (47.0 ksi); ultimate tensile strength, 614 MPa (89.1 ksi); elongation, 45.7%. Composition: 37Fe-35Ni-27Cr Source: Courtesy of Special Metals Corporation
/'
~
gf 60
~
~
AS.056 Incoloy 803 annealed nickel alloy steel sheet 3 mm (0.118 in.) longitudinal engineering stressstrain curve (full range)
0.15 Strain
0.20
0.25
o
0.30
124/Alloy Steel (AS)
g¡
60
420
AS.057 Incoloy 803 annealed nickel alloy steel sheet 3 mm (0.118 in.) longitudinal engineering stressstrain curve (expanded range)
50
350
0.2% yield strength, 301 MPa (43.7 ksi); ultimate tensile strength, 614 MPa (89.1 ksi); elongation, 46.4%. Composition: 37Fe-35Ni-27Cr
280 ~ :2
Source: Courtesy of Special Metals Corporation
40
rñ In
~
g' 30
.~
'e" .6> e
20
W
10
/
~
I I I
rñ
In
~ 210 ~ c
.~
'c"
.6> c
140 w
70
1/ 0.004
0.002
0.006
0.008
o.oPo
Strain
100
700
80
560
~ rñ 60
i
Cl
c
.~
'" .§,
40
c
w
I
/
/'
V
.,---~
AS.058 Incoloy 840 annealed nickel alloy steel sheet 0.51 mm (0.020 in.) longitudinal engineering stressstrain curve (full range)
0.2% yield strength, 197 MPa (28.6 ksi); ultimate tensile strength, 552 MPa (80.1 ksi); elongation 40.5%; n, 0.371. Composition: 58Fe-21Ni-19CrO.8Si-0.03C tU
a. 420 gf :2 !!:! "tí Cl
c
"m 280.s:
Cl
c
W
140
20
0.05
0.10
0.15 Strain
0.20
0.25
o
0.30
Source: Courtesy of Special Metals Corporation
Alloy Steel (AS)/125
30
í
25
!.----
AS.059 Incoloy 840 annealed nickel alloy steel sheet 0.51 mm (0.020 in.) longitudinal engineering stressstrain curve (expanded range)
245
--
35
210
0.2% yield strength, 201 MPa (29.2 ksi); ultimate tensile strength, 563 MPa (81.6 ksi); elongation, 38.8%. Composition: 58Fe-21Ni-19Cr-0.8Si-0.03C
175
I
ro
c..
Source: Courtesy of Special Metals Corporation
:2:
140 gf ~
1ií Cl
e
105 -g'j
10
5
e
I
.0,
e
UJ
70
I
35
0.002
0.004
0.008
0.006
o
0.010
Strain
80
~ ui 60
i
Cl
e "55 Ql
.¡§,
40
e
UJ
AS.060 Incoloy A286 annealed nickel alloy steel sheet 1 mm (0.039 in.) longitudinal engineering stress-strain curve (full range)
700
100
/
/
v
/'
v-
~ 560
&.
:2: 420 ui
i
Cl
e "55
280 ~
"g> UJ
140
20
0.05
0.10
0.15 Strain
0.20
0.25
o
0.30
Iron-base superalloy. 0.2% yield strength, 283 MPa (41.1 ksi); ultimate tensile strength, 652 MPa (94.5 ksi); elongation, 37.8%. Composition: Fe-25.5Ni-14.25Cr1.25Mo Source: Courtesy of Special Metals Corporation
126/Alloy Steel (AS)
I "-
40
280
I I
~
~
el
e
.~ Q)
.g, 20 e
LU
10
AS.061 Incoloy A286 annealed nickel alloy steel sheet 1 mm (0.039 in.) longitudinal engineering stress-strain curve (expanded range)
350
50
'"
Il.. ::l;
210
~
Iron-base superalloy. 0.2% yield strength, 288 MPa (41.7 ksi); ultimate tensile strength, 644 MPa (93:4 ksi); elongation 36.5%. Composition: Fe-25.5Ni-14.25Cr1.25Mo Source: Courtesy of Special Metals Corporation
el
e
.~
140 ~
'g
LU
I
70
I 0.002
0.004
0.006
0.008
o
0.010
Strain
AS.062 Incoloy 864 annealed nickel alloy steel 0.41 mm (0.016 in.) sheet longitudinal engineering stressstrain curve (full range)
700
100
80
( ,..,
V
/:
~
.......-
---
~
0.2% yield strength, 259 MPa (37.6 ksi); ultimate tensile strength, 658 MPa (95.5 ksi); elongation, 43.6%; n, 0.4435. Composition: 39Fe-21Cr-34Ni-4.2Mo
560
'"
Il..
420
~
'"~
UJ
tí
el
e
.~
280 .~
el
e
LU
140
20
0.05
0.15
0.10 Strain
0.20
o
0.25
Source: Courtesy of Special Metals Corporation
Alloy Steel (AS)/127
AS.063 Incoloy 864 annealed nickel alloy steel 0.41 mm (0.016 in.) sheet longitudinal engineering stressstrain expanded range
350
50
--
40
_ _ _ _ 1-
0.2% yield strength, 262 MPa (38.0 ksi); ultimate tensile strength, 652 MPa (94.5 ksi); elongation 43.6%. Composition: 39Fe-21Cr-34Ni-4.2Mo
280
'"
o...
Source: CQurtesy of Special Metals Corporation
210 ::2. gJ ~
iñ el 1:
"55
140
:g
'61 1:
w
70
10
0.010
0.005
o.olo
0.015
Strain
320 -
280
A-~
\~, \
'"
240
o... ::2 rñ
'"~
iñ 200
~,
,
~
........ ~
~~ .....
......
.....
al
>
-"'-- .. --..... ..... .....
..... ........... 8:1
.....
t5
,¡g w
45
....
~
160
Lld=-
- - /1
l
...... -
-
-- i1 I
"-'-
_. - 4:1
120 -
I
15
¡
2
345 Effective strain
6
7
8
AS.064 3.3% silicon alloy steel, von Mises effective stress-strain curves Strain rate = 6.5/s. Tested at 700 oC (1290 °F). Stressstrain curves for solid torsion specimens of 3.3% Si steel showing effect of gage length to diameter ratio (LI á) on flow stress at high strain rates when adiabatic heating occurs. The flow curves are in terms of von Mises effective stress-strain (a - E), defined by a = ~, and E = r / V3 where 1: - r is the shear-stress/shearstrain curve obtained in torsion testing. In both solid bars and tubular specimens, the gage length-to-diameter ratio may have a marked effect on the actual specimen temperature during moderate-speed r = 10-2 to 10 S-l torsion tests because of the effects of heat conduction. Because of this, flow curves derived from data obtained at these rates tend to show a dependence on the length-todiameter ratio (Llá). Flow curves for large Lid specimens tend to fall below those for small Lid ratios, in which most of the deformation heat is dissipated into the shoulders. Interpretation of fracture strain data from such tests should take into account not only the nominal (initial) test temperature, but also the temperature history during the test. Source: R.A. Kuhn, Shear, Torsion, and Multiaxial Testing, Mechanical Testing and Evaluation, Vol 8, ASM Handbook, ASM International, 2000, p 191
High-Strength Steel (HS)/129
High-Strength Steel (HS) HS.001 Various HSLA and A36 steel high-strength low-alloy (HSLA) steel, stress-strain curves
-.---,---,------,---,---r----r-----, 980
140
Comparison of stress strain curves for alloys with specified minimum values. Curve 1: T-l, T-l type A, T-l type B; minimum yield strength (MYS) = 689 MPa (100 ksi). Curve 2: CON-PAC; MYS = 551 MPa (80 ksi). Curve 3: EX-TEN 60; MYS = 413 MPa (60 ksi). Curve 4: COR-TEN, TRI-TEN, EX-TEN 50; MYS = 345 MPa (50 ksi). Curve 5: EX-TEN 42; MYS = 289 MPa (42 ksi). Curve 6: ASTM A36; MYS = 248 MPa (36 ksi). Modulus of elasticity =200 GPa (29 x 106 psi)
120 f:f----+-==-+-----t.--+--t---t----i 840
Source: "High-Strength Low-Alloy Steels," U.S. Steel, Oct 1971. As published in Structural Alloys Handbook, Vol 1, Battelle Columbus Laboratories, 1980, p 3
~~~--+--___t--+--+_-_+-~~280
20~----+--+--___t--+--+_-_+--~140
OL-·--~---~-~
O
0.05
0.10
__-~---~-~--~O
0.15
0.20
0.25
0.30
0.35
Slrain, in.lin.
80
60
-
i'-..
~
70
r--
/
/"
50
'\
560
HS.002 A242 high-strength low-alloy (HSLA) steel sheet, stress-strain curve (complete range)
490
USS COR-TEN A sheet. Composition: Fe-0.09C0.37Mn-0.088P. UNS K11510
420
Source: B.A. Dolega, "Investigation of Low Alloy, High Strength Steel as a Missile Fuel Tank," Report BLR 53-56, Bell Aircraft, March 1953. As published in Structural Alloys Handbook, Vol 3, CINDASlPurdue University, 1994, p 6
350
&.
::< 280 .;
~
30
210
20
140
10
70
5
10
15 Slrain, 0.001 in.lin.
20
25
130/High-Strength Steel (HS)
60
I
55 50 45
I /
40
~ 35
v
00 25 20 15
/
/
385
r----r'
/
315 280
/ / 1
USS COR-TEN A sheet. Sheet thickness = 1.778 mm (0.070 in.). Composition: Fe-0.09C-0.37Mn-0.088P. UNS K11510
350
Yield strength at 0.2% offset
/
245
& ::a:
0 .2 % offset
Source: EA. Dolega, "Investigation of Low Alloy, High Strength Steel as a Missile Fuel Tank," Report BLR 53-56, Bell Aircraft, March 1953. As published in Structural Alloys Handbook, Vol 3, CINDASlPurdue University, 1994, p 6
210 cñ
J
~
5
/
.-'"
1/
~Z30
10
HS.003 A242 high-strength low-alloy (HSLA) steel sheet, stress-strain curves (expanded range)
420
'"~
/
175 00
/
/
I
140
/
105
/
70
/
/
1/
35
1/ 2
3
5
4
6
o
Strain, 0.001 in.lin.
150
r
-
~
HS.004 Fe-5Ni-Cr-Mo-V high-strength low-alloy (HSLA) steel plate, stress-strain curve
1050
700
100
::a:'"
.¡¡;
a.
-"
cñ
cñ
'" ~
'"
~
ro
350
50
0.02
0.04 Strain, in.lin.
0.06
o
0.08
Plate thickness 50 mm (2 in.). Heat treatment: 899 oc (1650 °F), 1 h, water quenched, 816 oC (1500 °F), 1 h, water quenched, 566 oC (1050 °F), 2 h, water quenched. Tensile yield strength = 944 MPa (137 ksi); elastic modulus = 203 GPa (29.5 x 106 psi). Composition: Fe0.IIC-5Ni-0.55Cr-0.47Mo-0.07V Source: L.E Porter et al., "The Development of an HY 130(T) Steel Weldment," Report 39.018-001, NOBS 88540, U.S. Steel Applied Research Laboratory, 1 July 1966. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1216, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 21
High-Strength Steel (HS)/131
HS.005 Microalloyed high-strength low-alloy (HSLA) steel, compressive true stress-true plastic strain curves at different strain rates
350
300
Rot roUed. Thermomechanical processing typicaUy ineludes rough rolling, 1100-1240 oC (2012-2264 °F), and finish rolling, 810-900 oC (1490-1652 °F), fast cooling to 700 oC (1292 °F), and air cooling. (a) Tested at 900 oC. (b) At 1200 oc. Composition: Fe-0.08C-1.3Mn0.3Si-0.2Ni-0.08V-0.05Nb-0.015P-0.008S
250 ro
o..
::;: 200 ui
'"~
Source: N.S. Mishra, in Hot Working Guide A Compendium of Processing Maps, Y.V.R.K Prasad and S. Sasidhara, Ed., ASM International, 1997, P 337
iñ (1)
:>
150
¡!:
100
50
O O
0.1
0.2
(a)
0.3
0.4
0.5
0.6
True plastic strain
125 100/s
1O/s
1.0/s
0.1/s 0.01/s
0.001/s
0.1 (b)
0.2
0.3 True plastic strain
0.4
0.5
0.6
132/High-Strength Steel (HS)
80
~
/
60
--
e
560
HS.006 A633 grade high-strength low-alloy (HSLA) steel plate, stress-strain curve (complete range)
-~
~ 420
a..'"
:2
280
~
3
6
12
9
18
15 Slrain, %
21
24
120
80
HS.007 Various high-strength structural steels, typical stress-strain curves (full range)
840
-.........
/ ~ ,.--
~'\ A~ ~~
1/
Lf
....-
700
~ - --........
A572
r-40
Source: "P1ate Se1ection Guide Book," Beth1ehem Stee1, Beth1ehem, PA, 1985. As pub1ished in Structural Alloys Handbook, Vol 3, CINDAS/ Purdue University, 1994, p 6
140
20
100
Suitable for welded construction. Plate thickness = 19.05 mm (0.75 in.). Typical curve for 203.2 mm (8 in.) test coupon. Yield strength = 435 MPa (63.1 ksi); ultimate tensile strength =549 MPa (79.7 ksi); elongation = 26.3%. Composition: Fe-0.2C-l.32Mn-0.32Si-0.03Nb. UNS K12000
--.........
A36
560
~
ro a. :2 420 ui
'" ~
,
..J
280
140
20
0.04
0.08
0.12 Slrain, in.lin.
0.16
0.20
o
0.24
Comparison of structural steels with specified mínimum tensile properties. Typical yield strengths: A36 carbon steel, 248 MPa (36 ksi); A572 HSLA (grade 50), 345 MPa (50 ksi); A537, 276-414 MPa (40-60 ksi) (depends on class and thickness); A514, 620 or 689 MPa (90or 100 ksi) (depends on thickness) Source: R.L. Brockenbrough and B.G. Johnston, USS Steel Design Manual, Jan 1981. As pub1ished in Structural Alloys Handbook, Vol 3, CINDASlPurdue University, 1994, p 5
High-Strength Steel (HS)/133
HS.008 Various high-strength strudural steels, typical initial stress-strain curves
840
120
A514 100
(
-------
,,-
80
-
A537
560
40
A36
-
Source: R.L. Brockenbrough and B.G. Johnston, USS Steel Design Manual, Jan 1981. As published in Structural Alloys Handbook, Vol 3, CINDAS/Purdue University, 1994, p 5
-t::=
A572
~
280
20
140
5
10
15 20 Slrain, 0.001 in.lin.
25
30
100
HS.009 ASTM A514 and A517, grade A high-strength structural welded steel plate, typical tensile stressstrain curve
700
v
~
./
80
60
V
'00
-'"
/
V
40
/
/
420
ro
o..
::;;¡
280
V
140
2
ASTM A514 (high-strength plate suitable for welding); or ASTM A517 (pressure-vessel pI ate ). Typical composition, A514 grade A: Fe-O. 18C-0.95Mn-0.65Cr0.60Si-0.23Mo-0.lOZr. UNS K11856
560
/
"'
~
20
Comparison of structural steels with specified minimum tensile properties. Typical yield strengths: A36 carbon steel, 248 MPa (36 ksi); A572 HSLA (grade 50), 345 MPa (50 ksi); A537, 276--414 MPa (40-60 ksi) (depends on class and thickness); A514, 620 or 689 MPa (90or 100 ksi) (depends on thickness)
700
3 4 Slrain, 0.001 in.lin.
5
6
o
~
Source: "Evaluation of Great Lakes Steel Corp. Steel Alloy NAXTRA 100," Report A240, McDonnell Aircraft Corp., Dec 1963. As published in Structural Alloys Handbook, Vol 3, CINDAS/Purdue University, 1994, p 9
134/High-Strength Steel (HS)
120
100
I
80
/v--
I1/
V
20
6 O
4
~
iií
120
100
/
80
140
2
4
/
~
/ ,
/
840
Compressive yield strength = 876 MPa (127 ksi); modulus of elasticity in compression = 208 GPa (30.2 x 106 psi). Composition: varies with grade. UNS K11630, K11576, K11646
560 ~ :2
~ ~
420 iií
/
280
140
0.2
HS.Oll T-1 (ASTM A517, grades B, F, H) highstrength struclural steel pressure-vessel plate, typical compressive stress-strain curve
980
700
1/
'"
~ iií 60
/
1994, p 9
280
/ I
O
Source: "Evaluation of Great Lakes Steel Corp. Steel Alloy NAX1RA 100," Report A240, McDonnell Aircraft Corp., Dec 1963. As published in Structural Alloys Handbook, Vol 3, CINDASlPurdue University,
Strain, 0.001 inJin.
140
o
ro
a.
1/ 2
20
Test direction: left, longitudinal; right, transverse. Typical for Grade A from either ASTM A514 (high-strength plate suitable for welding), or ASTM A517 (pressure-vessel plates). Typical composition, A514 grade A: Fe-0.18C0.95Mn-0.65Cr-0.60Si-0.23Mo-0.IOZr. UNS K11856 :2
/
Strain, 0.001 inJin.
40
700
560
/
1/
g¡
HS.010 A514 and A517, grade A high-strength struclural steel plate, typical tensile stress-strain curves
420 rñ
/ /
40
/
840
0.4 Strain, %
0.6
Source: DJ. Carney, U.S. Steel Corp., personal communication witb W.J. Brown, 27 Jan 1972. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1103, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 8
High-Strength Steel (HS)/135
HS.012 T-l (ASTM A517, grades B, F, H) highstrength structural steel pressure-vessel plate, typical compressive tangent modulus curve
Compressive tangent modulus, GPa 56_ _ _ _ _1.,...12_ _ _ _-,16_8_ _ _---,221120 160°,--_ _ _----r
840
i20 ' - - - -
~
Compressive yield strength = 876 MPa (127 ksi); modulus of elasticity in compression =208 GPa (30.2 x 106 psi). Composition: varies with grade. UNS K11630, K11576, K11646
~
~ :::;: 80~----1----_+----~---1_1560 ~
00
~
~
00
Source: DJ. Carney, U.S. Steel Corp., personal communication with WJ. Brown, 27 Jan 1972. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1103, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 12
8 16 24 Compressive tangent modulus, 106 psi
250
200
.¡¡;
150
"'~" !I)
~
/
100
50
/
v/
/
/
v
V
1400
1050
~
700
350
4
6 8 Strain, 0.001 in.lin.
&.
:::;:
V 2
HS.013 AerMet 100 high-strength structural steel bar, typical tensile stress-strain curve at room temperature
1750
10
o
12
!
Bar thickness = ::;254 mm (::;10.000 in.). Test direction: longitudinal (L) and short transverse (ST). Reat treated to 1930-2068 MPa (280-300 ksi). Ramberg-Osgood parameters: n(L) = 6.8, n(ST) = 6.8. Composition: Fe0.23C-13.4Co-3.1Cr-1.2Mo-l1.1Ni Source: MIL-HDBK-5H, Dec 1998, p 2-110
136/High-Strength Steel (HS)
300
(
250
--
1---
--
HS.014 AerMet 100 high-strength structural steel bar, typical tensile stress-strain curve at room temperature
2100 ...
...........
.....
""
Test direction: longitudinal. Bar thickness = 127 mm (5.000 in.). Based on one heat. Heat treated to 1930-2068 MPa (280-300 ksi). Composition: Fe-0.23C-13.4Co3.1 Cr-l.2Mo-ll.INi
1750
",
200
,,
1400
,
'"
a.
\
Source: MIL-HDBK-5H, Dec 1998, p 2-112
:2
1050 ~-
iií 100
700
50
350
0.02
0.04
0.06
0.08 0.10 Slrain, inJin.
0.12
0.14
0.16
o
0.18
HS.015 AerMet 100 high-strength structural steel bar, typical tensile stress-strain curve (full range) at room temperature
2100
300
250
200
~
gf 150 ~
iií 100
50
o
/
O
I
/
/
/ v
/
/
...--
7
1400
'"
a.
1050
700
4
8 6 Slrain, 0.001 inJin.
l :2
350
2
Bar thickness = :::;254 mm (:::;10.000 in.). Test direction: longitudinal (L) and short transverse (ST). Heat treated to 1999-2137 MPa (290-310 ksi). Ramberg-Osgood parameters: n(L) = 15.9, n(ST) = 16.1. Composition: Fe0.23C-13.4Co-3.1Cr-l.2Mo-ll.1Ni
1750
10
Source: MIL-HDBK-5H, Dec 1998. p 2-113
High-Strength Steel (HS)/137
--..~
300
(
250
]
HS.016 AerMet 100 high-strength structural steel bar, typical tensile stress-strain curve (fuI! range) at room temperature
2450
350
2100
~.... Short
transverse
~t , , LOngitudin~
200
.;
Bar thickness = 127 mm (5.000 in.). Heat treated to 1999-2137 MPa (290--310 ksi). Based on one heat. Composition: Fe-0.23C-13.4Co-3.1Cr-1.2Mo-l1.1Ni
1750
Source: MIL-HDBK-5H, Dec 1998, p 2-115 1400 X
rf. :2
gi
~
~
1ií 150
10501ií
100
700
50
350
0.02
0.04
35
0.06
0.08 0.10 Strain. in./in.
250
~
200
~
gi 150 ~
1ií
50
0.14
Compressive tangent modulus, GPa 70 105 140
~
/
100
0.12
/
/
~
/
/
K
0.16
2
o
5
HS.017 AerMet 100 high-strength strudural steel bar, typical compressive stress-strain and compressive tangent modulus curves at room temperature
175
V
\
1400
rf.
:2
700
350
4
6 8 Strain, 0.001 in./in.
10
I 10 15 20 25 Compressive tangent modulus, 106 psi
Bar thickness = :-::;254 mm (:-::;10.000 in.). Test direction: longitudinal (L) and short transverse (ST). Heat treated to 1930--2068 MPa (280-300 ksi). Ramberg-Osgood parameters: n(L) = 11, n(ST) = 12. Composition: Fe0.23C-13.4Co-3.1Cr-1.2Mo-l1.1Ni
1750
1050
V
V
o
0.18
30
N
Source: MIL-HDBK-5H, Dec 1998, p 2-111
138/High-Strength Steel (HS)
Compressive tangent modulus, GPa 70 105 140
35
.......
300
/
"¡¡; 200
/
""
! en
150
100
50
/
/
90
70 60
/
/
I V
K
2100
1---...........
/
Bar thickness =:S:254 mm (:S:1O.000 in.). Test direction: 10ngitudinal(L) and short transverse (ST). Heat treated to 1999-2137 MPa (290-310 ksi). Ramberg-Osgood parameters: n(L) = 9.6, n(ST) = 13. Composition: Fe0.23C-13.4Co-3.1Cr-1.2Mo-l1.1Ni
1750
~
1400 lE
Source: MIL-HDBK-5H, Dec 1998, p 2-114
:<
en
2:!
1050 ¡¡¡
/
700
350
5
100
80
./
"'""-
250
HS.018 AerMet 100 high-strength structural steel bar, typical compressive stress-strain and compressive tangent modulus curves at room temperature
175
o
15 25 20 Strain, 0.001 in./in. Compressive tangent modulus, 106 psi 10
V-
......
-......
......
30
D~al
U.S.S. Phase 80
'\
\
HS.019 U.S.S. Dual-phase 80 high-strength low-alloy (HSLA) steel sheet, typical tensile stress-strain curve, compared with other steels
700 630
Ultimate tensile strength =660 MPa (95 ksi). Yield strength for coils = 340 MPa (50 ksi); for cut leve1ed lengths = 390 MPa (56 ksi). Composition: Fe-O. 15C1.75Mn-0.75Si-0.025P-0.020S-0.02V. AH maximum values except V which is the mínimum
560
SAE 980 490
-¡--
V
--......
'\
SAE 950
420
~
::?E
f\
350
uj (/)
~
¡¡¡ 40
280
30
210
20
140
10
70
5
15 25 10 20 Elongation in 2 in. (50 mm), %
30
Source: SA-352, Alloy Digest, Dec 1978
High-Strength Steel (HS)/139
HS.020 e5 dual-phase high-strength low-alloy (HSLA) steel sheet, log true flow stress-Iog true plastic strain curve
2.85
2.80
)
¿f 2.75 ::¡;
"'
~
"o 2.70
<;: Q)
.E
.3 2.65
./
2.60
V
2.55
~
-2.8
-2.5
/ I
I
I
Sheet thickness = 3 mm. Curve shows a double n behavior with the transition at about 0.01 strain. Composition: Fe-0.04C-1.28Si-1Mn-0.59Cr-OAOMo Source: M.R. Krishnadev et al., Formability of the Next Generation of High-Strength Low-Alloy Steels: The Effects of Low Temperatures and Processing Conditions, Formability of Metallic Materials-2000 A.D., STP 753, J.R. Newby and B.A. Niemeier, Ed., ASTM, 1982, P 253
/
~
-1.3
-2.2
-1.9 -1.6 Log true plastic strain
-1.0
HS.021 High-strength low-alloy (HSLA) steel sheet, comparison of nominal stress-strain curves for a variety of alloys
700 650
AU specimens hot roUed 1.99-2.53 mm thick. Specimen A: Si-Mn; yield strength (YS) = 519 MPa, strainhardening exponent (n) = 0.181. Specimen B: Si-Mn; YS = 458 MPa, n = 0.188. Specimen E: Si-Mn (heat treated); YS = 374 MPa, n = 0.223. Specimen F: Mn-Cr; YS = 428 MPa, n = 0.144. Specimen G: Mn-Cr; YS = 453 MPa, n = 0.147. Specimen 1: Mn-N; YS = 439 MPa, n = 0.154. Specimen J: Mn-N; YS = 484 MPa, n = 0.145. Specimen X: conventional Nb; YS = 500 MPa, n = 0.126. Specimen Z: commercial; YS = 300 MPa, n = 0.189
600
'"
550
a..
A J
::¡;
:i ~
500
xG B I F
~ 450
'E o z
400 E
Source: 1. Aoki, T. Horita, and T. Herai, Formability and Application of New Hot-Rolled High-Strength Sheet Steels, Formability of Metallic Materials-2000 A.D., STP 753, J.R. Newby and B.A. Niemeier, Ed., ASTM, 1982, p 239
350 300 250
Z
O
2
3
Nominal strain, %
.4
5
140/High-Strength Steel (HS)
HS.022 High-strength low-alloy (HSLA) steel sheet, comparison of tensile strength and elongation for a variety of alloys
45,---------,---------,---------,----------
AU specimens hot roUed 1.99-2.53 mm thick. Specimen 40r--,,-----+---------1---------~--------~
A: Si-Mn; yield strength (YS) = 519 MPa, elongation (e) = 37.5%. Specimen B: Si-Mn; YS = 458 MPa, e =
z
¿ ~
32.1 %. Specimen C: Mn (heat treated); YS = 333 MPa, e = 32.5%. Specimen D: Mn; YS = 467 MPa, e = 23.6%. Specimen E: Si-Mn; YS = 374 MPa, 34.3%. Specimen F: Mn-Cr; YS = 428 MPa, e =37.3%. Specimen G: Mn-Cr; YS = 453 MPa, e = 25.8%. Specimen H: Mn-Cr; YS = 395 MPa, e = 32.8%. Specimen 1: Mn-N; YS = 439 MPa, e = 29.0%. Specimen J: Mn-N; YS = 484 MPa, e = 21.6%. Specimen X: conventional Nb; YS = 500 MPa, e = 27.8%. Specimen Y: conventional Si-Mn; YS = 400 MPa, e = 31.5%. Specimen Z: commercial; YS = 300 MPa, e = 39.7%
35r---------+-------~~------~~--------~
o
:g Cl
c:
o
a;
$ 30~--------+-----~--1-----~~~~------~ tE!
• Dual phase steels O Canventianal steels
2~00
500
700
600
800
Source: 1. Aoki, T. Horita, and T. Herai, Forrnability and Application of New Hot-Rolled High-Strengtb Sheet Steels, Formability of Metallic Materials-2000 A.D., STP 753, J.R. Newby and B.A. Niemeier, Ed., ASTM, 1982, P 233
Tensile strength, MPa
2.90 1_--+------1_-----+-------1--------1:-::7'1"'----.1 2.85 1_--+------I_-----+------~"'----;;7!"---::--:;",c_-I 2.80 f-----I------+ro
a..
::;¡; uf 2. 75
~~""f'_=-------+=_.-c-_'__::
I/l
~
1ií ~
2. 70
I---'C:.-+---------,t,...~-
0= Q)
E Ol
2.65 I----+----.P""f'------+------+------I_---:Jt"'--
..:l
2.60
!----+-----+------+------+-------,-JrL-----
2.55
I----+-------+------+------+~----I------
2.50 1-----+-------i------+---;¡tf'--+-------I-------1 -2.5
-2.2
-1.9
-1.6
Lag true plastic strain
-1.3
-1.0
HS.023 High-strength low-alloy (HSLA) steel sheet, log true flow stress-Iog true plastic strain curves Experimental steels El, E4, E5, and E6 are compared with a commercial grade. El is a weathering steel, the other three are boron steels. C3 is a ferritic commercial HSLA Arctic steel with copper used for precipitation strengthening. Curve shows a double n behavior of the aUoys strengthened with copper. Strengthening with niobium produces single n behavior. Source: M.R. Krishnadev et al., Forrnability of the Next Generation of High-Strength Low-Alloy Steels: The Effects of Low Temperatures and Processing Conditions, Formability of Metallic Materials-2000 A.D., STP 753, J.R. Newby and B.A. Niemeier, Ed., ASTM, 1982, P 259
High-Strength Steel (HS)/141
300
L.-----~
250 .¡¡;
-'" 200 <ñ
HS.024 200 high-strength maraging steel, true stressstrain curve
2450
350
~
----
l----
--
Heat treatment: 816 oC (1500 °F), 1 h, air cooled, 482 oC (900°F), 3 h. Composition: Fe-18Ni-8.5Co-3.3Mo-0.2TiO.lAI
2100
1750
1400
~
u; ID
1050
~ 150
~'"
Souree: "18% Niekel Maraging Steels," Data Bulletin, International Niekel Co., Nov 1964, P 11. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1223, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 7
:i ~ g¡
~
100
700
50
350
0.2
0.4
0.6
0.8
o
1.0
True strain
320
HS.025 T-250 high-strength maraging steel bar, stress-strain curves at room and elevated temperatures
2240
75 °F (24 OC)
Bar thickness = 16.5 mm (0.65 in.). Heat treatment: 85% cold formed, 482 oC (900°F), 4 h. Composition: Fe18.5Ni-3.0Mo-1.4Ti-0.1AI (Co free)
1
305 °F (152 OC) 240
.¡¡; -'" <ñ
'" ~
1680
917 °F (492 oC)
'"
a.
:¡;
160
1120 <ñ
'" ~
-1500 °F (-816 OC) 80
560
~----~OL.4------~OL.8------~1L.2-------1L.6------~2.~
Strain, %
Souree: Personal eornmunieation from W.B. Austin, Hereules Ine., MeGregor, TX, 14 Nov 1989. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1228, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 14
142/High-Strength Steel (HS)
160
1120
140
980
120
840
HS.026 18Ni (250) high-strength maraging steel plate, monotonic and cyclic stress-strain curves
ro a. ::¡;
.¡¡; -'"
gf 100
700 Vi !I)
~
~
1ií 80
560
60
420
Test direction: longitudinal. Specimen size = 6.35 mm (0.25 in.) diam, 18.03 mm (0.71 in.) long. Heat treatment: austenitized 927 oC (1700 °P), solution annealed 804 oC (1480 °P). Strain rate = 6.097 mm/min (0.24 in./min). Test condition: monotonic tension, MT; monotonic compression, MC; cyc1ic tension, CT; cyc1ic compression, Ce. Composition: Pe-18Ni-7.5Co-5Mo-Ti-AI Source: W.B. Jones and J.e. Swearengen, Mechanical Stability of U1trahigh Strength Steels, Mater. Sci. Eng., Vol 41 (No. 2), Dec 1979, p 225-235. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1220, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 21
4ooL----o~,1-----0,~2----0~,3----~0.-4----0~,5----0~,-6--~0,i80 Plastic strain, %
300 280 260 240
200 180 160
~
V
/
V
1// 11 L
11
/'"
~
~ ,....-
v:-r:::: --~
".-
V
-
~
~
¡---
-
1960 1820
-
1680 ro a. ::¡; 1540 Vi
VcT
~
1400 1260
11
1120
0,1
0,2
0,3
004 Plastic strain, %
0.5
HS.027 18Ni (250) high-strength maraging steel plate, monotonic and cyclic stress-strain curves
2100
0,6
980
0,7
Test direction: longitudinal. Specimen size = 6.35 mm (0.25 in.) diam, 18.03 mm (0.71 in.) long. Heat treatment: austenitized 927 oC (1700 °P), solution annealed 804 oC (1480 °P), aged 482 oC (900 °P), 4 h, air cooled. Strain rate = 6.097 mm/min (0.24 in./min). Test condition: monotonic tension, MT; monotonic compression, MC; cyc1ic tension, CT; cyc1ic compression, CC. Composition: Pe-18Ni-7 .5Co-5Mo-Ti-Al Source: W,B. Jones and J.C. Swearengen, Mechanical Stability of U1trahigh Strength Steels, Mater. Sci. Eng" Vol 41 (No, 2), Dec 1979, p 225-235. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1220, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 21
High-Strength Steel (HS)/143
300 ,--.---,-----,---.--r---.,-----r---,-----, 2100 ~-~---_+---~~~~~--+_----~--~1960
~--~~--+---~---~---+_---~--~1400
~~~·----+---~---~---+_--~--~1260
HS.028 18Ni (250) high-strength maraging steel plate, monotonic and cyclic stress-strain curves Test direetion: longitudinaL Speeimen size = 6.35 mm (0.25 in.) diam, 18.03 mm (0.71 in.) long. Heat treatment: austenitized 927 oC (1700 °P), solution annealed 804 oC (1480 °P), aged 482 oC (900 °P), 8 h, air eooled. Strain rate = 6.097 mmlmin (0.24 in./min). Test eondition: monotonie tension, MT; monotonie eompression, MC; eyclie tension, CT; eyclie eompression, Ce. Composition: Pe-18Ni-7 .5Co-5Mo-Ti-Al Source: W.B. Jones and J.e. Swearengen, Mechanical Stability of Ultrabigh Strength Steels, Mater. Sci. Eng., Vol 41 (No. 2), Dec 1979, p 225-235. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1220, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 21
~--~----+--~---~---+----~--~1120
0.1
0.2
0.3
0.5
0.4
0.6
Plastic strain, %
300
250
200
r r-..
-I ~~
.¡;;
"'vi"
'" ~
HS.029 18Ni (250) high-strength maraging steel bar, stress-strain curve (fuI! range)
2100
Consumable vaeuum are remelted. Heat treatment: annealed 816 oC (1500 °P), 30 min, air eooled, aged 482 oC (900 °P), 3 h. Composition: Pe-18Ni-7.5Co-5MoTi-Al
1750
~
150
1400
~
8:.
:;
1050
li
~ 100
700
50
350
0.02
0.04
0.06 Strain, in.lin.
0.08
0.10
0.1~
Source: "Vascomax 18 Percent Nickel Ultrabigh Strength Maraging Steels," VASCO, Latrobe, PA, 1966. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1220, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 21
144/High-Strength Steel (HS)
HS.030 18Ni (250) high-strength maraging steel bar, tensile stress-strain curves at room and elevated temperatures
300 r----,----r----,----r----,----r----,----,2100
Room temperature 250
Air melted. Heat treatment: annealed 816 oC (1500 °F), 30 min, air eooled, aged 482 oC (900°F), 3 h. Composition: Fe-18Ni -7 .5Co-5Mo-Ti-Al
200
Source: "Vascomax 18 Percent Nicke1 Ultrahigh Strength Maraging Stee1s," VASCO, Latrobe, PA, 1966. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1220, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 43
8:
~
.;
'"~
::.:
150
1000 °F (538 OC) 1050 gf
~
i'ií
100
50
~---2~---4L----6L----8L---~lLO----1L2----1L4--~1; Strain, 0.001 in./in.
HS.031 18Ni (250) high-strength maraging steel bar, tensile stress-strain curves at room and elevated temperatures
300 r----,----r----,----r----,----r----,----, 2100
Consumable vaeuum are remelted. Heat treatment: annealed 816 oC (1500 °F), 30 min, air eooled, aged 482 oC (900 °P), 3 h. Composition: Pe-18Ni-7.5Co-5MoTi-Al ro
o..
::.: 1050 gf ~
i'ií ~---+--~~~~----+----+----+----+--~700
~~+----+----+----+----+----+--~ 350
2
4
6 8 10 Strain, 0.001 in./in.
12
14
Source: "Vascomax 18 Percent Nicke1 Ultrahigh Strength Maraging Stee1s," VASCO, Latrobe, PA, 1966. As pub1ished in Aerospace Structural Metals Handbook, Vol 1, Code 1220, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 44
High-Strength Steel (HS)/145
280r-·--~-----.-----.-----r-----.----~----'
HS.032 18Ni (250) high-strength maraging steel, typical tensile stress-strain curves at room, low, and elevated temperatures
1960
1680
Consumable vaeuum are remelted_ Reat treatment: mill annealed 816 oc (1500 °F), aged 482 oC (900°F), 3 h, Exposure time at test temperature = 0.5 h, Composition: Fe-18Ni-7.5Co-5Mo-Ti-Al
1400
·00 160~--~~--~----~~~~----~----~----1 1120~
::;:
-'"
g (J)
'" ~ 120~--~~--~~~~----~~~~~~~~~ 840 (J) 1000 "F (538 OC)
Source: A.E Hoenie, J.A. Lumm, RJ. Shelton, and RA Wallace, "Determination of Mechanical Property Design Values for 18NiCoMo 250 and 300 Grade Maraging Steels," AFML-TR-65-197, July 1965. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1220, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 44
560
280
2
4
6 8 Slrain. 0.001 in.lin.
10
12
O
14
280~-----r-~-.-----'-----r-----,----,-----,1960
Room lemperalure 240 1----f-----i-----I---+-------:;¡;;>~~:::::::¡::=---__l1680
200~--~~--~----_+--~~--~~----,_--__11400
HS.033 18Ni (250) high-strength maraging steel sheet, typical compressive stress-strain curves at room and elevated temperatures Consumable vaeuum are remelted. Reat treatment: mill annealed 816 oC (1500 °F), aged 482 oC (900°F), 3 h. Exposure time attest temperature = 0.5 h. Composition: Fe-18Ni-7 .5Co-5Mo-Ti-Al Source: AE Hoenie, J.A Lumm, RJ. Shelton, and RA. Wallace, "Determination of Mechanical Property Design Values for 18NiCoMo 250 and 300 Grade Maraging Steels," AFML-TR-65-197, July 1965. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1220, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 48
80~----1~ ~~----+_----~----~--~----_1560
40~_.~----_+----_+----~----4_----+_--__4280
L---~2L---~4----~6-----8L---~1-0----~12----~1¡
Slrain, 0.001 in./in.
146/High-Strength Steel (HS)
HS.034 18Ni (250) high-strength maraging steel bar, typical stress-strain curves at room, low, and elevated temperatures
300 ¡ - - - - , - - - - - , - - - - r - - - - r - - - , - - - - - - - , 2100
1----+----+-~7""_-+---I----f-----11750
1----+--~~~7""_-+-----I-------f------11400
ro ::;:
Il.
1-----+--#/,H--+-----+-----I-------f------1 1050 gf ~
(Ji
Test direetion: longitudinal. Consumable vaeuum are remelted. Heat treatment: annealed, aged 482 oC (900 °P). Exposure time at test temperature = 0.5 h. RT, room temperature. Ramberg-Osgood parameters: n(-100 °P) = 24, n(RT) = 26, n(300 °P) = 29, n(600 °P) = 26, n(800 °P) = 11, n(lOOO °P) = 11. Composition: Pe18Ni Source: MIL-HDBK-5H, Dec 1998, p 2-101
f--~~+-----4------+-----+----~---~350
8
4
Compressive langenl modulus, GPa 70 105 140
35
'-.... 250
1-----~
1'\
/
150
(Ji
50
175
- 1-----
/
.¡¡;
100
20
I
1400 ro
4
o
5
i ::;:
1050
700
O
o
Test direetion: longitudinal. Consumable vaeuum are remelted. Heat treatment: annealed, aged 482 oC (900 °P). Exposure time at test temperature = 0.5 h. RT, room temperature. Ramberg-Osgood parameter: n(RT, eompressive) = 22. Composition: Pe-18Ni
1750
Il.
1/
/ V
HS.035 18Ni (250) high-strength maraging steel bar, typical compressive stress-strain and tangent modulus curves at room and elevated temperatures
210 2100
~
V
200
""
12 16 Slrain, 0.001 in.lin.
350
8
16 12 Slrain, 0.001 in.lin.
20
I 15 20 25 10 Compressive langenl modulus, 106 psi
30
Source: MIL-HDBK-5H, Dec 1998, p 2-102
High-Strength Steel (HS)/147
HS.036 18Ni (250) high-strength maraging steel bar, typical tensile stress-strain curves at room and elevated temperatures
350 r-·----.-----,------~----,_----,_----,2450
300 ~----r_----+_----~=---+-----~----~2100
250
g¡
'"
200 ~----r_--_H~~--+_----+-----~----~1400& ::;;;
l'i
'" ~
en 150 ~----r_~~+_~--~1-00-0-·-F~(5-38-·-C~)~----~1050~
Consumable vaeuum are remelted. Heat treatment: Annealed, aged 482 oC (900°F). Exposure time at test temperature = 0.5 h. RT, room temperature. RambergOsgood parameters: n(-100 °F) = 19, n(RT) = 22, n(300 °F) = 17, n(600 °F) = 17, n(800 °F) = 12, n( 1000 °F) = 11. Composition: Fe-18Ni Source: MIL-HDBK-5H, Dec 1998, p 2-101
100 ~--~~~--+_----+_----+-----~----~700
50 ~~~+_----+_----+_----+-----~----~350
L-·____L -_ _ _ _
00
300
250
4
r
~
8
____
~
____
~
1'-,
,,
"
........
,
'
........
____
20
~O
24
......
'
~
l'i
~
HS.037 18Ni (280) high-strength maraging steel bar, typical tensile stress-strain curve at room temperature (fuI! range)
2100
200
~
____
12 16 Strain. 0.001 in.lin.
......
,
1750
Test direetion: longitudinal. Consumable vaeuum are remelted. Heat treatment: annealed, aged 482 oC (900°F). Composition: Fe-18Ni
1400
Source: MIL-HDBK-5H, Dec 1998, p 2-104
,
ro
D..
l ::;;;
150
1050
100
700
50
350
en
0.02
0.04
0.06 Strain, in.lin.
0.08
0.10
o
0.12
148/High-Strength Steel (HS)
35
........
300
250
.¡¡; 200
/
~ ~
100
/ o
Test direetion: longitudinal. Consumable vaeuum are remelted. Reat treatment: annealed, aged 482 oC (900 °P). Exposure time at test temperature = 0.5 h. RT, room temperature. Ramberg-Osgood parameter: n(RT, eompressive) = 21. Composition: Pe-18Ni
2100
v
"\
1750
1400
lE
Source: MIL-HDBK-5H, Oec 1998, p 2-103
::;;:
v
en 150
300
/
HS.038 18Ni (280) high-strength maraging steel bar, typical compressive stress-strain and tangent modulus curves at room temperature
175
-----r----- ---
x
50
Compressive tangent modulus, GPa 70 105 140
1050
~
Uí
700
/
350
4
8
12 16 Strain, 0.001 in.lin.
I 5
20
o
24
I
I
10 15 20 25 Compressive tangent modulus, 106 psi
30
HS.039 18Ni (300) high-strength maraging steel bar, typical stress-strain curve
2100
r~
250
..........
--........
200
Consumable vaeuum are remelted. Reat treatment: milI annealed 816 oC (1500 °P), 0.5 h, air eooled, aged 482 oC (900 °P), 3 h. Composition: Pe-18Ni-9Co-5MoTi-Al
1750
~ ..........
1400
...............
~ ~ 150
~
~
o.'"
::;;: 1050 ~
Uí 100
700
50
350
0.02
0.04
0.06 Strain, in.lin.
0.08
0.10
o
0.12
Source: "Vascomax 18 Percent Nickel Ultra High Strength Maraging Steels," VASCO, Latrobe, PA, 1966. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1225, CINOASIUSAF CROA Handbooks Operation, Purdue University, 1995, p 17
High-Strength Steel (HS)/149
320
2240
280
1960
HS.040 18Ni (300) high-strength maraging steel bar, tensile stress-strain curves at room, low, and elevated temperatures
Consumable vaeuum are remelted. Heat treatment: mill annealed 816 oC (1500 °F), 0.5 h, air eooled, aged 482 oC (900°F), 3 h. Exposure time at test temperature 0.5 h. Composition: Fe-18Ni-9Co-5Mo-Ti-AI
240
1400
200
ro ::;;
~
Il.
1120
IJ)
~
g¡ ~
¡¡¡
¡¡¡ 120
840
80
560
40
280
2
4
6 8 10 Strain, 0.001 in.lin.
12
14
=
Source: A.F. Hoenie, J.A. Lumm, RJ. Shelton, and R.A. Wallace, "Determination of Mechanical Property Design Values for l8Ni-Co-Mo 250 and 300 Grade Maraging Steels," AFML-TR-65-197, July 1965, P 65. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1225, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 27
0 16
HS.041 18N i (300) high-strength maraging steel bar, compressive stress-strain curves at room and elevated temperatures
320r----,----,----,----,----,----,----,----,2240 Room temperature ~--_r----r_--_r----r_--_+~~~--_+--__11960
Consumable vaeuum are remelted. Heat treatment: mill annealed 816 oC (1500 °F), 0.5 h, air eooled, aged 482 oC (900°F), 3 h. Exposure time at test temperature = 0.5 h. Composition: Fe-18Ni-9Co-5Mo-Ti-Al
r----r----t----+----~~~~~~~~~~1680
r----r----t----+~~~~_+----~~~~~1400
&.
l ::;;
1120 r----_r----~~_r----r_--_+----r_--_+--__1840
~--_r,.~r_--_r----r_--_+----r_--_+--__1560
~~~----r_--_r----r_--_+----r_--_+--__1280
~---~----~---L----~---L----L---~--~1~
Strain, 0.001 in.lin.
Source: A.F. Hoenie, J.A. Lumm, RJ. Shelton, and R.A. Wallace, "Determination of Mechanical Property Design Values for 18Ni-Co-Mo 250 and 300 Grade Maraging Steels," AFML-TR-65-197, July 1965, p 65. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1225, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 32
150/High-Strength Steel (HS)
HS.042 17-22A(S) ultrahigh-strength steel sheet, tensile stress-strain curves at room and elevated temperatures
12or---------,_------~,_--------,_------__,840
Test direction: longitudinal. Sheet thickness = 1.575 mm (0.062 in.). Heat treatment: 954 oC (1750 °P), 0.25 h, oil quenched, tempered 704 oC (1300 °P), 1 h. Exposures at temperature = 0.5-1000 h. Composition: Pe-0.3C-1.3Cr0.5Mo-0.25V UNS K14675
100~--------~--------~----~--~------__4700 I~-_+-Room
temperature
I
~
li
600°F (316 oC) 80 1------1---j'-=::::;;~=:;*';¡=:.:-.806 °F (427 OC) 400°F (204 oC)
560
~
I 60 f_--------t-H.'hI''---------=¡...-=7----1-00-0-0,F-'-(5-3-8-0C--')-------j 420
en~
Source: J.R. Kattus, J.B. Preston, and H.L. Lessley, "Deterrnination of Tensile, Compressive, Bearing, and Shear Properties of Sheet Steels at Elevated Temperatures," WADC Technical Report 58-365, Nov 1958. As published in Aerospace Structural M etals Handbook, Vol 1, Code 1210, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 8
! ~ i'ií
40f_-----h~f_--------f_--------f_-----------j280
20f_~~----f_--------f_--------f_-----------j140
°0L---------2~--------4~--------6~------~80
Strain, 0.001 in.lin.
HS.043 300M ultrahigh-strength steel bar, tensile stress-strain curves at room and low temperatures
320 ,...------,------,-------,_----,------,-----__, 2240
280
f-.-----+_-----+------t__----+_------l;;;~--=--¡
1960
240
¡........----+_----_+------~--____:#'~",=-t7l_----j
1680
Bar thickness = 25.4 mm (1 in.). Heat treatment: 871°C (1600 °P), 4 h, oil quenched, 316 oC (600 °P), 4 + 4 h. Composition: Pe-0.4C-l.8Ni-l.6Si-0.8Cr-0.4Mo-V
200¡........----+_----_+------~~~+-----_+------j1400
~
~'"
t)
.: en
li
160 f-.-----+_-----+--~~t__----+_-----+---------j 1120 .; m ~ 120f-.-----+_----.l.~----t__----+_-----+---------j840
80¡........----+_~~_+------~----+_----_+------j560
40¡........--~+_----_+------~----+_----_+----__4280
2
4
Strain, 0.001 in.lin.
Source: S.L. Pendleberry, R.E Simeng, and E.K. Walker, "Fracture Toughness and Crack Propagation of 300M Steel," Technical Report DS-68-18, Contract FA67-WA-1812, Lockheed-California Co., Aug 1968. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1217, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 25
High-Strength Steel (HS)/151
~
160
.¡¡; -'"
120
/
'"~
Uí
80
40
HS.044 9Ni-4Co-O.20C ultrahigh-strength steel plate, stress-strain curves with effect of tempering temperatures
1400
200
/
V
/
/
A
I--B 1120
V
840
560
V
8: ::;<
1
2
4 6 Strain. 0.001 in.lin.
o
10
8
1400
175
1225
150
1050
125
875
.¡¡; -'"
HS.045 9Ni-4Co-O.20C ultrahigh-strength forged steel bar, compressive stress-strain curves at room and elevated temperatures
'"
a.
::;<
gf 100
700
~
'"~
Uí
Uí 75
525
50
350
25
175
2
Source: A.H. Rosenstein, M.R. Oross, W.O. Schreitz, and O.A. Wacker, "Metallurgical Investigation of 9Ni-4Co-.2C Steel," Report 2678, Naval Research and Development, July 1968. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1221, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 47
280
200
O O
Plate thickness = 25.4 mm (1 in.). Consumable electrode vacuum process, carbon deoxidation (CEVM (C-deox)). Heat treatment: 913 oc (1675 °F), 1 h, air cooled, 843 oC (1550 °F), 1 h, oil quenched + tempered, 2 h, air cooled. Tempered at: curve A, 538 and 566 oC (1000 and 1050 °F); curve B, 482 oC (900°F). Composition: Fe-0.20C9Ni-4Co-Cr-Mo-V
6
Strain. 0.001 in.lin.
8
10
O
12
Test direction: transverse. Bar size = 57.15 x 152.4 x 213.36 mm (2.25 x 6 x 84 in.). Heat treatrnent: 899 ° C (1650°F), 1 h, air cooled, 816 oC (1500 °F), 1 h, oil quenched, tempered 552 oC (1025 °F), 6 h, air cooled. Composition: Fe-0.20C-9Ni-4Co-Cr-Mo-V Source: O.L. Deel and H. Mindlin, "Engineering Data on New Aerospace Structural Materials," AFML-TR-72-196, Vol n, Sept 1972. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1221, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 65
152/High-Strength Steel (HS)
HS.046 9Ni-4Co-O.20C ultrahigh-strength steel plate, typical tensile stress-strain curves at room and elevated temperatures
250 r - - - - , - - - - - , - - - - - - - - , - - - . - - - - - - , , - - - - - , 1750
~--+----4----~--_+--~~--~1400
~---+---+--+~_=~=+--_I------l1050
~
~
Test direction: longitudinal and long transverse. Plate thickness = 25.4-101.6 mm (1.000-4.000 in.). RT, room temperature. Exposure at temperature = 0.5 h. RambergOsgood parameters: n(RT) = 14, n(700 °F) = 13, n(900 °F) =7.7. Composition: Fe-9Ni-4Co-0.20C Source: MIL-HDBK-5H, Dec 1998, p 2-79
ui
~
r---7~---,r----T---+----r----1350
~
__~~--~----~----~-----L----~o 2
4
6
8
10
12
Strain, 0,001 in./in,
HS.047 9Ni-4Co-O.20C ultrahigh-strength steel plate, typical compressive stress-strain curves at room and elevated temperatures
Compressive tangent modulus, GPa
g
250 0;:-_ _3;:5~_-.:.70=___~10~5~---.:1:.;.40=---_.:.;17-=5--_=.;21 750
Test direction: longitudinal and long transverse. Plate thíckness = 25.4-101.6 mm (1.000-4.000 in.). RT, room temperature. Exposure at temperature =0.5 h. RambergOsgood parameters: n(RT) = 15, n(700 °F) = 12, n(900 °F) = 9.0. Composition: Fe-9Ni-4Co-0.20C
Room temperature
Room temperature
200 1---+-=~-=-+----+------b......".=-_I-------l1400
1050
150
ro
'00
C.
(1)
ui (1)
~
"'ui" jg rJ)
700
100
501--~~---+---~---+--~-I~--~350
00
2
4
6
O
8
10
12
20
25
30
Strain, 0,001 in./in,
I O
5
10
15
Compressive tangent modulus, 106 psi
~
Source: MIL-HDBK-5H, Dec 1998, p 2-79
High-Strength Steel (HS)/153
280
1960
240
-110°F (-79 OC) 1680
200
1400
1120/f ::;:
'00 160
-'"
''"" ~
1ñ
HS.048 9Ni-4Co-O.30C ultrahigh-strength forged steel billet, typical compressive stress-strain curves at various temperatures
120
840
80
560
40
280
2
4
6 8 Strain. 0.001 in./in.
''"" ~
1ñ
Source: D.F. Bulloch, T.W. Eichenberger, and J.L. Guthrie, "Evaluation of the Mechanical Properties of 9Ni-4Co Steel Forgings," AFML Contract AF 33615-67-C-1724, AFML TR 68-57, The Boeing Co., March 1968. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1221, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 65
O 12
10
HS.049 9Ni-4Co-O.30C ultrahigh-strength steel hand forging, typical compressive stress-strain and compressive tangent modulus curves at various temperatures
0 300 ;...---=r----=r---:,.'-------'..,.=--...:..¡..:'---'---;:.::.-_.:..r_-=;22~1 00
Porging thickness = 76.2 mm (3.000 in.). Por all directions. Exposure at temperature = 0.5 h. RT, room temperature. Ramberg-Osgood parameters: n(-110 °P) = 11, n(RT) = 12, n(300 °P) = 12, n(500 °P)= 10. Composition: Fe-9Ni-4Co-0.30C
*--,::;;;1,......,,"--+----11750
1400 ro
a. ::;: !--+----+........,Vú''I---+---=l'''''--=-+-'''''''''-+-Y..--I1050 gf
~
~---2~-~4~-~6--~8--1LO-~1L2-~14~~1~ Strain. 0.001 in./in.
O
4
8
I
I
I
12
16
20
24
Compressive tangent modulus. 106 psi
Test direction: longitudinal, long transverse, and short transverse. Billet size = 76.2 x 228.6 x 609.6 mm (3 x 9 x 24 in.). Consumable electrode vacuum process, carbon deoxidation (CEVM (C-deox». Heat treatment: 871927 oC (1600-1700 °P), 1 h, air cooled, 621 ± 14 oC (1150 ± 25°F), x h min, 843 ± 14 oC (1550 ± 25 °P), 1 h, oil quenched, -73 oC (-100 °P), 2 h, 510 ± 14 oC (950 ± 25 °P), 2 + 2 h, air cooled. Curves based on average of 3 heats.
28
32
Source: MIL-HDBK-5H, Dec 1998. p 2-87
154/High-Strength Steel (HS)
300
250
200
~ '1
-111J.cl -
~
V
--
p-
=-:z :::::
V70 'F (21
'C) ...... ~ / 300 'F (149 ~C)
-
¡..~ ....... ~............
...... " ......~ 500 'F (260 .C) . . .
~ ~ 150
~ .............
~
2100
HS.050 9Ni-4Co-O.30C ultrahigh-strength steel hand forging, typical tensile stress-strain curves (full range) at various temperatures
1750
Test direction: longitudinal. Forging thickness (3,000 in,), Exposure at temperature = 0,5 h . Composition: Fe-9Ni-4Co-0.30C
1400
~~ ......
iií
a.
"
:2
1050
50
350
0.06
0.08
0.10
0.12
0.14
0.16
~
~
'X
700
0.04
Source: MIL-HDBK-5H, Dec 1998, p 2-88 ro
100
0.02
= 76,2 mm
o
0.18
S!rain, in./in.
300
-111J.cl
250
0 ,-
~
200
'tú
f---
;::::.
--
C~
--~
!J)
i
~~I~"""
....... r-......"'-::~
500 'F (260 ·C)......
'iñ
"'
¿ 70 'F (21 'C) ' ........... k300 'F (149 'C)
"X
~~~ ~
2100
HS.051 9Ni-4Co-O.30C ultrahigh-strength steel hand forging, typical tensile stress-strain curves (full range) at various temperatures
1750
Test direction: long transverse. Forging thickness = 76.2 mm (3.000 in.). Exposure at temperature =0.5 h. Composition: Fe-9Ni-4Co-0.30C
1400
Source: MIL-HDBK-5H, Dec 1998, p 2-89
~ :2 1050 ~
150
iií 100
700
50
350
0.02
0.04
0.06
0.08
0.10
S!rain, in./in.
0.12
0.14
0.16
o
0.18
High-Strength Steel (HS)/155
300
250
~
200
lo"""
-I1LJ.Cl
...... --
-:::.~
¡..¡..-:::
".:zp °F (21°C)
HS.052 9Ni-4Co-O.30C ultrahigh-strength steel hand forging, typical tensile stress-strain curves (full range) at various temperatures
1750
Test direction: short transverse. Exposure at temperature =0.5 h. Composition: Fe-9Ni-4Co-0.30C
K~O °F (149 OC)
::::::Z::r-... "-
Source: MIL-HDBK-5H, Dec 1998, p 2-90 1400
-~::::::::: ........~
"
2100
500°F (260 OC) ......
........, ................
~~
lE
1050
100
700
50
350
0.02
0.04
0.06
0.08 0.10 Strain, in./in.
0.12
0.14
0.16
o
0.18
300
2100
250
1750
Longitudinal
200
J
/
HS.053 AF141 O ultrahigh-strength steel bar, typical tensile stress-strain curves at room temperature
Bar thickness = ::;107.95 mm (~.250 in.). RambergOsgood parameters: n(longitudinal) = 11, n(short transverse) = 9.1. UNS K92571
~ngitudinal
Source: MIL-HDBK-5H, Dec 1998, p 2-107
1400
VShort transverse
~
gf 150
/ /
~
1ií 100
50
tu
a.
/
::!:
1050 gf
~ 700
/
V
o
O
2
350
4
6 8 10 Strain, 0.001 in./in.
12
14
g ::!:
156/High-Strength Steel (HS)
300
o
Compressive tangent modulus, GPa 140 168 56 84 112
28
......
250
........
'"/
200 .¡¡; -'"
~
/
100
50
~c
196
V
~
Source: MIL-HDBK-5H, Dec 1998, p 2-107
/Sh~ transver~
/
1400
~~ ~
12
6 8 10 Strain, 0.001 inJin.
O
2
4
o
4
20 24 16 8 12 6 Compressive tangent modulus, 10 psi
~
I
14
I 28
32
HS.055 D6A, D6AC ultrahigh-strength steel plate, typical stress-strain curves at room and elevated temperature
1750
r /Í
200
150
Room temperature
-:J
~
i'ñ 100
I
!
1400
250 "F (121 "C)
1050
/I
m
700
350
4
ro o.. :2:
Ij 2
gf
350
250
50
'"
o..
:2:
1050
700
I
.¡¡; -'"
Bar thickness = ::;107.95 mm (::;4.250 in.). RambergOsgood parameters: n(longitudinal) = 9.0, n(short transverse) = 10. UNS K92571
1750
V
o
HS.054 AF141 O ultrahigh-strength steel bar, typical compressive stress-strain and compressive tangent modulus curves at room temperature
22~100
6
Strain, 0.001 inJin.
8
10
o
12
~
D6A, air melted; D6AC, consumable electrode vacuum melted (CVM). Heat treatment: 899 oc (1650 °F), 1 h, solution quenched, 204 oC (400°F), 10 min, air cooled, 604 oC (1120 °F), 4 h, air cooled. Composition: Fe0.46C-1.0Cr-1.0Mo-0.55Ni. UNS K24728 Source: Private Cornmunication, G.R. Sipple, General Motors Allison Division with W.F. Brown, Jr., 1965. As published in Aerospace Structural Metals Handbook, Vo11, Code 1213, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 34
High-Strength Steel (HS)/157
HS.056 Transformation-induced plasticity (TRIP) high-strength steel plate, engineering stress-strain curves at 25 oC of alloy deformed at 450 oC and martensite volume versus strain
300 (2100 l
250 (1750
ro a. 5
~
~'"
~
l~
./
200 (1400 l
150 ~ (1050 e "5j
r
--
-
(J)
e
.g> w
/' \1 100
~ /"
/
100 (700 l I
50 (350 l
I
I
I
I
...-.... ,,/
-
....
".... ",
,," "
I
f,-----
,,"
r2 75
----1V
..............
---
2V 25
Test direction: longitudinal. Curve 1: hot forged to 9.525 mm (0.375 in.). Plate then austenitized at 1200 oC, 3 h, in 4% H atmosphere, brine quenched, and flat roUed 80% to 1.905 mm (0.075 in.) at 450 oC. Curve 2: hot forged to 2.54 mm (0.10 in.) with similar treatment and reduced to 1.905 mm (0.075 in.) (20%) at 450 oC. Test specimen size = 3.175 x 1.905 x 25.4 mm (0.125 x 0.075 x 1 in.) gage length. Curve IV and 2V: vol% martensite versus strain curve for these alloys. Composition: Fe-9Cr-8Ni3Mn-3Si-4Mo-0.25C Source: G.R. Chanani, S.D. Antolovich, and w.w. Gerberich, Fatigue Crack Propagation in Trip Steels, Metal!. Trans., Vol 3, Oct 1972, P 2664
",'" ",
~
0.2
0.1
0.3
0.4
o
0.5
0.6
Strain
HS.057 Transformation-induced plasticity (TRIP) high-strength steel plate, engineering stress-strain curves at 25 oC of alloy deformed at 250 oC and martensite volume versus strain
300 (2100l
250 (1750
ro
a.
5
~
~
~
lf\- _
200 (1400 l
:z
~ 150 ~ (1050l r e "5j
----
------
(J)
e
.g> w
/
100 (700 l I
50 (350 l
O
I
I
I
,,"
,"'~
100
'2 75 ----1V
...."
"
"
",
"",'"
I I ",,,/
o
\1
-_."",,;
¿!.-- ----~ 0.1 0.2
",'"
...
- ---
2V 25
,,',,/
0.3 8train
0.4
0.5
o
0.6
Test direction: longitudinal. Curve 1: hot forged to 9.525 mm (0.375 in.). Plate then austenitized at 1200 oC, 3 h, in 4% H atmosphere, brine quenched, and flat rolled 80% to 1.905 mm (0.075 in.) at 250 oc. Curve 2: hot forged to 2.54 mm (0.10 in.) with similar treatment and reduced to 1.905 mm (0.075 in.) (20%) at 250 oc. Test specimen size = 3.175 x 1.905 x 25.4 mm (0.125 x 0.075 x 1 in.) gage length. Curve IV and 2V: vol% martensite versus strain curve for these alloys. Composition: Fe-9Cr8Ni-3Mn-3Si-4Mo-0.25C Source: G.R. Chanani, S.D. Antolovich, and W.W. Gerberich, Fatigue Crack Propagation in Trip Steels, Metal!. Trans., Vol 3, Oct 1972, P 2664
158/High-Strength Steel (HS)
HS.058 Fe-8.4Cr-8.4Ni transformation-induced plasticity (TRIP) high-strength steel strip, stress-strain and Hall voltage output-strain curves
TRIP steels can be used as strain sensors. (a) Roomtemperature stress-strain curves for specimens as wrought (0%), 20, 40, 60, and 80% reduction at 450 oC warm rolling. The magnetic properties of the material change irreversibly as austenite to martensite transformation occurs. (b) As the magnetic susceptibility changes dramatically, an accurate history of the peak strain can be derived from the Hall effect voltages shown on lower curves. Composition: Fe-8.4Cr-8.4Ni-2.1Mn-0.26C Source: J.S. Dunning, Characterization of TRIP Steels as Strain Monitor Materials, Microstructural Science, Vol 25, Proc. 30th Annual Technical Meeting of the Intemational Metallographic Society, IMS & ASM Intemational, July 1997, p 417
oo
0.05
0.10
0.15
0.20
0.25
0.30
Strain, m/m
(a)
3.6 80% 3.0
> S
-5o 1.6 f----+-+_-+.F--+--,J-----::~"--+_---+------j
ro I 1.2 f---+-----j4--:h.?--+---f-----+_---+------j
0.05 (b)
0.10
0.15 Strain, m/m
0.20
0.25
0.30
High-Strength Steel (HS)/159
1200,------,-----,------,------,------,------,
2
1000~----~----~------~-----+--~~~----~
800 ro
[l.
:2
'" '"
~
600
HS.059 Transformation-induced plasticity (TRIP) high-strength steel strip, true stress-strain curves with effect of niobium content
Strip tbickness = 2 mm. After 60% rolling reduction, tests were conducted with 0.8 mm sheet. Material was annealed, 780 oC, 180 s, transformed, 400 oC, 400 s. Niobium adds about 15 MPa strength/O.Ol % without significantly changing the shape of curve. Curve 1,0% Nb; curve 2, 0.02% Nb; curve 3, 0.04% Nb. Composition: Fe-O. 17C-1.4Mn-1.5Si + Nb as shown Source: K. Hulka, W. Bleck, and K. Papamantellos, Re1ationship between Heat Treatment Conditions, Microstrncture, and Properties of Niobiurn Microal1oyed TRIP Stee1, 41st Mechanical Working and Steel Processing Con! Proc., Vo137, Iron & Stee1 Society, 1999, p 75
Q)
~
400
200
0.10
0.05
0.20
0.15
0.25
0.30
True strain
Temperature, oC
1050
160
967
883
800
717
/
140
.1
120
/:
:2 .;
80
"lñ (])
~ 60 40 20
¡:7'
~
0.05
/
0.10
/
¡
r Va'" ;/
ro 100 Il..
~
550
633
0.15
0.20
This type of test examines transformation behavior. Note portion of curve with negative slope indicating material has softened. Other less dramatic slope changes exist and indicate other transformations. Cooling rate = 0.5 oC/s. Strain rate = 0.0003/s. Composition: steel A, Fe-0.22Cl.55Mn-1.55Si-0.035Nb-0.028AI (N, 20-40 ppm); steel B, Fe-O. 19C-1.54Mn-1.50Si-0.024AI (N, 20-40 ppm) Source: A.Z. Hanzaki, R. Pandi, P.D. Hadgson, and S. Yue, Continuous Cooling Deforrnation Testing of Stee1s, Metal/. Trans. A, Vol 24A, Dec 1993, p 2661
~
True strain
HS.060 Transformation-induced plasticity (TRIP) high-strength steel, continuous-cooling compression true stress-strain curves
0.25
0.30
160/High-Strength Steel (HS)
Temperature, 'C
967
883
800
717
550
633
This type of test examines transformation behavior. Note portion of curve with negative slope indicating material has softened. Other less dramatic slope changes exist and indicate other transformations. Cooling rate =0.5 oC/s. Strain rate = 0.0003/s. Composition: steel C, Fe-0.l45C1.50Mn-1.55Si-0.027Al (N, 20-40 ppm); steel D, Fe0.18C-1.50Mn-0.93Si-0.024Al (N, 20-40 ppm); steel E, Fe-0.21C-1.50Mn-1.10Si-0.027Al (N, 20-40 ppm)
140
IL
120
g:
1/
100
:2
¡i ~ 80
ft
t=" :>
60
40
20
~
/
0.05
P ~ 0.10
l)D ~ 1\. /·c
Source: AZ. Hanzaki, R. Pandi, P.D. Hadgson, and S. Yue, Continuous Cooling Deforrnation Testing of Steels, Metall. Trans. A, Vol 24A, Dec 1993, p 2661
?'
0.15 True strain
0.20
0.25
HS.061 Transformation-induced plasticity (TRIP) high-strength steel, continuous-cooling compression true stress-strain curves
0.30
5tainless 5teel (55)/161
Stainless Steel (SS) 200r---~r----.-----.-----r-----r----,-----,1400
- - Longitudinal - - Transverse
SS.OOl 201 stainless steel, stress-strain curves
showing effect of cold work Test direction: longitudinal and transverse. Composition: Fe-17Cr-6.5Mn-4.5Ni. UNS S20 100
150~----~--~-----+-.~~----~----~--~
1050
Source: P.D. Harvey, Engineering Properties of Stee/, American Society for Metals, 1982
875
~
~
¡i 100 ~----l----Il:"'~~~~-+=__-+,""",,~::I==---:-- 700 "'",10% Cold work
al
~
~
75~--~~~~~---+-----+----~----4---~525
350 ~~-4-----+----4-----t---~-----+--~175
L-----2L---~4----~6----~8-----1~0----~12~--~1; Strain, 0.001 in.lin.
SS.002 201 stainless steel sheet, tensile and
450
compressive stress-strain curves 400 350
4-:'"'
~
",.'
Q'
300
/ ' ... h' tY,/ t,/' ,
ro
~ 250 ui
'"
~ 200 rn
50
'
...
~
--- ---
VLT
-
¡..-'-'LC
v.' /
Six tests were made in each orientation on cold-rolled specimens. Curves: LT, longitudinal tensile; LC, longitudinal compressive; TT, transverse tensile; TC: transverse compressive. Elastic modulus: LT, 195.7 GPa; TT, 196.7 GPa; LC, 189.7 GPa; TC, 197.0 GPa. Yield strength (0.2%): LT, 359.6 MPa; TT, 383.1 MPa; LC, 295.8 MPa; TC, 380.2 MPa. Ultimate tensile strength: LT, 745 MPa; TI, 730 MPa. Composition: Fe-17Cr-6.5Mn4.5Ni. UNS S20100 Source: P. Van Der Merwe and G.J Van Den Berg, The Advantages of Using Cr-Mn Steels Instead of Cr-Ni Steels in Cold-Formed Design, High Manganese High Nitrogen Austenitic Stee/s, R.A. Lula, Ed., Conf. Proc., 10-15 Oct 1987 (Cincinnati, OH) and 2-4 Nov 1992 (Chicago, IL), ASM Intemational, 1992, p 129
~,
150 100
TI .......,.". ?r:pi'"~
T~
/'
/
1/
2
3
Strain x 0.001
4
5
162/Stainless Steel (SS)
200 180 160 140
./
/
120
A
•
A ~ /f
V
le
/
1260 1120
~1
980
/
840
60 40
~
V
V:I f
700 ,¡¡
'"~
20 0.2
!
f f
f f
140
0.8 0.6 Strain, in./in. (2 in. gage)
1.0
1.2
o
1.4
3 ______
400
V
./
350
,/
~ 250
~ 200
(/)
b/--
150
50
~
r-
-
/'
:i
100
2
/ / / -----
al
/
1/
/
Source: E.R. Cunningham, Cold Forming Stainless Steels and Other Specialty Grades, Source Book on Cold Forming, American Society for Metals, 1975, p 126
280
450
300
iñ
Comparison of true stress-strain for coiled strips of ferritic (434) and austenitic (201, 301) alloys. Higher work-hardening rates of austenitic grades indicate improved deep-drawing capability. Localized reduction, necking, is retarded. Vertical dashed lines are the points of maximum uniform strain, aboye which the localized deformation takes place. The load corresponding to this point is the maximum load .
420
I f f f
0.4
560
f f f
f f f
al
a.
:2
4~4
80
SS.003 201, 301, 434 stainless steel sheet, stressstrain curves used in case study
1400
----
...!-~
1/
2
3
Strain x 0.001
4
5
SS.004 201-1, 201-2, 301, 304 stainless steel sheet, compressive stress-strain curves for various annealed alloys Test direction: longitudinal. Curve 1, types 201-1, 301, 304. Curve 2, type 201-2. Curve 3, type 205. lnitial elastic modulus = 193 GPa, all curves. Longitudinal compressive yield strength: type 201-1, 185 MPa; type 201-2,280 MPa; type 205, 405 MPa; type 301, 185 MPa; type 304, 185 MPa Source: P. Van Der Merwe and G.J Van Den Berg, The Advantages of Using Cr-Mn Steels Instead of Cr-Ni Steels in Cold-Formed Design, High Manganese High Nitrogen Austenitic Steels, KA. Lula, Ed., Conf. Prac., 10-15 Oct 1987 (Cincinnati, OH) and 2-4 Nov 1992 (Chicago, IL), ASM Intemational, 1992, p 130
Stainless Steel (SS)/163
55.005 202 (UN5 520200) annealed stainless steel bar, stress-strain curves at room and low temperatures
300r---~--'--r-r~--'----r-.-'-r---r---'--r-,,2100
200~------------+--------------r--~~7-----~
Bar diameter = 6.426 mm (0.253 in.). Composition: Fe18Cr-8.75Mn-5Ni. UNS S20200
100~------~--~~~----------~----~-------1700
~
ro
~
gf 80
560 gf
~
Souree: CJ. Gunter and R.P. Reed, "Meehanieal Properties of Four Austenitie Stainless Steels at Temperatures between 300 and 20 K," National Bureau of Standards, Cryogenie Engineering Laboratory, 1960. As published in Structural Alloys Handbook, Vol 2, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1994, p 51
~
80°F (27 OC) 420 ¡¡¡
60
~F-~~------+---·~---------r------------~280
~L-----------+--------------r------------~210
0.1 Strain, in.lin.
80
Iitudina~t----V
Lon 70
1//
560
SS.006 21-6-9 annealed stainless steel, stress-strain curves
490
Test direction: longitudinal and transverse. Composition: Fe-Iow C-20.25Cr-9Mn-6.5Ni-0.28N. UNS S21900
420
Souree: "Armeo 21-6-9 Stainless Steel," Produet Data Broehure S-26e, Armeo Steel Corp., Baltimore, MD, Apri11969. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1314, CINDAS/ USAF CRDA Handbooks Operation, Purdue University, 1995, p 18
,/ Transverse
60
)~'
50
30
20
10
/
/
/
/
350
/ V
ro [L ::¡; 280 ui Ul
~
en 210 140 70
2
3
Strain, 0.001 in./in.
4
164/Stainless Steel (SS)
80
--II -----k::::
70
50
/
/t V -
30
10
-
SS.007 21-6-9 annealed stainless steel sheet, stressstrain curves at room and elevated temperatures
490
Test direction: longitudinal. Composition: Fe-20.25Cr9Mn-6.5Ni-O.28N. UNS S21900
420
Source: O. Deel, P. Ruff, and H. Mindlin, "Engineering Data on New Aerospace Structural Materials;' AFML TR-73-1l4, AD:762305, Battelle Columbus Laboratories, Columbus, OH, June 1973. As published in Structural Alloys Handbook, Vol 2, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1994, p 49
Room temperature
/'
60
20
-
560
r
350
- 700 0,F (371°C) 900°F (482 OC)
280
400
ro
(204 OC)
o..
:2
~
210
V
140
I
70
/
2
4
8 6 Strain, 0.001 in./in.
10
SS.008 21-6-9 annealed stainless steel sheet, stressstrain curves at room and elevated temperatures
70,------,------,------,------,-------,-----,490 Room temperature
Test direction: transverse. Composition: Fe-20.25Cr9Mn-6.5Ni-0.28N. UNS S21900
60~-----+~----+------+------1-------~----~420
50~----~----~------~----_+------+_----~350
400°F (204 OC) .¡¡;
40
""
_-..-_ 700°F (371°C) I_ _- - ¡ - - 900 (482 OC)
(J)
:2
+
~
.......~+------+------+-----f___--~ 280 &
f.----+-+~
gf
~
210 úl
30
20f___~~_r---+_-----+------i-----~------~140
10~~--_r------+------+------~----~------~70
L------2L-----~4------~6------~8------1~0----~1~ Strain, 0.001 in./in.
Source: O. Deel, P. Ruff, and H. Mindlin, "Engineering Data on New Aerospace Structural Materials," AFML TR-73-114, AD:762305, Battelle Columbus Laboratories, Columbus, OH, June 1973. As published in Structural Alloys Handbook, Vol 2, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1994, p 50
Slainless Sleel (SS)/165
225 200 175 150
SS.009 21-6-9 stainless steel, stress-strain curves at room and low temperatures
1750
250 /'
I
//
h
x -4¿2 °F (-26b OC) 1575
\ /"'l
Composition: Pe-20.25Cr-9Mn-6.5Ni-0.28N. UNS S21900
-320 1°F (-196 OC)
...-
1400 1225
f/
1050", o.. :2
875
.----
100 75 50
/"
Room temperature
"'
~-
~
700
1*
Source: M.B. Kasen, R.E. Schramm, and D.T. Read, "Semi-Annual Report of Materials Research in Support of Super Conducting Machinery," ARPA Order-2569, AD-B063554, National Bureau of Standards, Cryogenics Division, Boulder, CO, Oct 1976. As published in Structural Alloys Handbook, Vol 2, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1994, p 50
525 350 175
25
0.1
0.3
0.2
0.5
0.4
0.6
o
0.7
Strain
250
¿;.
200
150 ~
?
~-'2L <-l.e)
~
-
,-
-~
-107°F (-77 OC)
1050",
...........
--- ---
o.. :2
-T' ~ \
"Room temperature
~
50
'"
700
350
10
20
Specimens annealed 1050 oC (1922 °P), 2 h. Hydrogen charged 573 oC (1063 °P), 14 days, 69 MPa (10 ksi) H2 • Strain rate =0.00045/s. Composition: Pe-low C-20.25Cr9Mn-6.5Ni-0.28N. UNS S21904
1400
~ --ro IY' ," ~ 100 íI" V
'"~
---- H, charged
l'
/
SS.010 21-6-9 stainless steel plate, stress-strain behavior of uncharged and hydrogen-charged alloys at room and low temperatures
1750 -1_ _ 1unCha1rged
30
40
50 Strain, %
60
70
80
90
~
Source: J .H. Holbrook and AJ. West, The Effect of Temperature and Strain Rate on the Tensile Properties of Hydrogen-Charged 304L, 21-6-9, and JBK 75, Proc. Hydrogen Effects in Metals, 26-31 Aug 1980 (Moran, WY), TMS/AIME, 1981, P 655-663. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1314, CINDAS/ USAF CRDA Handbooks Operation, Purdue University, 1995, p 22
166/Stainless Steel (SS)
180
1260
SS.Oll 301 stainless steel sheet and strip, stressstrain curves at different tempers
160
1120
Test direction: longitudinal and transverse. Curves: LT, longitudinal tensile; LC, longitudinal compressive; TT, transverse tensile; TC: transverse compressive. Composition: Fe-18Cr-8Ni. UNS S30100
140 Y,
hard
120 '00
-'"
'"~
Cií
980 840
100
Y. hard TI
700
g¡ t\l
80
560 C/) ~
60
420 Annealed
Le
Souree: M. Watter and R.A. Lineoln, "Strength of Stainless Steel Struetural Members as Funetion of Design," Allegheny Ludlum Steel Corp., 1950. As published in Aerospace Structural Metals Handbook, Vo12, Code 1301, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 22
280 140
o Strain, 0.001 in.lin.
SS.012 301 stainless steel sheet, stress-strain curves at different tempers
280,------,------,--, .------,-------,---,1960
Test direction: longitudinal and transverse. Sheet and strip cold roUed to fuU hard and extra-hard tempers. Curves: LT, longitudinal tensile; LC, longitudinal compressive; TT, transverse tensile; TC: transverse compressive. Composition: Fe-18Cr-8Ni. UNS S30100
~----~------~--~1680
~----~------~_?~1400
~ 160~----~~~--~~-4
~----~----~~---;1120~
:2
g
~
C/)120~-----H~~--~--~
~----~~~~~---;840
~--~~------+-~560
~~---r------+-~280
L -_ _ _ _-L______
4 8 Strain, 0.001 in.lin.
L-~o
o Strain, 0.001 in.lin.
~
Cií
Souree: "High Strength Cold Rolled Stainless Steels," Data Sheet, Allegheny Ludlum Steel Corp., 1958. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1301, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 22
5tainless 5teel (55)/167
SS.013 301 stainless steel sheet, tensile stress-strain curves at various temperatures
2oor-------~------,-------,_------_r------_,1400
Average of longitudinal and transverse. Top: 0.508 mm (0.020 in.) sheet full hard, 40% reduction. Bottom: 0.813 mm (0.032 in.) sheet full hard, stress relief 427 oC (800°F), 8 h. Composition: Fe-18Cr-8Ni. UNS S30100
160~------+-------4-------~-----7~------~1120
400°F (204 oC
I
Source: "High Strength Cold Rolled Stainless Steels;' Data Sheet, Allegheny Ludlum Steel Corp., 1958. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1301, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 30
600 °F (316 oC)
40r---__~~~~~~------_r------_r------_1280
~------~------~-------L-------L
______
~O
r-------~------,_------,_------_r------~1400
840
c.. '"
·00 -'" ,¡;
:2
'" ~
~
,¡;
'"
560
4 6 Strain, 0.001 in.lin.
8
en
168/Stainless Steel (SS)
28o,---------,---------,---------,---------,196o
SS.014 301 stainless steel sheet, tensile stress-strain curves at various temperatures and exposure times 60% cold-reduced sheet, 1.27 mm (0.050 in.) thick. Composition: Fe-18Cr-8Ni. UNS S30100
200~--------~--------~~~~~--~~~~--~1400
I----------+---------~
Source: M.M. Lemcoe and A. Trevim, Jr., "Detennination of the Effects of Elevated Temperature Materials Properties of Several High Temperature Alloys," ASD-TDR-61-529, June 1962. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1301, CINDAS/ USAF CRDA Handbooks Operation, Purdue University, 1995, p 30
560
40~~~~--+_--------+_--------_r--------~280
°0~--------~4----------~8----------1L2--------~1~
Strain, 0.001 in.lin.
SS.015 301 stainless steel sheet, tensile stress-strain curves at room and low temperatures
280,---------,----------,---------,---------, 1960 -420 °F (-251°C)
Extra hard cold-rolled sheet, 1.524 mm (0.060 in.) thick. Composition: Fe-18Cr-8Ni. UNS S30100
1680
200~--------+-------~~--~~--~--~--~~
1400
~160~--------+---~--~~~------~--------~ 1120~
:2
¡i
g
'" IJ)
ro120~--------~~------_r--------_i--------~
840
80~----~~~--------~--------~------~
560
40~-h~----~--------~--------~------~
280
OL---------L---------L---------~------~
O
4
8
Strain, 0.001 in.lin.
12
0 16
~
Source: L.P. Rue, J.E. Campbell, and W.F. Sirnmons, "The Evaluation and the Effects of Very Low Temperatures on the Properties of Aircraft and Missile Metals," WADD-TR-60-254, Feb 1960. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1301, CINDAS/ USAF CRDA Handbooks Operation, Purdue University, 1995, p 31
5tainless 5teel (55)/169
SS.016 301 stainless steel sheet, tensile stress-strain curves at room and elevated temperatures
2240
320
Average of longitudinal and transverse. Top: sheet extra hard, 65% reduction. Bottom: extra hard, stress relief 399 oc (750 °P), 8 h. Composition: Pe-18Cr-8Ni. UNS S30100
Room temperature 1680
240
ro
.¡;; -'" vi en 160
c..
:; 1120
~
:Z ~
éñ 560
80 1200 'F (649 'C)
O
O
2240
320
Room temperature 1680
240
ro
c..
~
:;
vi en 160
1120
~
:Z
~
éñ
1000 'F (538 'C) 560
80
I
1200 'F (649 'C)
00
2
4 6 Straín, 0.001 ín./ín.
8
O 10
Source: "High Strength Cold Rolled Stainless Steels," Data Sheet, Allegheny Ludlum Steel Corp., 1958. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1301, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 31
170/Stainless Steel (SS)
24or-------,-------~------~------~------~1680
1120
160
~
1 2 3 54
u) U)
~
160
ro
3
u)
4
u)
U)
~
~ en éñ
O
o
3 .¡¡;
4 5
""u) '"~
O
1680
240
3
1120
(a)
4 6 Strain, 0.001 in.lin.
8
4
""u) u) '" éñ'"~
10
~
1120
.¡¡;
:;;;
_ _ _ _ _ _L __ _ _ _~~_ _ _ _~_ _ _ _ _ _~_ _ _ _ _ _~O
2
ro
o..
560
~
u)
'" ~
1 2
éñ
80
ro
o..
:;;;
560
80
1 2 160
1120
5
O
1680
240
2
o.. :;;; ~ U)
560
80
240r-------~------,_------_r------_,------_.1680
ro
o..
:;;;
5
u) CJ)
~
560
80
en
~------L-----~------~------~------~O
2
(b)
4 6 Strain, 0.001 in.lin.
8
10
55.017 301 stainless steel sheet, compressive stress-strain curves at room and elevated temperatures (a) Full hard sheet. Top: longitudinal; bottom: transverse. (b) Full hard sheet, stress relief 427 oC (800°F), 8 h. Top: longitudinal; bottom: transverse. Curve 1, room temperature; curve 2, 204 oC (400°F); curve 3, 316 oC (600°F); curve 4,427 oC (800°F); curve 5, 538 oC (1000 °F). Composition: Fe-18Cr-8Ni. UNS S30100 Source: "High Strength Cold Rolled Stainless Steels," Data Sheet, Allegheny Ludlum Steel Corp., 1958. As published in Structural Alloys Handbook, Vol 2, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1994, p 30
Stainless Steel (SS)/171
,.----,-----,-------¡----,----,1680
2 4 o , . - - - - , . - - - - , . - - - - - , - - - - - - - ¡ - - - - - - , 1680
.¡¡;
1120
160
'"
a.
-"
::¡;
ui en
ui en
~
~
Iñ
560
80
en
1120
.¡¡; ui en
ui en
~
~
560
O~·--~----L---~------L----~O
~---L----L--_~
3 2 0 . . . - - - - - , . - - - - - , - - - - - , - - - - - - - ¡ - - - - , 2240
.¡¡;
'"
g 160
1120:
~
en
~
Iñ
80
560
~---2L----4L---~6~--~8---~1~ Strain, 0.001 in./in.
_ _ _~_ _ _~O
1680
240
a.
-"
Iñ
320 , . - - - - , - - - - , - - - - - , - - - - - - - ¡ - - - - , 2240
1680
240
'"
a.
::¡;
-"
'"
~
a. ::¡; 1120 ui
g 160
!
en
~ 80
560
~---2L---~4~--~6---~8---~1~
(b)
Strain, 0.001 in./in.
SS.018 301 stainless steel sheet, compressive stress-strain curves at room and elevated temperatures (a) Extra hard sheet. Top: longitudinal; bottom: transverse. (b) Extra hard sheet, stress relief 399 oC (750 °P), 8 h. Top: longitudinal; bottom: transverse. Curve 1, room temperature; curve 2, 204 oC (400 °P); curve 3, 316 oC (600 °P); curve 4, 427 oC (800 °P); curve 5, 538 oC (1000 OP). Composition: Pe-18Cr-8Ni. UNS S30100 Source: "High Strength Cold Rolled Stainless Steels." Data Sheet, Allegheny Ludlum Steel Corp., 1958. As published in Structural Alloys Handbook, Vol 2, CINDAS/USAF CROA Handbooks Operation, Purdue University, 1994, p 30
172/Stainless Steel (SS)
240
V
/ V/
200
;/ /:V
160 ~
gf 120
~
en 80
40
VV/ J
Vl' V/ V / V/ /
;/
1680
SS.019 301 stainless steel sheet, room-temperature tensile stress-strain curves with varying amounts of cold work prior to stress-relief annealing
1400
Test direction: longitudinal. Curve 1: 50% cold reduction (CR), 399 OC (750 °P), 1 h, air cooled. Curve 2: 60% CR, 399 OC (750 °P), 1 h, AC. Curve 3: 70% CR, 399 OC (750 °P), 1 h, AC. Composition of heat: Pe-O.l1C17.9Cr-6.72Ni-0.56Mn-0.27Si. UNS S30100
1120 ti!
o.. :2
840 '"
~
éñ
Source: "Data Sheet 14-10256-301," Allegheny Ludlum Steel Corp., Pittsburgh, PA. As published in Structural Alloys Handbook, Vol 2, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1994, p 28
560
280
o
Strain, 0.001 in.lin.
2oo.-----,------,-----,------,-----,------,14oo
~----+------*----~------~----~r__,-i1120
SS.020 301 stainless steel sheet, elevatedtemperature tensile stress-strain curves with different stress-relief annealing Test direction: longitudinal. Curves on left, 65% cold reduction (CR), 482 oC (900 °P), 2 h, air cooled (AC). Curves on right, 65% CR, 399 oC (750 °P), 2 h, AC. Composition of heat: Pe-0.11 C-17 .25Cr-7.00Ni-0.57Mn0.50Si. UNS S30100 Source: "Data Sheet 19-101656-301," Allegheny Ludlum Steel Corp., Pittsburgh, PA. As published in Structural Alloys Handbook, Vol 2, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1994, p 29
~.w~+-----~----~--~--T_----~-----i280
~----+------L----~~----~----~----~O
Strain, 0.001 in.lin.
5tainless 5teel (55)/173
55.021 301 %-hard stainless steel sheet, typical tensile and compressive stress-strain curves
14or-------,-------,-------,-~~--_r------~980
Test direction: longitudinal and transverse. Half-hard sheet in as-roUed condition shows its anisotropic behavior. Curves: LT, longitudinal tensile; LC, longitudinal compressive; TI, transverse tensile; TC: transverse compressive. Composition: Fe-18Cr-8Ni. UNS S30100
120~----~-+_------~---~~7F~~--_r------_4840
100~------+_------~~~--~--~~_r------_4700
g¡
80 ~------_I_--_U_,1'----+7?-----+------+------- 560
~
:2
~ ~
rñ
Source: Technical Blue Sheet, www.alleghenyludlum.com. Allegheny Ludlum Steel Corp., 2002, P 3
~
Woo
~~
40~--~~~------~-------~------_r------_1280
20~~----~------~-------~------_r------_1140
2
4
6
8
Strain, 0.001 inJin.
55.022 301 %-hard stainless steel sheet, typical tensile and compressive stress-strain curves
140,-------,-------,------,-------,-------, 980 TI LT
g¡
120~------+_------~--~~~~~~_+------_4
840
100~------+_----~~L-----+------_+------_4
700
80~------+_...~--~------~------_+------~
560 ~ :2
gf
ui (J)
~
~ 60r-----~F_------+_------~------_r------_1 420
40~--~--+_------+-------~------_r------_1280
~~----+-------4-------+------+------~140
~~-----~2------~4------~6~------8L-----~1~ Strain, 0.001 inJin.
~
~
Test direction: longitudinal and transverse. Stress relief 538 oC (1000 °F), 2 h. A more isotropic nature and improved load-carrying ability is noted. This is especially true if longitudinal compression controls the designo Curves: LT, longitudinal tensile; LC, longitudinal compressive; TI, transverse tensile; TC: transverse compressive. Composition: Fe-18Cr-8Ni. UNS S30100 Source: Technical Blue Sheet, www.alleghenyludlum.com. Allegheny Ludlum Steel Corp., 2002, P 3
174/5tainless 5teel (SS)
SS.023 301 %-hard stainless steel sheet, typical tensile stress-strain curves
1400
200
Test direction: longitudinal (L) and long transverse (LT). Ramberg-Osgood parameters: n(L) = 4.5; n(LT) = 5.9. Composition: Fe-18Cr-8Ni. UNS S30100
1120
160
LOn[~~ Long transverse
120 '¡ji .:.:;
(/i
'"~
Uí
80
40
Source: MIL-HDBK-5H, Dec 1998, p 2-224
j
I
V
2
V ~
840 ro a.
::2: ui
560
~ Uí
280
4
6
10
8
o
12
Strain, 0.001 in./in.
SS.024 301 %-hard slainless sleel sheet, typical compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
200 0; -_ _..:,35-=--_ _,70-=--_ _1..,..0_5_ _ _1,40_ _ _17,5_ _-21 . 9400
Test direction: longitudinal (L) and long transverse (LT). Ramberg-Osgood parameters: n(L) = 3.4; n(LT) = 4.3. Composition: Fe-18Cr-8Ni. UNS S30100
160~---~~~_4------+------+------r-----~1120
Source: MIL-HDBK-5H, Dec 1998, p 2-224
840 ro a.
120 '¡ji .:.:;
::2:
ui
ui (J)
'"~
~
Uí 560
80
Strain, 0.001 in./in.
o
5
10
I 15
25
20 6
Compressive tangent modulus, 10 psi
30
Uí
Stainless Steel (SS)/175
LOngit~
90
/'
""!Ji Ul
~ 60
30
Test direction: longitudinal (L) and long transverse (LT). Ramberg-Osgood parameters: n(L) = 3.9; n(LT) = 5.8. Composition: Fe-18Cr-8Ni. UNS S30100
840
120
.¡¡;
SS.025 301 1,4-hard stainless steel sheet, typical tensile stress-strain curves
1050
150
I
V
V
Source: MIL-HDBK-5H, Dec 1998, p 2-221
~ng transverse 630
V
'"
420
~
2
o..'"
:2 !Ji
~
210
4
6 8 Strain, 0.001 in.lin.
10
o
12
SS.026 301 1,4-hard stainless steel sheet, typical compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
15oor----~3r5----_,70----~1T05~--~14rO~--~17r5----~21~050
Test direction: longitudinal (L) and long transverse (LT). Ramberg-Osgood parameters: n(L) = 3.8; n(LT) = 4.8. Composition: Fe-18Cr-8Ni. UNS S30100
~----~--~~------+-----~----~~--~840
Source: MIL-HDBK-5H, Dec 1998, p 2-221 630 '00
""!Ji
o..'"
:2 !Ji
Ul
~
'"~
iñ 420
8
10
o 12
20
25
30
Strain, 0.001 in.lin.
I O
5
10
I 15
Compressive tangent modulus, 106 psi
iñ
176/5tainless 5teel (SS)
Test direction: longitudinal (L) and long transverse (LT). Ramberg-Osgood parameters: n(L) = 4.7; n(LT) = 5.4. Composition: Fe-18Cr-8Ni. UNS S30100
1400
200
.¡¡;
SS.027 301 %-hard stainless steel sheet, typical tensile stress-strain curves
1750
250
Source: MIL-HDBK-5H, Dec 1998, p 2-225
.,..V
150
1050",
Lo"'fl~
"'cñ" !/)
~
O-
::¡; cñ !/)
¿ngitudinal
Ci5 100
50
V
~
700
/ 2
Ci5
350
4
10
6 8 Strain, 0.001 in./in.
o
12
SS.028 301 %-hard stainless steel sheet, typical compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
250 or-_ _,35_ _ _7To_ _ _ 1or5_ _ _1--¡4_o_ _ _1T75_ _--..,21~750
200
1-----t----'''-+---t----t------t--::7''~----i
Test direction: longitudinal (L) and long transverse (LT). Ramberg-Osgood parameters: n(L) = 3.5; n(LT) =4.7. Composition: Fe-18Cr-8Ni. UNS S30100
1400
Source: MIL-HDBK-5H, Dec 1998, p 2-225
1050
150
~
'"
O-
::¡; cñ !/)
cñ !/)
~
700
100
2
o 12
4 Strain, 0.001 in./in. I
O
5
10
15
25
20 6
Compressive tangent modulus, 10 psi
30
~
Stainless Steel (SS)/177
160 , - - - , - - - - . . , - - - - - , - - - - - - , - - - - - - , - - - - , 1120
SS.029 301 annealed stainless steel sheet, stressstrain curves at various temperatures
140
~----~------Y-~---r--~--~----_+----~980
120
~----4_--~~~~--~~--~--~~~--__1840
Test direction: transverse. Sheet thickness = 0.508 mm (0.020 in.). Specimen size = 5.08 x 30.48 mm (0.20 x 1.20 in.). Strain rate =0.062/min. Annealed 600 oc (1112 °F), 30 min, grain size = 34 !lm. Composition: Fe18Cr-8Ni. UNS S30100
86°F (30 OC)
104°F (40 OC)
----1
122 °F (50 oC)
100
700 ro
.¡¡;
o..
O<:
ui U)
~
::2;
80
560
60
420
40
280
20
140
ui U)
~
en
0
0
20
Source: A. Rosen, R. Jago, and T. Kjer, Tensile Properties of Metastable Stainless Steels, J. Mater. Sci., Vol 7, 1972, P 870--876. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1301, CINDAS/ USAF CRDA Handbooks Operation, Purdue University, 1995, p 29
O
40
60
80
100
120
Strain, %
SS.030 301 annealed stainless steel sheet, compressive stress-strain curves at elevated temperatures
50r-·------,--------r--------r-------,-------~350
Sheet thickness = 1.6 mm (0.063 in.). Composition: Fe18Cr-8Ni. UNS S30100
40~------~-------~------~~------~------~280
400°F (204 OC)
600 °F (316 OC) ~----~~~~~~c--------~------4_------~210
&.
::2;
gf ~
~~~--4_------_+--------~------4_------~140 00
ri------+-------~------~-------r-------170
°0~------~2--------~4--------6L-------~8------~1~
Strain,
0.001 in.lin.
Source: D.E. Miller, "Determination of!he Tensile, Compressive and Bearing Properties of Ferrous and Non-Ferrous Structural Sheet Materials at Elevated Temperatures," AF TR No. 6517, Pt V, Armour Research Foundation, Dec 1957. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1301, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 47
178/Stainless Steel (SS)
250
1750
200
1400
150
800 °F (427 OC)
'iii
.l<
1050
55.031 301 full hard stainless steel sheet, typical tensile stress-strain curves at room and elevated temperatures Test direction: longitudinal. 0.5 h exposure to elevated temperatures. Ramberg-Osgood parameters: n(room temperature) = 4.4; n(400 °P) = 3.4; n(600 °P) = 4.6; n(800 °P) = 4.2; n(lOOO °P) = 4.3. Composition: Pe18Cr-8Ni. UNS S30100
'"
11.
:2
~
g
I
1000 °F (538 OC) 100
Source: MIL-HDBK-5H, Dec 1998, p 2-229
ui (J)
m
700
en
50~--~~---r----+-----~---+-----r--~350
°0~--~2-----4L---~6-----8L---~10-----1L2--~1!
Strain, 0.001 in.lin.
250
1750
200
1400
150
1050
'iii -"
55.032 301 full hard stainless steel sheet, typical tensile stress-strain curves at room and elevated temperatures Test direction: long transverse. 0.5 h exposure to e1evated temperatures. Ramberg-Osgood parameters: n(room temperature) = 5.4; n(400 °P) = 4.8; n(600 °P) = 4.3; n(800 °P) = 5.3; n(1000 °P) = 4.6. Composition: Pe18Cr-8Ni. UNS S30100
'"
11.
:2
m
ui
i'i5
! 700
m
~
100
50 1-------:~~----~----+-------1-----_t_----____l 350
Strain, 0.001 in.lin.
Source: MIL-HDBK-5H, Dec 1998, p 2-229
Stainless Steel (SS)/179
55.033 301 full hard stainless steel sheet, typical compressive stress-strain and compressive tangent modulus curves at room and elevated temperatures
Compressive tangent modulus, GPa
250 o.-----_ _--,35_ _ _7-ro_ _ _1T"o5_ _ _ 14r-o_ _ _1--r7_5_ _---,21~750
Test direction: longitudinal. 0.5 h exposure to elevated temperatures. Ramberg-Osgood parameters: n(room temperature) = 5.3; n(400 °F) = 4.8; n(600 °F) = 5.2; n(800 °F) = 5.4; n(lOOO °F) = 5.7. Composition: Fe18Cr-8Ni. UNS S30100
200~----~-----+------+-----~----~----~1400
-00
1050
150
Source: MIL-HDBK-5H, Dec 1998, p 2-230 tU
[L
""ui
:2 ui
'"~
'"
¡¡; 700
100
2
6
~
o 12
8
Strain, 0.001 in.lin.
L
I
O
5
I 10
15
20
25
30
Compressive tangent modulus, 106 psi
Compressive tangent modulus, GPa
2500r----3r5---¡70---1,0-5--1T40---17,5--2,1rO---,241750
55.034 301 full hard stainless steel sheet, typical compressive stress-strain and compressive tangent modulus curves at room and elevated temperatures Test direction: long transverse. 0.5 h exposure to elevated temperatures. RT, room temperature. Ramberg-Osgood parameters: n(RT) = 7.7; n(400 °F) = 8.2; n(600 °F) = 6.7; n(800 °F) = 5.8; n(1000 °F) = 6.7. Composition: Fe18Cr-8Ni. UNS S30100 Source: MIL-HDBK-5H, Dec 1998, p 2-230
2
4
6
8
10
12
o 14
25
30
35
Strain, 0.001 in.lin.
O
5
Hi
I 15
I 20
Compressive tangent modulus, 106 psi
180/5tainless 5teel (SS)
SS.035 301 stainless steel strip, true tensile stressstrain curves
200r----r--~-_,---_r---,----,---,----,1400
Ultim~te stres~ = 185 k~i (1276 ~pa)
-.... _/
180f___--+---+_---t---+----+----t~--+--__I1260
160
f___--+---+_---t---+---+V..,./
140r---+-~-+----t--_+_74-~-+--+_-__I--~980 Stress a~ maximum load / Modulus of strain hardening =107 kSI (738 MPa)
120
/ . - (slope)
=107 ksi (738 MPa)
840 .\ / 8: ::¡: ~ 100 r---+--+_--;¡.z-; ,.,+-----.--I---+--+_-__I--~ 700 ui
-
00
/
JlV
~
II
80r---+~~+_-~--_+_---+----+---+-~560
00
¡
60r.-~~--+_--rf___--_+_--+--__I--_+_-__I420
!t/'Vield strength I = 49 ksi (338 MPa)1
4d'
Source: E.R. Cunningham. Cold Forming Stainless Steels and Other Specialty Grades. Sourcebook on Cold Forming, American Society of Metals, 1975, p 124
280
II
Graph provides useful data for evaluating stretch-forming operations. Yield strength is the stress at which specimen shows deviation from linear proportionality of stress and strain. Stress at maximum load is the stress at the highest load sustained by the specimen. Maximum uniform strain is the maximum value before uniform deformation ceases and necking begins; this is the strain at point of maximum load. Modulus of strain hardening is the slope of plastic region of true stress-strain curve. Ultimate stress is the stress at rupture. Composition: Pe-18Cr-8Ni. UNS S30100
2O~--+--+_---+-f___-_+_--+--__I----+--__1140 I I Uniforf strain 0.56 in.~in. I L_ _ _ _L __ _- L__ L -_ _- L____L -__L
'1
O O
~L----L--~O
0.4
0.2
1.0
0.8
0.6
1.2
1.4
1.6
Strain, in.lin.
500 . / -321 'F
450 400
I L
350 ~
300
g
/
~ 250
'"2
'"
f--
! /
200 150 100 50
/
(~196 'c)
/
21008: -112 'F (-80 I'C)
/
::¡:
~ '" 1400 ~ 1750
32°F (O lC)
/'
~
1050 700 350
20
Annealed 1093 oC (2000 °P), 1 h, grain size = 31 ¡.tm, strain rate =0.025/min. Composition: Pe-18Cr-9Ni. UNS S30200
2450
/ / / v..--- ~ /,¿ ~
10
3150 2800
¡..- 77 °F (25 OC)
~
SS.036 302 annealed stainless steel extruded bar, true stress-strain curves at room and low temperatures
3500
30
True strain, %
40
tí
Source: S.N. Monteiro and H. Fonseca, The Effect of Phase Transformation on the Tensile Fractnre of Austenitic Stainless Steel, Proc. Fourth Int. Con! Fracture, University of Waterloo, Ontario, Canada, June 1977, p 135-140. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1301, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 29
Stainless Steel (SS)/181
/ 280
/
240
V
200 rñ
en 160
~
en
80
-4J3 °F (-253
od)
Bar diameter = 19.05 mm (0.75 in.). Composition: Fe18Cr-9Ni + S. UNS S30300
1960
1680
I
-320 °F (-196 OC)
/ / h / //
~
120
SS.037 303 annealed stainless steel bar, stress-strain curves at room and low temperatures
2240
320
1400
'"
c.. ::;;
1120
\ -110 °F (-79 oC)
Source: K.A Warren and R.P. Reed, Tensile and Impact Properties of Selected Materials from 20 to 300K, Monograph 63, National Bureau of Standards, 28 June 1963. As published in Aerospace Structural Metals Handbook, Vo12, Code 1302, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 5
g
840
rwt~ ~
Room temperature
560
7
40
280 ,
0.2
0.4
0.6
0.8
o
1.0
Strain, in./in.
60
V 50
40 '00
-'" rñ
en 30 ~
é'i5 20
/
/
b --
43d °F (221 OC) ii reactor pile
1
4 30 °F (221 /
420
SS.038 304 annealed stainless steel bar, typical stress-strain curves at room temperature and 221°C (430°F) inside and outside of reactor pile
350
Bar diameter = 25.4 mm (1 in.). Ultimate strength = 612 MPa (88.8 ksi); yield strength = 295 MPa (42.8 ksi); elongation (in 4D) = 57.2%. Composition: Fe-19Cr9.25Ni. UNS S30400 Source: c.A. Schwanbeck, "Effect of Nuclear Radiation on Materials at
1
I
ocl
outside of reac¡or pile
~
Room
temp~rature
280
&.
r
::;; 210 rñ
~
140
10
70
2
4 6 Strain, 0.001 in./in.
8
Cryogenic Temperatures," NASA CR-54881, Lockheed-Georgia Co., Jan 1965. As published in Structural Alloys Handbook, Vol 2, CINDAS/ USAF CRDA Handbooks Operation, Purdue University, 1994, p 62
182/Stainless Steel (SS)
55.039 304 stainless steel wire, stress-strain curves at 767 oC (302°F) showing effect of nitrogen content
7o.---------,---------,---------,---------~490
60~--------+_--------+_--------~--------~420
50~--------+---------~~----~~--------~350
40
'iñ
~--------+_---7"-____,7"'+_--------_t_--------~
280
~
~
~
00
00
~ (/)
~
210 c;¡
30
20~----úR--+---------+----------t---------~140
Wire diameter = 0.635 mm (0.025 in.). Heat treatment: annealed 1010 oC (1850 °P), 20 min, water quenched, nitrided at 538 oC (1000 °P) and homogenize annealed 1010 oC (1850 °P), 71 h, water quenched, carbide reso1ution annealed 1093 oC (2000 °P), 15 min, water quenched. Composition: 18.65Cr-1O.5Ni-0.05C-1.44Mn0.66Si-0.02P-0.008S-bal Pe-N as shown. UNS S30400 Source: B.N. Ferry and J.F. Eckel, The Effect of Nitrogen on AISI Type 304 Stainless Steel Proportional Limit and Work Hardening Rate at 302F, J. Mater., Vol 5 (No. 1), March 1970. As published in Structural Alloys Handbook, Vol 2, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1994, p 63
10~~------+---------+---------~--------~70
L---------~--------~--------~--------~O
0.1
0.2
0.3
0.4
Strain, %
55.040 304 stainless steel tube, compressive stressstrain curves at elevated temperatures
1400
200 400 oC 160
(
-,
/
1120
120 'iñ ~
rñ !I)
fE
c;¡ 80
Strain rate = O.Olls. Composition: Pe-19Cr-9.25Ni. Dimensions in inset given in inches (1 in. = 25.4 mm). UNS S30400
/..
I(
/
/'
V-
/
.... 840
~
®
----1
40 i
rñ
'"fE c;¡
1--0.100-
560
T
i i i
0.300
i ! ...LI
-
280
~ 0.200 1
0.1
0.2
0.3
Strain, in.lin.
~
0.4
o
0.5
Source: M. Young et al., "Studies on lhe Warm Working Characteristics of Alloys," AMMRC CTR 72-27, Arrny Materials and Mechanics Research Center, Dec 1972, AD 758912. As published in Structural Alloys Handbook, Vol 2, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1994, p 72
5tainless 5teel (55)/183
55.041 304 stainless steel, general, full-range stressstrain curves at room and elevated temperatures
700
100
Curves shown to failure. Composition: Fe-19Cr-9.25Ni. UNS S30400
Room temperature 560
80
Source: Bettis Plant Materials Manual, Westinghouse Electric Corp., Standards Engineering Section, May 1957. Aspublished in Aerospace Structural Metals Handbook, Vol 2, Code 1303, CINDASIUSAF CROA Handbooks Operation, Purdue University, 1995, p 13
600°F (316 OC) .¡¡;
420
60
l1l
c..
"'<ñ"
:2 <ñ
~'"
(J)
280
40
'" ~
400°F (204 OC)
140
20
ooL-------L-------~------~-------L-------JO
0.2
0.4 0.6 Strain, in.lin.
0.8
60
420
55.042 304 stainless steel, general, expanded-range stress-strain curves at room and elevated temperatures
50
350
Composition: Fe-19Cr-9.25Ni. UNS S30400
Room tempera tu re
/
40 .¡¡;
"'<ñ"
'" ~
1.0
30
k
(J)
20
10
280 l1l
400°F (201 OC) :.-600 °F
(31~ OC)
c..
:2 210 <ñ
~
I
800°F (427 OC)
r
140
70
I
4
Source: Bettis Plant Materials Manual, Westinghouse Electric Corp., Standards Engineering Section, May 1957. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1303, CINOASIUSAF CROA Handbooks Operation, Purdue University, 1995, p 13
8 Strain, 0.001 in.lin.
12
184/Stainless Steel (SS)
400
200 70°F (21°C)
~
55.043 304 annealed stainless steel bar, true stressstrain curves at room and elevated temperatures
2800
/
100
-
40
V ~
1---
100 .001
--
/
V
1400
oí (42í oC)
V
Source: J.B. Conway, "Evaluation of Plastic Fatigue Properties of HeatResistantAlloys," GEMP-740, General Electric Co., Dec 1969. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1303, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 13
700 '" o.. :2
Ul
V1200 °F (649 OC)
¡,.....- V
Bar diameter = 15.875 mm (0.625 in.). Composition: Fe19Cr-9.25Ni. UNS S30400
~
V
~ ~o
v :/
-----V V
~ ;;~
...-...-
20
./
V
/
I I I ol (81l OC)
-do
420 ~
al
280
2
1-
140
0.01
0.1
70
1.0
True strain
260
.....-cr•••
240 220 21°C (70°F).....-a 200 180
P max ,
~ 160
~
gf 140 ~
~
120
1-
100
rY"
2
./ ,/1"
80 .,t:!'
/...:::
/~ ~
~-
20
o
O
k
-----.Pmax
0.3
1400 1260
~
840 1ñ al 2 700 1-
......
P~ax
'~
.~
.
i.
'"
.
560
~
420
'\ 650 oC (1200 Oí)
....
~
•
0.-0-0.
280
8~6 oc (1500 °F)
140
"C¡ 0.5
1680 1540
430 oc (806°F) 430 oC
004
b
:2 980 gf
816 oC 0.2
V
1820
1120~
/'
656 oc
"- P max
0.1
V
~
¡.....--
/
VL ~ ...-40 60
~
...........: -o....o-Q....
0.6
0.7
0.8
0.9
1.0
1.1
1.2
1.3
o
104
Total true strain
55.044 304 annealed stainless steel bar, true stress-strain curves al room and elevated temperatures Bar diameter = 6.35 mm (0.25 in.). Data were collected at constant axial true strain rates of 0.004 (open data points) and 0.00004 (solid data points). The curves for the higher strain rates are aboye the other curve at 650 and 816 oC (1202 and 1580 °F), while the reverse is true for 430 oC (806°F). Contrary to what is expected for true stress-strain curves, these have a maximum point. This is believed to be due to the formation of internal voids that reduce the actual area under stress. For this reason the lines are dashed as they approach the fracture point. P max is the point of maximum load. Composition: Fe-19Cr-9.25Ni. UNS S30400 Source: lB. Conway, RH. Stentz, and J.T. Berling, "Fatigue, Tensile, and Relaxation Behavior of Stainless Steels," Technical Infonnation Center, USAEC, 1975, P 213
Stainless Steel (SS)/185
100 21
90 ..",.-
80 70
V
V
~ rñ 60
~
I1
'" c: 50
.~
al
;
f- r--
.§, 40 c:
w 30 20
560
.f. G.••
~~
~
~
-.
1\,
··· ·
.
-.......
0.2
0.3
0.6
0.5
0.7 0.8 Engineering strain
0.9
o 1.0
al
c: c:
'0,
140
"''''
0.4
'"c:
w
70
"'....'o
0.1
Oí
210
···ct····· ".0."Q. -o 816 oC (1500 °F
816 oC
rñ
'"~
280
;
:\
420
.~
L
R.
650 oC
.
a.
:2:
350
~',
1--...
C\l
",
""""- 0.'-0. ~
490
'. ".
""
- -)
•• O' •• .Q.
650 oC (1200 °F)
~
10
-
430 oC (806°F)
~
.
Ik
630
----
~
~
ob (70°F)
~
/ ./
~
700
v
v
/\
1.1
1.5
v
"
2.9
3.0
O
SS.045 304 annealed stainless steel bar, engineering stress-strain curves at room and elevated temperatures Bar diameter = 6.35 mm (0.25 in.). Data were collected at constant axial true strain rates of 0.004 (open data points) and 0.00004 (solid data points). Same data was used as for the true stress-strain curve. The curves for the higher strain rates are aboye the other curve at 650 and 816 oC (1202 and 1580 °F), while the reverse is true for 430 oC (806°F). The strain rate effect is more pronounced for the higher temperatures. The lines are dashed as they approach the fracture point. Composition: Fe-19Cr-9.25Ni. UNS S30400 Source: J.B. Conway, R.H. Stentz, and J.T. Berling, "Fatigue, Tensile, and Relaxation Behavior of Stainless Steels," Technical Information Center, USAEC, 1975, P 216
520 480 440
/
400
V
/ V J/' /
360 ._ 320
YV
~
li 280
~J"
~
~ 240
r¡~ V
::J
¡!: 200
,1
160
¡
I~ 1*'" 80 ~
120
V .",.-
./"
V
..V
V
...
/
/'"
/'
-32~ °F (-1 96 OC) 1
-452 °F (-269 °6)
~
/'
......
, / -240°F. (-151°C) 1
y-
1
3360
2800
¿
¿
",.,.
.r' ~om temperature
2240
1960~ rñ
1680 ~
ro
/
1400 1120
840 560
40
280 O
0.2
0.4
0.6
0.8 1.0 True strain
Bar diameter = 12.7 mm (0.500 in.). Composition: Fe19Cr-9.25Ni. UNS S30400
3080
,../ -105°F (-76 OC) 2520
1.....
o
SS.046 304 stainless steel bar, true stress-strain curves at room and low temperatures
3640
1.2
1.4
1.6
o
1.8
Source: T.S. DeSisto and EL. Carr, "Low Temperature Mechanical Properties of 300 Series Stainless Steels and Titanium," WAL TR 323, 4/1, Dec 1961. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1303, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 14
186/5tainless 5teel (SS)
1200r----r----~---,----,_--_,----,_----r_--~
-80 oC 1000~--_+----~----~--~~~~----+_--_4----~
55.047 304 stainless steel sheet, true stress-strain curves at various temperatures Strain rate = 0.015/s. Composition: Fe-19Cr-9.25Ni. UNS S30400 Source: G.L. Huang, D.K. Matlock, and G. Krauss, Martensite Formation, Strain Rate Sensitivity, and Deformation Behavior of Type 304 Stain1ess Stee1 Sheet, Metal!. Trans. A, Vo120A, 1989. As published in G. Krauss, Steeis: Heat Treatment Processing and Principies, 1990, p 369
200~--_+----~----~--_+----~----+_--_4----~
0.1
0.2
0.3 0.4 0.5 Engineering strain
0.6
0.7
0.8
400
55.048 304 stainless steel sheet, tensile and compressive stress-strain curves
350
24 to 35 tests were made in each orientation on coldroUed specimens. Curves: LT, longitudinal tension; TT, transverse tension; LC, longitudinal compression; and TC, transverse compression. Elastic modulus: LT, 199.8 GPa; TT, 197.3 GPa; LC, 208.1 GPa; TC, 205.1 GPa. Yield strength (0.2%): LT, 290.3 MPa; TT, 290.0 MPa; LC, 295.7 MPa; TC, 308.0 MPa. Ultimate tensile strength: LT, 676 MPa; TT, 651 MPa. Composition: Fe-19Cr-9.25Ni. UNS S30400
......-:;:t' ~ .../;(;~ TS··
250 ro
a. :2 cñ 200
'" ~
150
100
50
_. --- ------.:...-..: ~ --...::;;:::
300
/ V
I
f
j" ,/
TI
...-
/'LC
Source: P. Van Der Merwe and G.J Van Den Berg, The Advantages of Using Cr-Mn Stee1s Instead of Cr-Ni Stee1s in Co1d-Formed Design, High Manganese High Nitrogen Austenitic Steeis, RA. Lula, Ed., Conf. Proc., 10-15 Oct 1987 (Cincinnati, OH) and 2-4 Nov 1992 (Chicago, IL), ASM Intemationa1, 1992, p 129
2
3
Strain x 0.001
4
5
Stainless Steel (SS)/187
.....-
100
ui
'" ~
60
/
/
80 ~
SS.049 304 annealed stainless steel bar, stress-strain curves
840
120
"
\
/
Bar diameter = 12.7 mm (0.5 in.). Specimen: 9.525 mm (3/8 in.) diam threaded ends, 3.175 mm (0.125 in.) square cross section of 38.1 mm (1.5 in.) gage length tested at strain rate of 0.001ls. Composition: Fe-19Cr-9.25Ni. UNS S30400
700
560
8: ::¡;
1\\
40
420
ui
!rn
Souree: P.C. Johnson, et al., "Basic Parameters of Metal Behavior under High Rate Forming," Report No. WAL TR 111.2/20-3, Arthur D. Little Ine., Mareh 1962, AD 418727. As published in StructuralAlloys Handbook, Vol 2, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1994, p 64
280
,
20
140
20
10
30
40
50
60
Strain, %
25 Elastil strain
20
15 '00
.><
ui
'"~
Cií
/
/
Il'
10 f
I
V
V
./
/ ...... ... ...
.........
-....----
4
10 h
~
~
-ros;; r-~5h
175
SS.050 304 annealed stainless steel, isochronous stress-strain curves at 538 oC (1000 °F)
140
Souree: "Isoehronous Stress-Strain Curves for 2YíCr-1Mo, Type 304304H, and Type 316-316H Steels," TR 2012-Part 1, prepared for U.S. Atomie Energy Commission, Contraet No. AT(04-3)-781, Braun Projeet 4122-W, United Nuclear Projeet 2351, 16 Oet 1970. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1303, CINDAS/ USAF CRDA Handbooks Operation, Purdue University, 1995, p 25
-
Composition: Fe-19Cr-9.25Ni. UNS S30400
----
105
ui
70
.-
"
5
35
0.5
1.0
1.5
2.0 Strain, %
2.5
3.0
3.5
.,
o.. ::¡;
o
4.0
'" ~
188/Stainless Steel (SS)
25 Elastil strain 1(fh
20
.c;;
15
~
rñ
'"~
é'ií
10
/'
~ ~
/'
V~
f1'// -------""
I
/
;'
;'
~
/
~
------
175
SS.051 304 annealed stainless steel, isochronous stress-strain curves at 593 oC (1100 °F)
140
Souree: "Isoehronous Stress-Strain Curves for 2Y4Cr-1Mo, Type 304304H, and Type 316-316H Steels," TR 2012-Part 1, prepared for U.S. Atomie Energy Commission, Contraet No. AT(04-3)-781, Braun Project 4122-W, United Nuclear Projeet 2351, 16 Oet 1970. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1303, CINDASI USAF CRDA Handbooks Operation, Purdue University, 1995, p 25
Composition: Fe-19Cr-9.25Ni. UNS S30400
~
~~
-
105 ro a.
:2 rñ
'"~
I
5 x 1Cfh
70
¡...---
é'ií
....
/
5 I
35
0.5
1.0
1.5
2.0 Strain, %
2.5
3.0
3.5
o
4.0
SS.052 304 annealed stainless steel, isochronous stress-strain curves at 649 oC (1200 °F)
175
25 Elaslie strain
Composition: Fe-19Cr-9.25Ni. UNS S30400 140
20
.c;;
15
~
rñ
'"~
é'ií 10
5
V ------------ft -- --/
/
105 ro a.
:2 rñ
104 h
'"~
r70
V
1(fh
V--
5 x 1cr h 35
;'
/
I
1tY h ¡--
'"
0.5
1.0
1.5
2.0 Strain, %
2.5
3.0
3.5
o
4.0
é'ií
Souree: "Isoehronous Stress-Strain Curves for 2Y4Cr-1Mo, Type 304304H, and Type 316-316H Steels," TR 2012-Part 1, prepared for U.S. Atomie Energy Commission, Contraet No. AT(04-3)-781, Braun Projeet 4122-W, United Nuclear Project 2351, 16 Oet 1970. As published in Aerospace Structural Metals Handbook, Vo12, Code 1303, CINDASI USAF CRDA Handbooks Operation, Purdue University, 1995, p 25
5tainless 5teel (55)/189
15o.-----r-----r-----r-----r-----~
55.053 304 hot-rolled solution-annealed stainless steel plate, stress-strain curves at room temperature (a) and 500 oC (b) for shock-strengthened material
,--,------, 1050
700
100
(ti
~
[L
::;;:
gf 75
525 ui
'"~
~
éi5 50
350
25 I - - - - - t - - - - - t -
175
Source: M. Kangilaski and A.A. Bauer, "Mechanical Properties of Shock-Strengthened Austenitic Stainless Steel," BMI-1909, Battelle Columbus Laboratories, June 1971; M. Kangilaski et al., Elevated Temperature Mechanical Properties of Shock-Strengthened Austenitic Stainless Steel, Metall. Trans., Vol 2, Sept 1971. As published in Structural Alloys Handbook, Vol 2, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1994, p 64
°0L-----1~0-----2~0-----L-----L-----LJ
Strain, %
(a)
700
100
80
~
-'"
ui
'"~
éi5
40
560
~\5
60 ji' "¡¡;
7
"
\
3\
\
4 ~
/~ 1(/,/
--------', -----
1
~
420
::;;:
gf ~
280 éi5
\
I
20
I
140
10
20
30 Strain, %
(ti
[L
6
40
o
50
Plate thickness = 12.7 mm (0.5 in.). Curve 1: unshocked. Curve 2: as-shocked at 320 kbar. Curve 3: shocked at 320 kbar, annealed 100 h at 650 oC. Curve 4, shocked at 320 kbar, annealed 1 h at 750 oC. Curve 5: shocked at 320 kbar, annealed 1 h at 800 oC. Curve 6: shocked at 320 kbar, annealed 1 h at 900 oC. Composition: 18.20Cr9 .60Ni-0.06C-1.45Mn-0.60Si-0.024P-0.0 18S-0.18MoO.17Cu-bal Fe-N as shown. Dimensions in schematic are given in inches (1 in. =25.4 mm). UNS S30400
190/Stainless Steel (SS)
SS.054 304L annealed stainless steel bar, stress-strain curves for room and low temperatures
280r---------,----------,---------,---------.1960 -423 °F (-253 OC)
Bar diameter = 19.05 mm (0.750 in.). Composition: Felow C-19Cr-IONi. UNS S30403
240~--------~----~---r---------4----------41680
Source: "Cryogenic Materials Data Handbook," ML-TRD-64-280, Martin Co., Denver, CO, Aug 1964. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1303, CINDASruSAF CRDA Handbooks Operation, Purdue University, 1995, p 13
200~--------4-~~~L-~~------~--------~1400
~ 160r-------~~+_-------r_r------~--------~1120~
::;;
~
~
1i5 120
840
~
°0L-------~OL.2---------0L.4---------0~.6--------~0.f Strain. in./in.
120
840
100
700
--o- ~
Ultimate tensile strength
80
'" ~
Sheet thickness = 1.60 mm (0.063 in.). Composition: Fe25Cr-20.5Ni. UNS S31000
.o---< 560
IV
~ ::;;
.¡¡;
""
SS.055 310 annealed stainless steel sheet, effect of strain rate on mechanical properties
420
60
40
O
Tensile yield strengt~ ~
(f)
280
140
20
O
j
~
0.1
1
Strain rateo S
-1
10
2
10
Source: R.G. Davies and C.L. Magee, The Effect of Strain-Rate upon tbe Tensile Deformation of Metals, J. Eng. Mater. Technol., Apri11975, p 151. As published in Aerospace Structural Metals Handbook, Vo12, Code 1305, CINDASruSAF CRDA Handbooks Operation, Purdue University, 1995, p 22
5tainless 5teel (55)/191
55.056 310 annealed stainless steel bar, stress-strain curves at room and low temperatures
200,-----,----,-----,-----,-----,----,-----, 1400 180~--~-----+~~
1260
160f---+7
1120
1401---F~~
980
Bar diameter = 19.05 mm (0.75 in.). Shaded area indicates serrated -452 °P (-269 oC) curve. Composition: Pe-25Cr-20.5Ni. UNS S31000
840
g¡ca
700
g (/J
(Jj
en
Source: CJ. Guntner and R.P. Reed, The Effect of Expeómental Vaóab1es Inc1uding the Martensitic Transformation on the LowTemperature Mechanical Properties of Austenitic Stain1ess Stee1s, Trans. ASM, Vo155, 1962. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1305, CINOAS/USAF CROA Handbooks Operation, Purdue University, 1995, p 22
560 420 280
0.1
0.3
0.2
0.4
0.5
140 0.7
0.6
Strain, in./in.
40 36 32
/
28
/
rJ)
CI)
c7> 20
6qO 'F (316 'C)
12
196 ca
-
1000 'F (538 ' C ) - 168 1200 'F (649 I
140 ~
I
112
1600 'F (871 'C)
I
I
1800 'F (982 ' C ) - 84 56
,(.,
2doo 'F (1093 'C) 28 2200 'F (1204 'C)
2
3
4
Strain, 0.001 in./in.
5
6
g¡ gf
'Gl
1400 'F (760 'C)
...'/ f/
224
-
8qO 'F (427 'C)
~~
16
Sheet thickness = 1.575 mm (0.062 in.). Test conditions: resistance heated at 93 °C/s (200 °p/s). Strain rate = 0.00 lis. Composition: Pe-25Cr-20.5Ni. UNS S31000
252
I/~
ui
4
/
75'F(24'C)------ 280
V-
/L
~ 24
8
55.057 310 annealed stainless steel sheet, stressstrain curves at room and elevated temperatures
308
44
7
Souree: A.S. Rabensteine, "Meehanieal Properties of 310,316 and 317L Stain1ess Stee1 Sheet Alloys at E1evated Temperatures," Contraet Number AF33(657)-8706, Projeet 281, The Marquardt Corp., Van Nuys, CA, Oee 1962. As pub1ished in Aerospace Structural Metals Handbook, Vol 2, Code 1305, CINOAS/USAF CROA Handbooks Operation, Purdue University, 1995, p 23
192/Stainless Steel (SS)
280
1960
280
240
1680
240 1-
1:1 Biaxial (::ipee NO. BS 26)
200
1400
j~ .¡¡; 160
"'
~
en
120
1120 ~
:;;
~
VJ
840 iií
80
40
/(1
.¡¡; 160
"'
1:1 Bila, (Spee No. BS 20)
1680
1400
17
2:1 Biaxial (Spee No. BS 32) 1120 ~
1(/
VJ
:;;
VJ
~ 840 en
iií 120
560
80
560
280
40
280
Room teTperature
2
3
Room teTperature
4
5
o 2
Nominal principal strain, %
280
1960
::L./
V
1:1 Biaxlal (Spee No. BS 24) 240
2:1 Biaxial (Spee No. BS 12)
~
200
VJ
~
en
4
5
o
(b)
280
"'
3
Nominal principal strain, %
(a)
.¡¡; 160
........ 13.0
Uniaxial (Spee No. USL 5)
//V?
200
2:1 Biaxial (Spee No. BS 7) Uniaxial (Spee No. USL 2)
!/ '/
1960
~
~
::;;-
........ 7.0
Uniaxial (Spee No. USL 3)
1680
240
1400
200
1120 ~
:;;
1:1 Biaxial (Spee No. BS 18)
({¡t?"
120
1680
Uniaxial (Spee No. USL 7)
1400
/r
.¡¡; 160
1120 ~
~
"'
~ ~ 840 en en 120 VJ
1960 2:1 Biaxial (Spee No. BS 31)
:;;
~
840 iií
11 80
560
80
560
40
280
40
280
1I
-105 °F (-76 OC) 00
I 2
3
4
5
o
2
oí
(-253 OC)
3
4
5
o
Nominal principal strain, %
Nominal principal strain, %
(e)
-423
(d)
55.058 310 stainless steel, typical stress-strain curves for uniaxial and biaxial stress at room and low temperatures Test direction: longitudinal. Composition: Fe-25Cr-20.5Ni. UNS S31000 Source: s.w. McClaren and C.R. Foreman, "Cryogenic Design Data for Materials Subjected to Uniaxial and Multiaxial Stress Field," AFML-TR-65-140, May 1965. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1305, CINDAS/USAF CROA Handbooks Operation, Ptlrdue University, 1995, p 23
5tainless 5teel (55)/193
45
~ ~2% bffse! yield
40 RT Lo! 2 / 35
// V J // ff/
30
]j 25 rñ
~ 20 15
V
V--
o
6
3 2
RT Lo! 1
rñ (f)
140 (/) ~
1400 °F (760 OC) Lo! 1
I
105
1600 °F (871 OC) Lo! 2 I
70
,
9
7
245
-,
1800 °F (982 OC) Lo! 1 I
234 S!rain, 0.001 in.lin.
35
5
63
,
.....J---r-0.2% Offse! yi~ld
8
I I I
I
V r? V
Bar diameter = 19.05 mm (Y.. in.). Test section diameter = 12.827 mm (0.505 in.). Difference between two 10ts is shown. RT, room temperature~ Composition 10t 1: 17.81Cr-13.17Ni-2.23Mo-1.54Mn-0.56Si-0.042C-0.027P0.017S. Composition 10t 2: 16.60Cr-12.15Ni-1.80Mo1.58Mn-0.46Si-0.090C-0.028P-0.013S. UNS S31600 ro
Y
O (a)
280
175 ~
V~~
5
SS.059 316 stainless steel bar, stress-strain curves at room and elevated temperatures
210
~
10
315
56
~OF(9820C)
49
Lo! 1 and 2 average
42 2000 °F (1093 OC)
---
Lo! 1 a~d 2 average
ro
35 ~
rñ (f)
,
28 (/) ~
2200 °F (1204 OC) I Lo! 21
21 2300 °F (1260 OC) Lot2
14
7
234 S!rain, 0.001 in.lin.
5
Source: T.W. Gibbs and H.W. Wyatt, Short Time Properties ofType 316 Stain1ess Stee1 at Very High Temperatures, Paper No. 60-WA-ll, Trans. ASME, J. Basic Eng., 1960. As published in Structural Alloys Handbook, Vol 2, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1994, p 31
194/5tainless 5teel (SS)
1 0 0 , . - - - - - - - , - - - - - , - - - - - - ¡ - - - - - - , 700
100
560
80
420 ro n.
60
700
2
'iñ
'"vi
280
~
~
tií
40
140
o
O
5
10 8lrain x 0.001
(a)
15
80 5
O
420
vi
~
4
t:
280 tií
Monotonic
(0.004/5)
140
I
I 15
10 8lrain x 0.001
(b) 560
80,------,-----,--------¡-------,560
420
60
~
280
40
~
tií
(0.004/s) 140
20
°0L----~5------~10~----1L5-----~2~
8lrain x 0.001
vi
~
420
,----. ---,
'iñ
'":Ii
40
tií
ro
n. ~
5
ro n.
(e)
)
II
20
~ ~
---
--- • o
60
:Ii
20
~
!
'"vi
vi
(0.004/5)
~
'iñ
~
Monotonic
./
560
o
8
9
ro
n. ~
280
vi rn ~
tií
20
Monolonic
(0.004/s) 140
°0L-----~5----~10-----1L5-----~2~
8lrain x 0.001 (d)
SS.060 316 stainless steel bar, monotonic and cyclic stress-strain curves at room and elevated temperatures Bar diameter = 15.875 mm (5/8 in.). Hot roUed, annealed 1066 oc (1950 °P), 1 h. Incremental steps: Solid line, annealed; dashed line, aged 1000 h at test temperature. Constant amplitude continuous cycling: open circle, annealed; solid circle, aged at 538 oC (1000 °P); solid diamond, aged at 649 oC (1200 °P). Strain rate for cyclic curves 1-5, 7-9 = 0.004/s; for curves 6 and 10, strain rate = 0.00004/s. (a) 21°C (70 °P). (b) 427 oC (800 °P). (c) 566 oC (1050 °P). (d) 649 oC (1200 °P). Composition:17.30Cr13.30Ni-2.33Mo-1.72Mn-0.40Si-0.06C-0.012P-0.007S-0.065Cu-O.003Ti. Dimensions in schematic given in inches (l in. = 25.4 mm). UNS S31600 Source: D.A. Keller, "Progress on LMFBR Cladding, Structural and Component Material Studies During July 1971 through June 1972," BMI-I928, Final Report, Task 32, Battelle Columbus, July 1972. As published in Structural Alloys Handbook, Vol 2, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1994, p 32
Stainless Steel (SS)/195
35
V
30
25
/
·iii 20 -" ui
15
~/
10
5
500 OF¡ (260 OC)
1000
¡--
~
~
rt
210
l.,.----
&
In
ro
'/
Sheet thickness = 3.175 mm (0.125 in.). Composition: 17.17Cr-12.96Ni-2.15Mo-l.7Mn-0.2Si-0.03C. UNS S31600
(25 OC)
175 -
~
t
77
SS.061 316 stainless steel sheet, typical stress-strain curves at room and elevated temperatures
245
140
o~ (538 OC)
& :2
I
105
Source: T.W. Gibbs, w. Kyros, and C.L. Theberge, "Development of a Resistance Heating Facility for the Determination of Tensile Properties of Aircraft and Missile Alloys," RaD. TM-63-8, Avco Corp., Feb 1963. As published in Structural Alloys Handbook, Vol 2, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1994, p 33
::i ~
1400 °F (760 lC)
f.o-
I
70
1600 °F (871°C)
f-"
T"" I
......... 1800
2
3
4
35
'C)
5
6
o
Strain, 0.001 in./in.
50
40
30
I
V
¡.--
¡.--
350
SS.062 316 wrought stainless steel bar, typical stressstrain curves at room and elevated temperatures
280
Source: L.J. Fritz and W.P. Koster, "Tensile and Creep Rupture Properties of (16) Uncoated and (2) Coated Engineering Alloys at Elevated Temperatures," NASA Cr-135138, Metcut Research Associates, lnc., Jan 1977. As published in Structural Alloys Handbook, Vol 2, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1994, p 33
Composition: Fe-18Cr-13Ni-Mo. UNS S31600
70°F (21°C)
210
~
a.'"
:2
ui
::i
In
~
-- ---
1100 °F (593 OC)
(Jl
..--
20
/
I ,, ¡ I
10
......... ¡,-- ~/'
, ,,
I
/'
1--¡,....~-
~
~-
1300 °F (704 OC)
-- ~;O-;;tF ~-~
ro 140
(816 OC)
/' I
I
~
70
I
I
o Strain, 0.001 in./in.
196/Stainless Steel (SS)
60
O
50
~~~ ~\OD
-Ó
V
li
~
O
e
f 8
•
....
350 D D
O
280
~
l= ~
~
00 D
~Cb
40
~ 30
>00
,.,.... D
a.'"
D
~
if
SS.063 316 annealed stainless steel bar, true stressstrain curves for irradiated and unirradiated samples
420
i
::lE
tJi
~
210 ~
tí
O
~
~
20 ;::r
140 ~
P
70
o o o 0.10
Source: J.B. Conway, J.T. Berling, and R.H. Stentz, "New Correlations Involving the Low-Cycle Fatigue and Short-Term Tensile Behavior of Irradiated and Unirradiated 304 and 316 Stainless Steel," GEMP 726, General Electric Co., Dec 1969. N70-25351. As published in Structural Alloys Handbook, Vol 2, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1994, p 34
o
10
0.05
True axial strain rate = 4 x 1O-5/s. Test temperature = 649 oC (1200 °F). Closed data points: unirradiated speeimens in duplieate tests. Open circles and squares: unirradiated speeimens. Open diamond: irradiated speeimen 4 x 1018 n/em2, E> 1 MeV at 70 oC in the ORR eore faeility. Composition: Fe-17.3Cr-13.1Ni-2.33Mo-1.72Mn-004Se0.065Cu-0.06C-0.012Al. UNS S31600
0.15
0.20
0.25
0.30
0.35
o
0.40
True strain
440
lA / / ' W ¡?P
~ 240
80
/"
~
li
/¡V/
IffV '/:V
~
~
~
2800
-196 OC
.......
f1#,
~ 280
120
3080
V
Fd
320
-269°C
,....-o
I
360
160
J
/
400
~ 200
SS.064 316 stainless steel plate, true stress-strain curves at room and low temperatures for base and weld metal
3360
480
,--o
2520 2240
/
-105 oC
'"
1960~
tJi
1680 ~
,-u
1400 ~
Vo ----24°C
1-
1120 840 560
/' 40
280 0.2
0.4
0.6
0.8 True strain
1.0
1.2
1.4
Plate thickness = 15.9 mm (5/8 in.). Squares: base metal data. Circles: weld metal data. Speeimen diameter = 60401 mm (0.252 in.). Composition: 16.64Cr-12.84Ni2.69Mo-1.91Mn-0045Si-0.068C-0.026P-0.012S. UNS S31600 Source: T.S. DeSisto, "Low Temperature Mechanical Properties of Base and Weld Deposits of Selected Austenitic Stainless Steels," AMRA TR 63-08, Metals and Ceramics Research Agency, U.S. Army Materials Research Agency, July 1963, AD 416119. As published in Structural Alloys Handbook, Vol 2, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1994, p 34
Stainless Steel (SS)/197
35~----.------,------,------,------~----~
SS.065 316 stainless steel sheet, stress versus plastic strain curves for elevated temperatures with effect of annealing and cold working
245
210
Sheet thickness = 1.47 mm (0.058 in.). Plastic strain resulting from constant stress for 2 min at elevated temperature. Composition: Fe-18Cr-13Ni-Mo. UNS S31600
175
.¡¡;
1600 °F (871°C)
2o1----..4---+----f-::::;l...-q-.,..---r'---'-_i 140
-'"
~
00
rf
::¡;
'"~ 151-~~~~~. .~~--f---_r---r---_i 105 ¡jj
Source: T.w. Gibbs and Wyatt, H.W., "Short-Time Tensile Properties of Type 316 Stainless Steel at Very High Temperatures," ASME Paper No. 60-WA-Il. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1307, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 40
1800 °F (982 OC) 70
5~--_i----+_---+----
•
...
•
Annealed 5% cold worked 10% cold worked
35
°0~-----2~----~4------~6------~8------1~0----~1l
Plastic strain, %
90 ~
80
A ~~
70
60
rI
~ 50
'"~
¡jj 40
30
..n
,-,.
~
f
~
~~ ~
630
SS.066 316 annealed stainless steel wire, effect of vacuum on stress-strain curves at room temperature
560
Wire diameter =0.457 mm (0.018 in.). Strain rate = 0.0001ls. Composition: Fe-18Cr-13Ni-Mo. UNS S31600
490
~ VF
420
it1'
'"
350 ~
V
li
280 ~
00
210
20
o ~
5
4 x 10· Pa (3 x 1()"7 torr) (vacuum) 101 kPa (760 torr) (air)
10
140 70
2
4
6
8
10 12 14 Strain x 0.01
16
18
20
22
Source: I.R. Kramer and S.D. Podlaseck, "Effect of Low Pressures on !he Mechanical Behavior of Metals," Martin Marietta Corp., Oct 1963, AD 424 292. As published in Structural Alloys Handbook, Vol 2, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1994, p 33
198/Stainless Steel (SS)
40
35
30
25
15
10
V
----
/
/
~4JC)
Composition: Fe-18Cr-13Ni-Mo. UNS S31600
245
Source: T.W. Gibbs and H.W. Wyatt, "Short-Time Tensile Properties of Type 316 Stainless Steel at Very High Temperatures," ASME Paper No. 60-WA-ll. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1307, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 29
210
175
/ 1V- 1I 11-
al
o..
::;¡;
--
140
1400 °F (760 OC)
u) (J)
~
ro
1600 °F (871 °C)_ 105
I
1800 °F (982 °C)_ 70
~
5
SS.067 316 annealed stainless steel bar, stress-strain curves at room and elevated temperatures
280
I
2000°F(1093°C) ___ 35 2200 °F (1204 OC)
I~
I
2300 °F (1260 OC)
11 0.1
0.2
0.3
0.4
0.5
o
0.6
Slrain, %
560,----,----,----,-----,----,----,----,----.3920
SS.068 316 mili annealed stainless steel bar, complete true stress-strain curves for room and low temperatures
480~--_+----+_--~----~----+_--_+----~--~3360
Bar diameter = 12.7 mm (0.5 in.). Composition: Fe-18Cr13Ni-Mo. UNS S31600 Source: T.S. DeSisto and EL. Carr, "Low Temperature Mechanical Properties of 300 Series Stainless Stee1s and Titanium," WAL TR 323, 4/1, Watertown Arsenal Laboratories, Dec 1961. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1307, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 29
160~~~~--+-~~----~----+----+-----r--~1120
80~--_+----+_--~----~----+_--_+----~--~560
OL-__-L____L -_ _-L____L -_ _- L__ O 0.2 0.4 0.6 0.8 1.0 1.2
~L----L--~O
True strain, in.lin.
1.4
1.6
5tainless 5teel (55)/199
220 J:J"
200 180 160 Pmaxz:;;
140
~
gf 120
/
~
"lií Ol ::J
100
/
~
80
F
",
/
~
---
~
~
- Pmax
~
V
V
VPma\
/
980
••
840
"
'l'.P max 0.4
(J)
•
~
700 "lií
Ol ::J
\,650 oC (1200 °F)
........ 0.3
:2:
't
430°C "
0.5
:>"-0.0.
560
0.6
816 oC
0.7
··b
280
..o
0.8
0.9
~
420
\:~ 816 0q (1500 °F)I
..... . .•
ro
o.
•••• \ 430 oC (806°F)
0:\
¡..o-~ 20
0.2
1400
od (70°F)
1120
/J.
0.1
1540
.-------- .. ········-0 O~O
1260
¡.o-
/P max ~~ ~¿:-.' /~ ~ /Pmax 650 oC 40
60
~
"""-21
•••••• 0' . .
140 1.0
1.1
1.2
1.3
Total true strain
SS.069 316 annealed stainless steel bar, true stress-strain curves at room and elevated temperatures Bar diameter = 6.35 mm (0.25 in.). Data were collected at constant axial true strain rates of 0.004 (open data points) and 0.00004 (solid data points). The curves for the higher strain rates are aboye the other curve at 650 and 816 oC (1202 and 1580 °F), while the reverse is true for 430 oC (806°F). Contrary to what is expected for true stress-strain curves, these have a maximum point. This is believed to be due to the formation of internal voids that reduce the actual area under stress. For this reason the lines are dashed as they approach the fracture point. P max is the point of maximum load. Composition: Fe-18Cr-13Ni-Mo. UNS S3l600 Source: J.B. Conway, R.H. Stentz, and J.T. Berling, "Fatigne, Tensile, and Relaxation Behavior of Stainless Steels," Technical Information Center, USAEC, 1975, P 214
200/5tainless 5teel (SS)
100 21
80
~ '" 60
~
Cl
c:
.~
Q)
.§, 40 c: tu
20
V
VV
v: rI
.A'
~
~
,b
700 (70 'F)
¡...-o-
'--
-
'""""--- r---
¡...---
.... ~ io-a.. 650 'C 1200 'F)
r---.,
t--- t--I-)
"<
'o
r-.:,. ¡-e...
(1l
:o.
.<>.~.
)p--650 'C
~
Cl
c:
"f5
""
280 '¡¡' ~
... .~.~?~~..la .......
"
"'b\
.... ()o ..
0.3
0.4
0.5
0.6
0.7
0.8
.
140
...o ...... "'().....
...................
''O
r." lo
0.2
c: tu
1>,
816 'C (1500 'F)
11
en
(1\ "
","
o
o.. 420 ::;;:en 1ñ
{
'
IJ . 0.1
560
430 'C (806 'F)
0.9
1.0
1.4
1.5
" ......o v
2.4
o
2.5
Engineering strain
SS.070 316 annealed stainless steel bar, engineering stress-strain curves at room and elevated temperatures Bar diameter = 6.35 mm (0.25 in.). Data were collected at constant axial true strain rates of 0.004 (open data points) and 0.00004 (solid data points). Same data was used as for the true stress-strain curve. The curves for the higher strain rates are aboye the other curve at 650 and 816 oc (1202 and 1580 °P), while the reverse is true for 430 oc (806 °P). The strain rate effect is more pronounced for the higher temperatures. The lines are dashed as they approach the fracture point. Composition: Pe-18Cr-13Ni-Mo. UNS S31600 Source: J.B. Conway, R.R. Stentz, and J.T. Berling, "Fatigue, Tensile, and Relaxation Behavior of Stainless Steels," Technical Information Center, USAEC, 1975, P 216
24o,------,------,------,------,-------,------,168o
200~-----+------+-----~--~--4-------~-----11400
160~-----+------+---~-+------4-~~--~----41120
SS.071 316 annealed stainless steel sheet, true stressstrain curves at room and low temperatures Sheet thickness = 0.762 mm (0.03 in.). Annealed 1049 oC (1920 °P), 0.25 h, water quenched, grain size = 100 ¡..Lm, gage section = 6.35 x 0.762 x 25.4 mm (0.25 x 0.03 x 1.0 in.), strain rate = 0.004/min. Composition: Pe-18Cr13Ni-Mo. UNS S31600 Source: V. Seetharaman and R. Krishnan, Influence of the Martensitic Transformation on the Deformation Behavior of an AISI 316 Stainless Stee1 at Low Temperatures, J. Mater. Sci., Vol 16 (No. 2), Feb 1981, p 523-530. As pub1ished in Aerospace Structural Metals Handbook, Vol 2, Code 1307, CINDAS/USAF CRDA Randbooks Operation, Purdue University, 1995, p 30
80~~---+.~----~--~~------4-----~~----~560
40~-=~-+------~-----+------4-------~----~280
°0L------1LO------2~0------3~0------~40-------5LO----~600 True plastic strain, %
Stainless Steel (SS)/201
40
-- --
SS.072 316 annealed slainless sleel wroughl, isochronous slress-slrain curves al elevaled lemperalures
280
~ooo
h - . _. 10,000 h _._-- 100,000 h - - 500,000h
Left: 538 oC (1000 °P). Middle: 593 oC (1100 °P). Right: 649 oC (1200 °P). Composition: Pe-18Cr-13Ni-Mo. UNS S31600
210
30
........
/ ",,""
/
, / . , 1
1
/
/""
/
/
V il/ ;/ ,
10
V
o
O
/.'
/.'1 / . " :, 1
Strain, %
40
I
"..'"
"..
"..""
--' -
V
/
l/'
//
V 2
.",,'
/'
/ ,1
I
. 1 1
/'
-'~
~
/.,
l /'
V
Strain, %
",'"
--~
70
//
1
2
~
m
-'~
",'
11
'"
a.
:2
140 ui Ul
40
~
2 Strain, %
SS.073 316 annealed slainless sleel bar, cyclic and monolonic slress-slrain curves in air al 627 oC (1160°F)
140,-----,------,------,------,------,------,980
120r------+------+-----~------~--~--F------1840
100r------+------~~--~-,~--~------r------1700
"C¡;
8:.
-'<-
80 ¡-------++-----:;¡,r-----f-------\-------I-----_j 560 :2
~
a)
e
rn
e
~
m
~w
~~ ~ (/)
40¡--~~~----_4~~~4_----_+------+_----_j280
~-----+------+-~---1------~------~----~140
°0~----~0~.5~----1~.0~----~1.~5----~2.~0------2L.5----~3.~ Strain range, %
Source: "Isochronous Stress-Strain Curves for 2Y4Cr-1Mo, Type 304304H, and Type 316-316H Steels," Technical Report 2012-Part 1, United Nuclear Corp., Sept 1970. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1307, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 40
Specimen reduced section 7.4 mm (0.29 in.) diam X 12.7 mm (0.50 in.) long. Solution annealed 699 oC (1920 °P). Cyc1ic test: triangular strain wave form, R = -1, strain rate = 4%/min. Composition: Pe-18Cr13Ni-Mo. UNS S31600 Source: D.S. Wood, J. Wynn, A.B. Baldwin, and P. O'Riordan, Sorne Creep Fatigue Properties of Type 316 Steel at 625 C, Fatigue Eng. Mater. Struct., Vol 3, No. 1, 1980, P 39-57. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1307, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 43
202/Stainless Steel (SS)
100
~
1
- . _. - - --
SS.074 316 annealed and cold-worked stainless steel sheet, stress-strain curves for room and elevated temperatures
700
I
1o
75 °F (24 C) 1400 °F (760 OC) 1600 °F (871°C) 1800 °F (982 OC)
80
.!
Test direction: longitudinal. Sheet thickness = 1.473 mm (0.058 in.). Specimens vacuum annealed, 1093 oC (2000 °F), 15 min, plus 5% and 10% cold worked. Composition: Fe-18Cr-13Ni-Mo. UNS S31600
560
I
10% cold work
5% coldwork 60
~
V-
<ñ (/) ~
1i5
I
40
¡..--
I I
20
1 1 1"-
/
....... ..... ...
1/: .... 1/ ....... .... ;:..:: ('
V-
oO
f--
0.2
0.4
:2
¡i
/ I _./ .~.-' /.' I --
/.
" --
f
_.- .-- -
0.4
0.6
0.2
Strain, %
0.4
0.6
0.8
V
./
/~ r::::V
100
/
~ 80 <ñ (/)
/ rf
~
<1l
40
~
140
o
SS.075 316L stainless steel pi ate, true roomtemperature stress-strain curves showing effects of grain size
980
120
1-
280
~ ~ V
221lmJ /lllm /
165 1lm
840
ro
o..
560 :2 <ñ
~
420 ~
¡!:
280
140
20
O
5
10
60 kg (11 O lb) laboratory heat containing 0.11 % N, annealed 999-1199 OC (1830-2190 °P), water quenched. Strain rate = 0.06/min. Composition: Fe-18Cr-13Ni-Molow C. UNS S31603
700
V
W
o
Source: T.W. Gibbs and H.W. Wyatt, "Short-Time Tensile Properties of Type 316 Stainless Steel at Very High Temperatures," ASME Paper No. 60-WA-ll. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1307, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 28
Strain, %
140
2 60
&.
./
0.2
Strain, %
420
I
1·//
V
1 - - 1-
I
i--
/
Annealed
-
/'
15
20 True strain, %
25
30
35
o
40
Source: L.-A. Norstrom, Influence of Grain Size on Flow Stress in an Austenitic Stainless Steel, Scand. J. Metall., Vol 6 (No. 4), 1977, P 145-150. As published in Aerospace Structural Metals Handbook, Vo12, Code 1307, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 25
Stainless Steel (SS)1203
.¡¡;
50
350
40
280
210
30
SS.076 321 annealed stainless steel sheet, tensile stress-strain curves at room and elevated temperatures Sheet thickness = 1.60 mm (0.063 in.). 0.5-100 h exposure. Composition: Fe-18Cr-lONi-Ti. UNS S32100
al
o..
:;
-'>!
ui
Source: D.E. Miller, "Detenmnation of the Physical Properties of Ferrous and Non-Ferrous Structural Sheet Materials at Elevated Ternperatures," AFfR 6517, Pt 4, Dec 1954. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1308, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 21
ui
VI
VI
~
Cií 140
20
~
10r-~--~-------+-----~------~------r-----~70
L------L------~----~------~
2
______ _____"O ~
3 4 Strain, 0.001 inJin.
5
6
100
-"
80 'F (27 'C) 80
.¡¡;
60
-'>!
ui
'"~
Cií
40
SS.077 321 annealed stainless steel sheet, complete tensile stress-strain curves at room and elevated temperatures
700
V /'
f;::-
---
-~
400 'F (204 'C)
r-
¡.--
420
~
" 800 'F (427 'C)
~
l'
280 Cií
20
140
0.16 0.24 Strain, inJin.
al
o..
:;
............ 1200 'F (649 'C)
0.08
Sheet thickness = 1.016 mm (0.040 in.). 0.5 h exposure. Strain rate = 0.003/s. Composition: Fe-18Cr-lONi-Ti. UNS S32100
560
I
l
~
"-
0.32
o
0.40
Source: H.E. Dedrnan, EJ. Wheelahan, and J.R. Kattus, "Tensile Properties of Aircraft-Structural Metals at Various Rates of Loading after Rapid Heating," WADC TR58-440, Part 1, Nov 1958. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1308, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 21
204/5tainless 5teel (SS)
SS.078 321 annealed stainless steel sheet, tensile stress-strain curves at room and low temperatures
70 r-------r-------,-------.--------,------~490
Sheet thickness = 1.27 mm (0.050 in.). Annealed 1066 oC (1950 °F), air cooled. Composition: Fe-18Cr-lONi-Ti. UNS S32100
~------+-------~~~--~~~----+_------~420
60
50
.¡¡; -'"
~----_,q-~----~------~--------+_------~280 ~
40
::;;:
70°F (21°C)
Source: E.H. Schmidt and E.F. Green, "Fatigue Properties of Sheet, Bar and Cast Metallic Materials for Cryogenic Applications," Rocketdyne R-7564, Aug 1968. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1308, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 22
L--~~~~--~~h=====::j:=======r==~--_J 210 iñ~
~
iñ 30
20 ~~----1--------+--------~------+_------~140
~------+-------~------~--------+_------~70
10
0
L -______L -_ _ _ _
~
2
0
______
~
4
______
~
______
~O
8
6
10
Strain, 0.001 in.lin.
280
240
/
.¡¡; -'"
C/)
120
80
1680
~-320 °F (-196 OC)
j V
160
¡z g
/
/ /
200
1/ / V IvuuL V~
1120~
/
::;;:
~ \-110 °F (-79 oC)
\ Room temperature
840
"
\
560
280
40
0.2
Bar diameter = 19.05 mm (0.75 in.). Composition: Fe18Cr-10Ni-Ti. UNS S32100
1400
\
V
0.1
55.079 321 annealed stainless steel bar, complete tensile stress-strain curves at room and low temperatures
1960
___ -42~ °F (-253 0b¡
0.3 Strain, in./in.
0.4
0.5
o
0.6
ffl
Source: T.F. Durham, R.M. McClintock, and R.P. Reed, "Cryogenic Materials Data Handbook," U.S. Dept. of Cornmerce, 1960. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1308, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 22
Stainless Steel (SS)/205
SS.080 321 annealed stainless steel sheet, compressive stress-strain curves at room and elevated temperatures
350
50
40
Sheet thickness =1.60 mm (0.063 in.). 0.5-100 h exposure. Composition: Fe-18Cr-lONi-Ti. UNS S32100
280
400°F (204 OC) 600°F (316 OC) 800 °F (427 OC) 1000 °F (538 OC)
210
30
~
:2 ui
ui tn
Source: D.E. Miller, "Detennination of the Physical Properties of Ferrous and Non-Ferrous Structural Sheet Materials at Elevated Temperatures," AFTR 6517, Pt 4, Dec 1954. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1308, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 26
tn
~
~
(f)
140
20
10~+-------+---------~--------~--------~70
oOL---------~2------·--~4----------6L-------~80
Strain, 0.001 inJin.
90
-4230Fl-2530C~ ~
80
~ ~OF (-196 OC)
70
60
g¡
50
ui tn
!!? é'i5 40 30
20 10
¿
r
/
V
/
~
630
SS.081 347 annealed stainless steel sheet, tensile stress-strain curves at room and low temperatures
560
Sheet thickness = 1.27 mm (0.050 in.). Composition: Fe18Cr-12Ni-Nb (Nb stabilized). UNS S34700
490 420
350 ~
~
70°F (21°C)
V-
280 (f) ~ 210 140
/
70
V
2
4 6 Strain, 0.001 inJin.
8
Source: E.E Green and E.H. Schmidt, "Fatigue Properties of Metallic Materials for Cryogenic Applications," R-7564, Rocketdyne, Aug 1968. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1309, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 11
206/Stainless Steel (SS)
SS.082 347 stainless steel sheet, tensile stress-strain curves at room and elevated temperatures
4o,-------,--------.-------,--------,-------,28o
Sheet thickness = 1.60 mm (0.063 in.). Composition: Fe18Cr-12Ni-Nb (Nb stabilized). UNS S34700 I----------j¡<--..~--_+------=__i.........=--_=__
_r_==--_='"'" 210
& ::2
~
g ~
Source: "Short-Time High Temperature Data," No. BLR 53-195, Bell Aircraft Corp., 16 July 1954. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1309, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 11
201------+---8-+-------_+--------I--------+---------j 140
ro
~
ro 101--~----~------_+------~--------+_------~70
°0L-------~-------2L-------~3--------~4------~50
Strain, 0.001 in./in.
SS.083 347 annealed stainless steel bar, complete engineering tensile stress-strain curves at room and low temperatures
280r------,------,------,------,------,------, 1960 -423 'F (-253 'C) 2401------_+------~_F--_+------r_----_+----~
1680
2001-------+----~~~~_+------~--~_+----~
1400
-250 'F (-157 OC)
'w
Composition: Fe-18Cr-12Ni-Nb (Nb stabilized). UNS S34700
1601-------+-t~~~-----+------~----_+----~ 1120~
-'"
::2
840
560
401-------+------~-----+------r------+----~
0.1
0.2
0.3 Strain, in.lin.
0.4
0.5
280
O
0.6
i'"
Source: K.A Warren and R.P. Reed, Tensile and Impact Properties of Selected Materials from 20 to 300K, Monograph 63, National Bureau of Standards, 28 June 1963. As published in Aerospace Structural Metals Handbook, Vo12, Code 1309, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 12
Stainless Steel (SS)1207
SS.084 347 stainless steel, general, complete engineering tensile stress-strain curves at room and elevated temperatures
700
100 Room temperature
.¡¡;
Compositíon: Fe-18Cr-12Ni-Nb (Nb stabilized). UNS S34700
560
80
420
60
'"
c..
-"
;¡;
400°F (204 OC)
Source: Properties of AISI Type 347 and 348 Stainless Steel, Bettis Plant Materials Manual, Westinghouse, May 1957. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1309, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 12
(f)
~
~
1i5 280
40
(f)
20~--------~---------~~--------~--------~140
ooL---------o~.2---------0~.4----------0.L6--------~0.R Strain, in./in.
SS.085 347 mili annealed stainless steel bar, complete true tensile stress-strain curves at room and low temperatures
550r-----,-----,-----,-----,-----,-----,---~3850
500~----~----+-----~~L-+-----+-----+---~3500
Bar diameter = 12.7 mm (0.5 in.). Composition: Fe-18Cr12Ni-Nb (Nb stabi1ized). UNS S34700
450r-----t_----t_---¿~----+_----+_----+_--~3150
400r-----~-----t_~--t_----+_~~~
2450
'"
c..
;¡;
2100
~ 1750 ~
1400 1050 700 50r---~~--~-----t----_+----~----~--~
350
°0L-----OL.2-----0L.4~---OL.6-----0~.8-----1~.0----~----~ 0
1.2
True strain, in./in.
1.4
~
Source: T.S. DeSisto and EL. Carr, "Low Temperature Mechanical Properties of 300 Series Stainless Steels and Titanium," WAL TR 323, 4/1, Watertown Arsenal Laboratories, Dec 1961. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1309, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 12
208/Stainless Steel (SS)
60
420
55.086 347 annealed stainless steel sheet, compressive stress-strain curves at room and elevated temperature
350
Sheet thickness = 1.60 mm (0.063 in.). Composition: Fe18Cr-12Ni-Nb (Nb stabilized). UNS S34700
280 ro o:2
'00
-'"
ui
Source: D.E. Miller, "Detennination of the Physical Properties of Ferrous and Non-Ferrous Structural Sheet Materials at Elevated Temperatures," AFTR 6517, Pt 4, Dec 1954. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1309, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 16
210 ui
~
~
Cií 20
140
10
70
L-------~------~2------~3------~k-----~50
Strain, 0.001 in./in.
55.087347 stainless steel pi ate, complete true tensile stress-strain curves at room and low temperatures
450,------,------,------,------,------,------, 3150 / -452 °F (-269 OC) 400~----~------~--~~------~----~------1
2800 2450
-
2100 ro
Il.
1750 ~
'"
1400 1050 hó.~~~-----+------~----~----_4----__1700
~-T---+-
347 weld metal~
9
347 parent meta~
e 0.252 in. O
350
°0L------OL.2------0L.4------0L.6------0L.8------1L.0----~1.f
True strain, in./in.
~
~
Plate thickness = 15.875 mm (5/8 in.). Comparison of parent metal (solid line) and weld metal (dashed line). Butt welded with type 347 coated stick electrodes and annealed after welding. Composition: Fe-18Cr-12Ni-Nb (Nb stabilized). UNS S34700 Source: T.S. DeSisto, "Low Temperature Mechanical Properties of Base and Weld Deposits of Selected Austenitic Stainless Steels," AMRA TR 63-08, United States Army Materials Research Agency, July 1963. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1309, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 21
Stainless Steel (SS)1209
120
O~
430 100
Pmax
r~
80
~ cñ ti)
~ 60 Ol
~
40
20
tt
/
V
~ ~
~
? ~
(B06 °F)
•
C\
~
~
\
,, ,, ,
"'"
I~ ~
"-
,
, In
~
,,
560
i:.
6
:2 cñ
\I
420 ~ tí
~
Ol
~ 816 oC (1500 °F)
280
-.() --,o
n
\0
~
•
~ P
\
\ b
'~
"
700 \ \
Q
•
650°C - ...
~
~ P max
~q
\
~¡--.r
.;.;
~
'-
~ PJ430°C
650 oC (1200 °F)
P max
/::::-0
840
~-,
816°C
•
•
11"
-....,
140
max
0.12
0.2
0.3
0.4
0.5
0.6
0.7
0.8
0.9
1.0
1.1
1.2
o
Total true strain
55.088 348 annealed stainless steel bar, true stress-strain curves at room and elevated temperatures
Bar diameter = 6.35 mm (0.25 in.). Data were collected at constant axial true strain rates of 0.004 (open data points) and 0.00004 (solid data points). The curves for the higher strain rates are aboye the other curve at 650 and 816 oC (1202 and 1580 °P), while the reverse is true for 430 oC (806 °P). Contrary to what is expected for true stress-strain curves, these have a maximum point. This is believed to be due to the formation of internal voids that reduce the actual area under stress. Por this reason the lines are dashed as they approach the fl'acture point. Proa. is the point of maximum load. Composition: Pe-18Cr-12Ni-Nb(Nb stabilized, Ta and Co restricted). UNS S34800 Source: J.B. Conway, R.H. Stentz, and J.T. Berling, "Fatigue, Tensile, and Relaxation Behavior of Stainless Steels," Technical Information Center, USAEC, 1975, P 215
210/Stainless Steel (SS)
80
560
70
.... r-
60
l I!
-A~
ro-
-
430 oC
V
----a
.a
~
~
O
~=-
f
7'
~
It
~~ \
\
~
816 oC (1500 °F)
350 :2
¡z
i'. . .'U
~ 280 :;
.'b
c:
\
~'tt
0.3
0.4
0.5
0.9
1.2
1.4
'g> UJ
b 140
-.
r-¡
0.8
c:
210
A~
816 oC
0.7
0.6
(j)
\
1.6
--- ....... o
70
a
-
;..
0.2
0.1
.~
q
\
"'7'
••
a
10
o
ro
O-
\
!--o-
\
aa
-
420
~
-1---
"
I~
v
650 oC (1200 °F)
v
Y
20
490
430 oC (806 °F)
1.8
2.0
2.2
Engineering strain
SS.089 348 annealed stainless steel bar, engineering stress-strain curves at room and elevated temperatures Bar diameter = 6.35 mm (0.25 in.). Data were collected at constant axial true strain rates of 0.004 (open data points) and 0.00004 (solid data points). Same data was used as for the true stress-strain curve. The curves for the higher strain rates are aboye the other curve at 650 and 816 oC (1202 and 1580 °F), while the reverse is true for 430 oC (806°F). The strain rate effect is more pronounced for the higher temperatures. The lines are dashed as they approach the fracture point. Composition: Fe-18Cr-12NiNb(Nb stabilized, Ta and Co restricted). UNS S34800 Source: J.B. Conway, R.H. Stentz, and J.T. Berling, "Fatigue, Tensile, and Relaxation Behavior of Stainless Steels," Technical Information Center, USAEC, 1975, P 217
300
2100
SS.090 Metastable austenitic stainless steel sheet, engineering stress-strain curves showing effect of varying carbon content at room temperature
250
1750
Sheet thickness = 1.27 mm (0.050 in.). After 80% reduction in thickness at 450 oC. Crosshead speed 0.04 in./min. Composition: Fe-9Cr-8Ni-3Mn with 0.2-0.5C
1400
Source: D. Fahr, Stress and Strain-Induced Formation of Martensite and lts Effects on Strength and Ductility of Metastable Austenitic Stainless Steels, Metal!. Trans. A, July 1971, P 1887
~C
," -,
200
r
'00
-'"
0j4C/
~~-rc ~3C ¿~
V J
ro
o-
! :2
1050
~
é'ií
rn
100
700
50
350
o
O
10
20 Strain, %
30
Stainless Steel (SS)1211
SS.091 Metastable austenitic stainless steel, roomtemperature engineering stress-strain curves
300 ,---------,----------.---------,----------,21oo
250
Effect of different rolling temperatures is shown. Reduction in thickness = 80%. Composition: 9Cr-8Ni-lMnO.4C-bal Fe
200 ~----_7~1---------_+--------~--------~1400
Source: D. Fahr, Stress and Strain-Induced Forrnation of Martensite and Its Effects on Strength and Ductility of Metastable Austenitic Stainless Steels, Metal!. Trans. A, July 1971, P 1889-1890
'"
.¡¡;
a.
-""
rñ
UJ
~
:2
150 r---------1---------_+--------~--------~1050~ ~
en
100 ~--------4_--------_+--------~----------1700
50 ~--------4_--------_+--------~._--------1350
OL---------~10-----------2LO--------~3LO--------~4~ O Strain, %
2100
250
1750 (\
200 .¡¡; -"" rñ UJ
!'! iií
SS.092 Metastable austenitic stainless steel, roomtemperature engineering stress-strain curves
300
150
100
n í
180%
1400
6O %
.....--
i--
'"
a.
40%
:2 1050
~
1
,
¡'-h 20% 700
i
50
350
10
Effect of varying reductions in thickness (and roHing times) at 450 oc rolling temperature is shown for a relatively unstable aHoyo Crosshead speed = 0.04 in./min. Composition: 9Cr-8Ni-2Mn-0.2C-bal Fe
20 Strain, %
30
Source: D. Fahr, Stress and Strain-Induced Forrnation of Martensite and Its Effects on Strength and Ductility of Metastable Austenitic Stainless Steels, Metall. Trans. A, July 1971, P 1889-1890
212/5tainless 5teel (SS)
55.093 Metastable austenitic stainless steel, roomtemperature engineering stress-strain curves
300 ,---------,----------,---------,---------,2100
Effect of varying reductions in thickness (and rolling times) at 450 oC rolling temperature is shown for a relatively unstable alloy. Crosshead speed = 0.04 in./min. Composition: 9Cr-8Ni-2Mn-0.2C-bal Fe
~--------+-------~~~~----~--------~1750
250
200 ~------~4-----~_r~------~~~------~1400 20%
~ ",-
~'"
ro
o..
::;;
Source: D. Fahr, Stress and Strain-Induced Formation of Martensite and Its Effects on Strength and Ductility of Metastable Austenitic Stainless Steels, Metall. Trans. A, July 1971, P 1889-1890
150 ~--------~~~----~~~-----4----------;1050~
~
(/)
100 ~----~~~--------~---------4----------;700
50 ~--------~--------~---------4----------;350
O O
20
10
30
Strain, %
h 1/ ji
200 '00
'"
~
150
1750 Um.mp,red
1400 ro
o..
::;;
1050
1(1
Uí
700
50
350
O
~
~
100
o
Effect of annealing 450 oC, 80 min, on partially transformed (M s > room temperature) alloy (alloy 681113). 60% reduction in thickness at 450 oc. Crosshead speed = 0.04 in./min. Composition: 9Cr-8Ni-2Mn-0.1Cbal Fe
Tempered
/
250
"'ui"
55.094 Metastable austenitic stainless steel, roomtemperature engineering stress-strain curves
2100
300
10
20 Strain, %
30
Source: D. Fahr, Stress and Strain-Induced Formation of Martensite and Its Effects on Strength and Ductility of Metastable Austenitic Stainless Steels, Metall. Trans. A, July 1971, P 1889-1890
Stainless Steel (SS)/213
/'"'
250
;v
.¡¡¡ -'"
'" ~
/ '/
A
200
(/)
SS.095 Metastable austenitic stainless steel, roomtemperature engineering stress-strain curves
2100
300
~ 2 Mn
~
........
1750
Effect of varying manganese content after 80% reduction in thickness, 450 oc. Crosshead speed 0.04 in./min. Composition: 9Cr-8Ni-lMn-0.3C-bal Fe
1400
Source: D. Fahr, Stress and Strain-Induced Forrnation of Martensite and Its Effects on Strength and Ductility of Metastable Austenitic Stainless Steels, Metall. Trans. A, July 1971, P 1885-1886
~3Mn
8:.
::2
150 - '
1050 ~
iií
iií
100
700
50
350
o
10
O
20
30
Slrain, %
300
250
f'\. 200
~/
// L~ ~
V
.¡¡¡ -'"
SS.096 Metastable austenitic stainless steel, roomtemperature engineering stress-strain curves
2100
~1Mn 2 Mn
1
3Mn
1750
Effect of varying manganese content after 80% reduction in thickness, 450 oc. Crosshead speed 0.04 in./min Composition: 9Cr-8Ni-lMn-OAC-bal Fe
1400
Source: D. Fahr, Stress and Strain-Induced Formation of Martensite and Its Effects on Strength and Ductility of Metastable Austenitic Stainless Steels, Metall. Trans. A, July 1971, P 1885-1886 ro
o..
::2
'" 150
1050 ~
(/)
~
iií
iií
100
700
50
1--.
o
O
350
10
20 Slrain, %
30
214/Stainless Steel (SS)
SS.097 S24000 (Nitronic 33) and S30400 (304) stainless steel bar, typical engineering tensile stressstrain curves. UNS S24000, S30400
490
70
/
S24000
60
(Nitronic 33)
50
0.2% offset yield strength
420
Test direction: longitudinal. Modulus of elasticity for Nitronic 33 = 199 OPa (28.8 x 106 psi) at room temperature. USN S24000, S30400
I
CI)
280 ~ :::;:
(Type 304)
ui
~'"
Source: Product Data, S-53b, Arrnco Steel Corp., 1977
I S30400
40
.¡¡; -'"
350
ui
30
210
20
140
10
70
00
2
120
6
5
3 4 Strain, 0.001 in./in.
Ultimate t~nsile strenglh
110
'"~
en
O
SS.098 UNS S21800 (Nitronic 60) stainless steel rod, room-temperature engineering stress-strain curves
840 770
In steel tension. Rod diameter = 9.525 mm (3/8 in.). 100
700
90
630
80
.~/ & :,.'1f/ ",0
__ 70
g¡ ¡i 60
o
§~/
~
en
~
L
20
."", Proportional / limil /
/ V
/
yield slrength
490 (L '" :::;: 420 ui 350
II
30
/
~---
¡.....-/ 0.2% offset
V'
¿
40
10
560
o?5
50
280
,/
210 140
/
70
/ 2
Ultimate tensile strength = 765 MPa (111 ksi). 0.2% yield strength = 483 MPa (70 ksi). Modulus of elasticity = 181 OPa (26.2 x 106 psi). Elongation = 69%. Reduction of area = 71 %. Developed with class B extensometer. Composition: Fe-17Cr-8.5Ni-8Mn-4Si. UNS S21800
3 4 Strain, 0.001 in./in.
5
6
~
CI)
Source: Steel Company Technical Literature, Arrnco. As published in Structural Alloys Handbook, Vol 2, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1994, p 49
5tainless 5teel (55)/215
2oor-.----~----,_----,_----._----_,----_r----_,1400
Sheet thickness = 1.6 mm (0.063 in.). Treatment: 982 oC (1800 °F), 30 min, oil quenched, 371°C (700°F), 1 h, air cooled. Composition: Fe-12Cr-lowC. UNS S41000
160~----+---~+-----1-----~----~----_+----~1120
75°F (24 OC) I 800°F (427 OC) 120 ~----~----r_~~~~_1----~----_+----_1840
o..'"
·00
"'.;"
::;; .;
1000 °F (538 OC)
'" ~ 80
SS.099 410 stainless steel sheet, tensile stress-strain curves at room and elevated temperatures
Source: W.W. Gerberich, H.E. Martens, and RA. Boundy, "Tensile Properties of Five Low-Alloy and Stainless Steels under High-HeatingRate and Constant-Temperature Conditions," Technical Report No. 32222, Jet Propulsion Laboratory, June 1962. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1401, CINDASIUSAF CROA Handbooks Operation, Purdue University, 1995, p 24
~----+_~~+_~~-~----~----~----_+----_1560 ~
40~--+.~----+_----1_----~----~----_+----~280
.J--+--t-----r 1200 °F (649 OC)
L-----~
2
____
~
____
4
~
6
_____ L_ _ _ __ L_ _ _ _
8
10
~
____
12
~O
14
Strain, 0.001 in.lin.
SS.100 410 stainless steel bar, true stress-strain curves at various temperatures
280r-------,---------.------~--------r_----__,1960
-320°F (-196 OC)
Bar diameter = 19.05 mm (0.750 in.). Treatment: 982 oC (1800 °F), 1 h, oil quenched, 427 oC (800°F), 4 h, air cooled. Composition: Fe-12Cr-lowC. UNS S41000 1680
o..'"
·00
"'.;" '"~
::;; .;
'"
~
tí
CI)
CI)
::l
F
~ 1400
1600~-------0~.2------~OL.4-------0~.6--------0L.8------~1.d120 True strain, in.lin.
Source: R Chait and V. Weiss, "Isothermal True Stress-Strain Curves of Body Centered Metals," Report No. MET. E. 1081-0666, Syracuse University Research Institute, June 1966; see also R Chait, "Deformation and Fracture of High Strength BCC Polycrystalline Alloys," Ph.D. thesis, Syracuse University, 1967, available from University of Michigan, Order No. 68-5451. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1401, CINDASIUSAF CROA Handbooks Operation, Purdue University, 1995, p 24
216/Stainless Steel (SS)
SS.101 410 stainless steel bar, stress-strain curves at room and low temperatures
2450
350 20 K
~K
250
.¡¡;
200
""'vi
~ C/)
150
Bar diameter = 19.05 mm (0.750 in.). Treatment: 982 oC (1800 °P), 1 h, oil quenched + tempered 371°C (700 °P), 4 h, air cooled, to 42 HRC hardness. Composition: Pe12.2Cr-0.12C-0.5Mn-0.2Si-0.02P-0.01S. UNS S41000
2100
300
1750
---- ----=:::::: ~
1400
vi
~95K
~
1050 é'i5
Room temperatl~
100
700
50
350
0.04
8: :2
0.08 0.12 Strain, in./in.
0.16
o
0.20
SS.102 420 stainless steel sheet, tensile stress-strain curves at room and elevated temperatures
1400
200
Test direction: longitudinal. Sheet thickness = l.575 mm (0.062 in.). Treatment: 982 oC (1800 °P), 15 min, oil quenched, 482 oC (900 °P), 3 h. Composition: Pe-130'0.35C. UNS S42000
1120
160
Room temperature 400°F (294 OC) 800°F (417 oC) )1,-1000 h
.¡¡;
840
120
ro
o.. :2
""'uf
uf
~
~
560
80
40~--~~~---4------+------+------r-----~280
L-----~----~------~----~----~1~0----~1~
Strain, 0.001 in./in.
Source: K.A. Warren and R.P. Reed, Ténsile and Impaet Properties of Seleeted Materials from 20 to 300K, Monograph 63, National Bureau of Standards, June 1963. As published in Struetural Alloys Handbook, Vol 2, CINDASlPurdue University, 1995, p 22
é'i5
Source: J.R. Kattus, J.B. Preston, and H.L. Lessley, "Detennination of Tensile, Compressive, Bearing, and Shear Properties of Sheet Steels at Elevated Temperatures," WADC TR 58-365, ASTIA Document No. 206075, Southern Research Institute, Nov 1958. As published in Aerospaee Struetural Metals Handbook, Vol 2, Code 1402, CINDASI USAF CRDA Handbooks Operation, Purdue University, 1995, p 8
Stainless Steel (SS)/217
55.103 420 stainless steel sheet, compressive stress· strain curves at room and elevated temperatures
2oor------r------~----_,------,_------r_----~1400
Test direction: longitudinal. Sheet thickness = 1.575 mm (0.062 in.). Treatment: 982 oC (1800 °P), 15 min, oil quenched, 482 oC (900 °P), 3 h. Composition: Pe-13Cr0.35C. UNS S42000
160~-----+------+-----~~~~~------r_----~1120
120~----~------+.~-,~------~------r-----~MO
&.
:2 ui If) ~
80~-----+--~~~~~~~~--~------r_----~560
1ñ
Source: J.R. Kattus, J.B. Preston, and R.L. Lessley, "Determination of Tensile, Compressive, Bearing, and Shear Properties of Sheet Steels at Elevated Temperatures," WADC TR 58-365, ASTIA Document No. 206075, Southem Research Institute, Nov 1958. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1402, CINDAS/ USAF CRDA Randbooks Operation, Purdue University, 1995, p 9
__ - 100 h : •• - - 1000 h 40~--~~------+_----~------~------r_----__1280
L------L------~----~
2
4
______
6
~
8
______
~
10
____
_"O 12
Strain, 0.001 in.lin.
200,---------,----------,----------,----------,1400
160~--------_r--------~----------+_--------__11120
Room temperature
55.104 422 stainless steel sheet, tensile stress·strain curves at room and elevated temperatures Test direction: longitudinal. Sheet thickness = 1.575 mm (0.062 in.). Treatment: 1038 oC (1900 °P), 15 min, oil quenched, 538 oC (1000 °P), 2 h. Composition: Pe-12Cr0.23C-IMo-l W-0.8Ni-0.25Y. UNS S42200 Source: J.R. Kattus, J.B. Preston, and R.L. Lessley, "Determination of Tensile, Compressive, Bearing and Shear Properties of Sheet Steels at Elevated Temperatures," WADC TR 58-365, AS TIA Document No. 206075, Southem Research Institute, Nov 1958. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1403, CINDAS/ USAF CRDA Randbooks Operation, Purdue University, 1995, p 10
r-----~~-r--------~----------+_--------__1280
~------~2~----·--~4~------~6--------~8·0
Strain, 0.001 in.lin.
218/Stainless Steel (SS)
SS.105 422 stainless steel sheet, compressive stressstrain curves at room and elevated temperatures
1400
200
Room temperature
160
1120
840
120
Test direction: longitudinal. Sheet thickness = 1.575 mm (0.062 in.). Treatment: 1038 oC (1900 °F), 15 min, oil quenched, 538 oC (1000 °F), 2 h. Composition: Fe-12Cr0.23C-IMo-l W-0.8Ni-0.25Y. UNS S42200
'"
a.
'00
.l<
en
:2 rñ (J)
Cií
Cií
rñ ~
~
560
80
Source: J.R. Kattus, J.B. Preston, and H.L. Lessley, "Determination of Tensile, Compressive, Bearing and Shear Properties of Sheet Steels at Elevated Temperatures," WADC TR 58-365, ASTIA Document No. 206075, Southern Research Institute, Nov 1958. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1403, ClNDASI USAF CRDA Handbooks Operation, Purdue University, 1995, p 12
40~--~~r-------+-------~-------r------~280
°0~------~2--------4L-------~6~------~8------~1~
Strain, 0.001 in./in.
SS.106 AFC-77 stainless steel sheet, tensile stressstrain curves at room and elevated temperatures
225,-----,,------,-----,,------,------,-----,1575 200~----~------~----~------~~=
1400
Test direction: L, longitudinal; T, transverse. Sheet thickness = 2.54 mm (0.10 in.). Tempered at 371°C (700°F). Treatment: 1038 oC (1900 °F), 15 min in protective atmosphere, oil quenched, -73 oC (-100°F), 30 min, 371°C (700 °F), 2 + 2 h. Composition: Fe14.5Cr-13.5Co-5Mo-0.5V-0.15C. UNS S65770
1225 150~----1-----_+--~~~~~~
1050
'"
g¡ 125 ~----~------IIh~«--~------~----_+----____j 875
~
00
00
~
(JJ
700 ~
Cií 100
75~----~~~--~----~------~----_+----____j525
50~--~~------~----_+------r_----_+----____j350
25~"--~------~----_r------~----_r----____j175
~-----2L------4L------6L------L------L-----~1l
Strain, 0.001 in./in.
Source: O.L. Deel and W.S. Hyler, "Engineering Data on Newly Developed Structural Materials," Technical Report AFML-TR-67-418, April 1968, P 145. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1509, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 10
Stainless Steel (SS)/219
SS.107 AFC-77 stainless steel sheet, tensile stressstrain curves at room and elevated temperatures
225,-----,------,------,------,-----,------,1575 200~----~-----4------+-----~~_
1400
175~----~----~------~77L-_r----~r_~)
1225
Test direction: L, longitudinal; T, transverse. Sheet thickness = 2.54 mm (0.10 in.). Tempered at 593 oC (1100 °P). Treatment: 1038 oC (1900 °P), 15 min in protective atmosphere, oil quenched, -73 oC (-100 °P), 30 min, 593 oC (1100 °P), 2 + 2 h. Composition: Pe14.5Cr-13.5Co-5Mo-0.5V-0.15C. UNS S65770
150~----·~----_4--~~~~--~----~r_~~1050 al
~125~----~----~~~--+------r------r------875~
~
m w
~
m100
molen
Source: O.L. Deel and W.S. Hyler, "Engineering Data on Newly Developed Structural Materials," Technical Report AFML-TR -67 -418, April 1968, P 160. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1509, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 11
75~----~~~_4------+_----~------r_--__4525
50~--~~----_+--·----+------r----~----~350
~,,~-~-----+--·----+-----~----~----~175
L-----~2------~4------~6------8L-----~10----~1;
Strain, 0.001 inJin.
225,-----,------,------,------,-----,------,1575
SS.108 AFC-77 stainless steel sheet, compressive stress-strain curves at room and elevated temperatures
200~----~----_+------+__.~~~--~--~~1400
150~-----r----_+_,~~+------r----~----~1050
al
~125r------4-----~~----~----~----_4----~875~
~~
~
m100
700
75~----~~--_+------+_----~----~----~525
50~--~~----_+------+_----~----~----~350
~~---r-----4------+_-----r----~----~175
°0~-----~2------~4------~6------8L-----~1-0----~1;
Sirain, 0.001 inJin.
Ien
Test direction: longitudinal and long transverse. Sheet thickness = 2.54 mm (0.10 in.). Tempered at 371°C (700 0F). Treatment: 1038 oC (1900 °P), 15 min in protective atmosphere, oil quenched, -73 oC (-100 °P), 30 min, 371°C (700 °P), 2 + 2 h. Composition: Fe14.5Cr-13.5Co-5Mo-0.5V-0.15C. UNS S65770 Source: O.L. Deel and W.S. Hyler, "Engineering Data on Newly Developed Structural Materials," Technical Report AFML-TR-67-418, April 1968, P 147. As published in Aerospace Structural M etals Handbook, Vol 2, Code 1509, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 14
220/Stainless Steel (SS)
275 250
~OO °F (316 OC)
/#
200
~~
175
//
150
'" IJ)
ID
&5 125 100
f
75 50 25
1750
/" ~Td,
225
g¡
SS.109 AFC-77 stainless steel sheet, compressive stress-strain curves at room and elevated temperatures
1925
70°F (21°C) Land T
I
/
J
P
1575 TL ~800~F(427oe)
-
l·
1400
f1ó00 °F (!538 OC) Land T
V
1225 ro
1050 ~
~
'" Cií IJ)
~
875 700
Test direction: L, longitudinal; LT, long transverse. Sheet thickness = 2.54 mm (0.10 in.). Tempered at 593 oC (1100 °F). Treatment: 1038 oC (1900 °F), 15 min in protective atmosphere, oil quenched, -73 oC (-100°F), 30 min, 593 oC (1100 °F), 2 + 2 h. Composition: Fe14.5Cr-13.5Co-5Mo-0.5V-0.15C. UNS S65770 Source: O.L. Deel and W.S. Hyler, "Engineering Data on Newly Developed Strnctural Materials." Technical Report AFML-TR -67 -418, April1968, P 162. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1509, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 14
525
~
350 175
2
4
6
10
8
Strain, 0.001 in.lin.
240r-----~-----.------,_----_.------r_----~1680
SS.110 13-8 PH Mo stainless steel bar, stress-strain curves with effect of aged condition
H 1000 H950 200~----4-----~------+-~~~~--
1400
Bar diameter = 19.05 mm (0.75 in.). Composition: Fe13Cr-8Ni-2Mo. UNS S13800
1120
Source: P.W. Johnson, Ir., Arrnco Steel Corp., Baltimore, MD, personal cornrnunication with c.l. Hickey, Ir., Feb 1973. As published in Aerospace Structural Metals Handbook, Vo12, Code 1510, CINDASI USAF CRDA Handbooks Operation, Purdue University, 1995, p 15
ro :2
c..
~
gf 120
840", IJ)
~
~
Cií 80
560
40
280
~----~2L-----~4------~6------~8------1LO----~1;
Strain, 0.001 in./ín.
Stainless Steel (SS)/221
320
55.111 13-8 PH Mo stainless sleel bar, lrue stressslrain curves with effecl of heal lrealment
2240
4
240
1680 3 2
.¡¡; --'"
'"
D..
::;:
IJ)
~
IJ)
1120 ~
iií 160
IJ)
Q)
Q)
~
::;¡
~
80
Test direction: transverse. Strain rate = 0.OO4/rnin. Heat treatment: curve 1,899 oc (1650 °P), 0.5 h; curve 2, 899 oc (1650 °P), 0.5 h, 599 oc (1110 °P), 4 h; curve 3, 899 oc (1650 °P), 0.5 h, 449 oc (840 °P), 4 h; curve 4, 899 oc (1650 °P), 0.5 h, 527 oC (980 °P), 4 h. Composition: Pe-13Cr-8Ni-2Mo. UNS S13800 Souree: V. Seethararnan, M. Sundarararnan, and R. Krisknan, Preeipitation Hardening in a PH 13-8Mo Stainless Steel, Mater. Sci. Eng., Vol 47 (No. 1), Jan 1981, p 1-11. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1510, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 15
560
L -________L -_________L __ _ _ _ _ _
0.01
0.02
~
________
0.03
~O
0.04
True plastic strain
240,-----,------,------,------,------,------,1680 Room temperature 200~----·~------~----~----~~~
1400
~ &. ::;: gf 120 1-------+--------1-r--H;¡C--_+_----____/_------+_----------I 840 gf
~
~
en
1000 °F (538 OC) 80~----~~~~~----_+_----_+------+_----~560
401----~~-------1------_+_----____/_------+_----_1280
°0~~-----2~-----4L------~6L-----~8------~10~--~1l Strain, 0.001 inJin.
en
55.112 13-8 PH Mo H1000 slainless sleel bar, slressstrain curves al room and elevaled temperalures Bar diameter = 19.05 mm (0.75 in.). Aging treatment: 538 oC (1000 °P), 4 h, air cooled. Composition: Pe-13Cr8Ni-2Mo. UNS S13800 Souree: P.W. Johnson, Jr., Armeo Steel Corp., Baltimore, MD, personal eornmunieation with C.I. Hiekey, Jr., Feb 1973. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1510, CINDASI USAF CRDA Handbooks Operation, Purdue University, 1995, p 21
222/5tainless 5teel (SS)
55.113 13-8 PH Mo H 1000 stainless steel bar, stressstrain curves at room and low temperatures
320,-----,---------,----------,---------,2240
Bar diameter = 19.05 mm (0.75 in.). Aging treatment: 538 oC (1000 °F), 4 h, air cooled. Data represent one test from one heat, according to Arrnco Data Bulletin S-24, 1984. Composition: Fe-13Cr-8Ni-2Mo. UNS S13800
-320 °F (-196 OC) 2401------+-------+--__~-~~~~~--I1680 -150 °F (-101 OC)
I
~
8:.
Room temperature
:2
gf 160 1------+------/-++->'---+------+------11120 gf ~
Souree: P.W. Johnson, Jr., Armeo Steel Corp., Baltimore, MD, personal eommunieation with C.I. Hiekey, Jr., Feb 1973. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1510, CINDAS/ USAF CRDA Handbooks Operation, Purdue University, 1995, p 21
w ~
00
801----~~+-----~-----+----~560
°0~--------~4--------~8----------1~2--------~1;
Strain, 0.001 in./in.
/
200
160
80
40
5S.114 13-8 PH Mo Hl000 stainless steel bar,
1680
240
/
/
/
/
compressive stress-strain curve
V--
/
1400
Bar size = 50.8 x 152.4 mm (2 x 6 in.). Aging treatment: 538 oC (1000 °F), 4 h, air cooled. Composition: Fe-13Cr8Ni-2Mo. UNS S13800
1120
Souree: P.W. Johnson, Jr., Armeo Steel Corp., Baltimore, MD, personal eommunieation with C.I. Hickey, Jr., Feb 1973. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1510, CINDAS/ USAF CRDA Handbooks Operation, Purdue University, 1995, p 19
a.
:2
840 ID cii
~
(J)
560
280
4
8
Strain, 0.001 in./in.
12
5tainless 5teel (55)/223
SS.115 13-8 PH Mo H1000 stainless steel forging, compressive stress-strain curves at room and elevated temperatures
225 r-----,_----~------,_----,_----~----_.1575 200 ~----~----_+--·----~~~~~--_+----~1400 175
Test direction: longitudinal. Forging size = 101.6 x 127 mm (4 x 5 in.). Aging treatment: 538 oC (1000 °F), 4 h, air cooled. Composition: Fe-13Cr-8Ni-2Mo. UNS S 13800
1225
150 .¡¡; -'"
al
125 ~----~----_+~~~r_----~~--~~--~875~
UJ
~
UJ
100 ~----~--~~~~--~----~----_T----~700: (J)
Source: O.L. Deel and H. Mindlin, "Engineering Data on New Aerospace Structural Materials," AFML-TR-72-196, Vol 2, Sept 1972. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1510, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 23
75 ~-----~~~_+------~----~----_T----~525 ~---7~~--_+------~----4_----_+----~350
~~L--4_----_+------~----4_----_+----~175
L-----~2L-----~4--·----~6------8L-----~10~--~1f
Strain, 0.001 in./in.
250
200
.¡¡;
/
150
V ----
~
/
Source: MIL-HDBK-5H, Dec 1998, p 2-157 c..
oí UJ
! 700 350
4
al
:;
/ 2
1400
1050
/
100
Test direction: longitudinal. Bar thickness = 19.05-50.8 mm (0.750-2.000 in.). Aging treatment: 538 oC (1000 °F), 4 h, air cooled. Ramberg-Osgood parameter: n = 17. Composition: Fe-13Cr-8Ni-2Mo. UNS S13800
f.---
JI
-'"
50
SS.116 13-8 PH Mo Hl000 stainless steel bar, typical tensile stress-strain curve at room temperature
1750
6 Strain, 0.001 in./in.
8
10
o
12
224/Stainless Steel (SS)
250
o
Compressive tangent modulus, GPa 70 105 140
35
'-.... 200
-----
./'
/
/
150
'"~
Cñ
100
V
-r----V--
~
V I
'00 -"
50
r---
/
SS.117 13-8 PH Mo H1000 stainless steel bar, typical compressive stress-strain and compressive tangent modulus curves at room temperature
175
Test direction: longitudinal. Bar thickness = 22.225-50.8 mm (0.875-2.000 in.). Aging treatment: 538 oC (1000 °F), 4 h, air cooled. Ramberg-Osgood parameter: n = 17. Composition: Fe-13Cr-8Ni-2Mo. UNS S13800
1400
Source: MIL-HDBK-5H, Dec 1998, p 2-157 1050
ro c.. 2
'"
700
~
350
o
10
12
25 15 20 10 Compressive tangent modulus, 106 psi
30
6
4
2
8
Strain, 0.001 in./in.
I
o
5
240
- '" ",
r' 1 - -
200
r--
180
--,...
220
160
V
......
~
',~
'.
"
,-
'\,\
g¡ gj" 120 ~
Source: MIL-HDBK-5H, Dec 1998, p 2-158
.....
H950
1120
1'-,
"
H1100
"x
H1050
980 ro c.. 2 840 gj" ~
700 Cñ
80
560
60
420
40
280
20
140 0.02
0.04
0.06
0.08 0.10 Strain, in./in.
Test direction: longitudinal. Based on one heat. Composition: Fe-13Cr-8Ni-2Mo. UNS S13800
1260
H1000
~
100
1400
....
"" "'~"
._ 140
Cñ
1540
"
....
SS.118 13-8 PH Mo stainless steel bar, typical tensile stress-strain curves (fuI! range) at room temperature for various heat treat conditions
1680
0.12
0.14
0.16
o
0.18
Stainless Steel (SS)/225
240 210 Transverse
180
I
150 .l<
ui
~
120
30
/
Test direction: longitudinal and transverse. Sheet thickness = 1.27 mm (0.050 in.). SRH aging treatment: 927 ° C (1700 °F), 1 h, -73 oC (-100°F), 8 h, 566 oC (1050 °F), 1 h, air coo1ed. Composition: Fe-14Cr-8Ni2.5Mo-Al. UNS S14800
1050
'"
o.. ::¡;
840 ui
'" ~
420 210
4
2
6 8 Strain, 0.001 in.lin.
10
O
12
14
200
SS.120 15-5 PH stainless steel bar, typical tensile stress-strain curves at room temperature for various heat treat conditions
1400 H925 H1025
.¡¡;
Source: "Fatigue Evaluation of PHI4-8Mo (SRH1050) AHoy," Arrnco Steel Corp., Advanced Materials Div., 17 Sept 1969. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1507, CINDAS/ USAF CRDA Handbooks Operation, Purdue University, 1995, p 8
630
/ )v
60
1470
00ngitudina,
j¡V
90
SS.119 14-8 PH Mo SRH1050 stainless steel sheet, stress-strain curves
1260
//
.¡¡; Ul
~
p-
1680
160
1120
120
840
Test direction: longitudinal. Bar thickness = 25.4--31.75 mm (1.000-1.250 in.). Ramberg-Osgood parameters: n(H925) = 13, n(H1025) = 24, n(Hll00) = 22, n(H1150) = 9.0, n(H1150M) = 7.8. Composition: Fe-15Cr-5Ni-4Cu. UNS S15500
'"
o.. ::¡;
.l<
ui
ui
Ul
~
Ul
~
80
560
40r---~~-----+------r-----4------+----~280
2
4
6 8 Strain, 0.001 in.lin.
10
en
Source: MIL-HDBK-5H, Dec 1998, p 2-169
226/Stainless Steel (SS)
SS.121 15-5 PH stainless steel bar, typical compressive stress-strain and compressive tangent modulus curves at room temperature for various heat treat conditions
Compressive tangent modulus, GPa
200 0.-_ _..,.35_ _ _7,0_ _---,10,5_ _ _1,4_0_ _ _1,75_ _ _2-,1 Q400
H1025 H1025 160 1----==",....;::---+-----11----:.0.....,,==----+----+----1 1120
.¡¡;
120
Test direction: long transverse. Bar thickness = 38.0139.7 mm (1.500-5.500 in.). Ramberg-Osgood parameters: n(H1025) =20, n(H1150) =7.8. Composition: Fe-15Cr-5Ni-4Cu. UNS S15500
840 ro
Source: MIL-HDBK-5H, Dec 1998, p 2-169
a.
-'"
:2
ui !/)
ui"
!/)
~
~
Cií 560
80
401---+--+----+-----1----+----+--~280
2
4
6
o
8
10
12
20
25
30
175
21Q400
Strain, 0.001 in./in.
I O
5
10
15
Compressive tangent modulus, 106 psi
SS.122 15-5 PH H1025 stainless steel bar, typical compressive stress-strain and compressive tangent modulus curves at various temperatures
Compressive tangent modulus, GPa
200
o
35
70
105
140
Test direction: longitudinal. Bar thickness = 38.0142.24 mm (1.500-5.600 in.). 0.5 h exposure. RambergOsgood parameters: n(room temperature) = 22, n(400 °F) = 18, n(700 °F) = 12, n(900 °F) = 11. Composition: Fe15Cr-5Ni-4Cu. UNS S15500
Room temperature
1601---....:::..'""'=:----+---1----:.0--=--+----+-----11120
.¡¡;
840 ro
120
a.
:2
-'"
ui"
ui"
!/)
!/)
i
~
560
80
40~-~~---+----I---+---rr~~~280
Strain, 0.001 in./in.
o
I 5
10
15
20
Compressive tangent modulus, 106 psi
25
30
Cií
Source: MIL-HDBK-5H, Dec 1998, p 2-171
Stainless Steel (SS)/227
SS.123 15-5 PH Hl025 stainless steel plate, typical tensile and compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa 200 or-_ _-r35_ _ _7To_ _ _ 1or5_ _ _1-r4_o_ _ _1T75_ _----,21~400
f---+-=-.....¡.==----::;~
Test direction: L, longitudinal; LT, long transverse. Plate thickness = 38.0-139.7 mm (1.500-5.500 in.). RambergOsgood parameters: n(L, tension) = 23, n(LT, tension) = 23, n(L, compression) = 20, n(LT, compression) = 21. Composition: Pe-15Cr-5Ni-4Cu. UNS S15500
___~::.p..c__--+----11120
Source: MIL-HDBK-5H, Dec 1998, p 2-172
840
.¡¡; -'"
ro
o.. :2
cñ en
cñ en
~
~
Cií 560
Cií
r--~+---+----r_--+---+--_H280
Strain, 0.001 in./in.
o
I 5
10 15 20 25 Compressive tangent modulus, 106 psi
30
Compressive tangent modulus, GPa O 35 70 105 140 175 210 200 , - - - - - - r - - - - - - , - - - - , . - - - - - - r - - - - - - , - - - - - - - , 1400
160 ¡ - - - - + - - - - - + - - - - t - - - + - - - - - + - - - - I 1 1 2 0
.-;~~~~f~e:::;~7~'0~0~OF (371 ;C) _ 900°F (482 OC)
cñ en
~
Cf)
80
40r--.w~---+-----r_--~--++-+~-H280
00
2
L O
4
6 8 Strain, 0.001 in./in.
10
1i
I 5
10 15 20 25 Compressive tangent modulus, 106 psi
Test direction: longitudinal. 0.5 h exposure. RambergOsgood parameters: n(room temperature) = 8.5, n(400 °P) = 14, n(700 °P) = 12, n(900 °P) = 10. Composition: Pe15Cr-5Ni-4Cu. UNS S15500 Source: MIL-HDBK-5H, Dec 1998, p 2-176
Room temperature 120 r----=-----f"~--'-'--'--t'...="-'---'71-""''_:::;;__400 °F (204 ·C) .¡¡; I I -'"
SS.124 15-5 PH H1150 stainless steel bar, typical compressive stress-strain and compressive tangent modulus curves at various temperatures
30
228/Stainless Steel (SS)
SS.125 15-5 PH H935 stainless steel casting, typical tensile and compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa r -_____ 4r2____-,84______1,2_6_____1,6_8_____2,1_o____~25i400
Casting thickness = 12.7-47.625 mm (0.500-1.875 in.). 0.5 h exposure. Ramberg-Osgood parameters: n(tension) = 12, n(compression) = 12. Composition: Fe-15Cr-5Ni4Cu. UNS S15500
r------r----~-=~~~~--~------~----_41120
Source: MIL-HDBK-5H, Dec 1998, p 2-170 840 ro a.
.¡¡; -'"
:2:
'"~
'"~
iñ
560
iñ
~--~~----_4------~----_4----_4H-----_4280
2
o 12
4 Strain, 0.001 in.lin.
I O
6
12
18
30
24
36
6
Compressive tangent modulus, 10 psi
SS.126 15-7 PH RH950 stainless steel sheet, stressstrain curves at room and low temperatures
320 r---------,---------,----------,---------,2240 280
Sheet thickness = 1.626 mm (0.064 in.). Composition: Fe-15Cr-7Ni-2.5Mo. UNS S15700
r---------~--------~~~--_.~~~~~~1960
-320°F (-196 OC)
240
200 .¡¡; -'"
'" ~
r---------~--~_7~~~-------T--------_41400
ro :2:
a. 160
r---------~L,~L---~---------T--------_41120 ~
~
iñ
UJ
120
~------~~~------~---------+--------_4840
80
~--~~~~------~~------~--------_4560
40
~~~----+_--------~---------+--------_4280
0 ~--------~4--------~8----------1L2--------~1~ 0 Strain, 0.001 in.lin.
Source: L.P. Rice, J.E. Campbell, and W.F. Simmons, "The Evaluation of the Effects of Very Low Temperatures on the Properties of Aircraft and Missile Metals," WADD TR 60-254, Feb 1960, p 40. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1503, CINDAS/ USAF CRDA Handbooks Operation, Purdue University, 1995, p 11
5lainless 5leel (55)/229
.¡¡;
200
1400
160
1120
120
840
80
560
-'"
cñ en ~
SS.127 15-7 PH RH950 stainless steel sheet, isochronous stress-strain curves at various temperatures Sheet thickness = 1.27 mm (0.050 in.). Composition: Fe15Cr-7Ni-2.5Mo. UNS S15700
ro c.. :2 cñ en ~
ro
40~~---+--+---4---~--+-~~~~----~--~280
L -_ _ _ _-L______L -_ _ _ _-L______
Strain, 0.001 in./in.
~
____
~
__
~O
ro
Source: "Armco 17-7 PH and PH 15-7Mo," Armco Steel Corp., July 1968, P 37. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1503, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 19
230/Stainless Steel (SS)
240
1680
SS.128 15-7 PH RH950 (a) and TH1050 (b) stainless steel sheet, typical tensile stress-strain curves at room and elevated temperatures
200
1400
Sheet thickness = 1.27 mm (0.050 in.). RT, room temperature. Composition: Fe-15Cr-7Ni-2.5Mo. UNS S15700
160
1120 ro
a.
'00
"'
'"~
:2
840
120
'" ~
iñ
80
560
40
280
2 (a)
4 6 Strain, 0.001 in./in.
8
240
1680
200
1400
160
1120
120
:2 840
ro
a.
'00
"'
'"~
iñ
CIl
80
560
40
280
2 (b)
4 6 Strain, 0.001 in./in.
O
10
Source: Armco Precipitation Hardening Stainless Steel Technical Manual, Arrnco Steel Corp., I March 1958. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1503, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 10
Stainless Steel (SS)/231
300
RT
250
2100
55.129 15-7 PH RH950 (a) and TH1050 (b) stainless steel sheet, typical compressive stress-strain curves at room and elevated temperatures
1750
Sheet thickness = 1.27 mm (0.050 in.). RT, room temperature. Composition: Fe-15Cr-7Ni-2.5Mo. UNS S15700
200
1400
150
1050 gf
'"
a.
~
~
:2
~ 100
700
50
350
Strain, 0.001 in./in.
(a)
300,-----,------,------,-----,------,-----, 2100
250r_----~----_+------r_----~----_+----~
1750
RT 1400
'"
a.
:2
1050 gf
~ 700
350
2 (b)
4
6
Strain, 0.001 in./in.
8
10
Source: "Armco 17-7 PH and PH 15-7Mo," Armco Steel Corp., July 1968, P 29. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1503, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 15
232/Stainless Steel (SS)
SS.130 15-7 PH TH1050 stainless steel sheet, typical tensile stress-strain curves at room and elevated temperatures for various exposure times
200 ¡ - - - - - - - , - - - - - ¡ - - - - - - , , - - - - - - - , - - - - - - ¡ - - - - - , 1400 RT RT
Sheet thiekness = 1.27 mm (0.050 in.). RT, room temperature. Exposure times: (a) 30 min, (b) 10 h, (e) 100 h, and (d) 1000 h. Composition: Fe-15Cr-7Ni2.5Mo. UNS S15700
"-:--+---,4-----11120
840
'"
o.. :2
~ vi
vi
'"
'" ~
~
1ií 560
I__-I-I-+----+-----j
I__~-_+_---+-----j
280
'------'------'------' ' - - - - - ' - - - - - ' - - - - - - ' O 12 O 4 8 12 8 4' Stram, 0.001 in.lin. Strain, 0.001 in.lin: (a) (b)
200
1400
RT
RT
.'d~"------l
1120
I-----thr---+-+-----i I__----+l--I---+-----j 840
~
~ ~ 1ií
~'"
~ ~
80
I__--Ihf+--~""'--+-----j
I__---H+--:J-""'-_+-----j 560 1000 °F (538 OC)
1__~-+-----+-------j1__~--_+_----_+---~280
L---~4---~8---1~2 ~0---~4---~8------'1P
Strain, 0.001 in.lin.
Strain, 0.001 in.lin. (e)
(d)
1ií
Source: M.M. Lemcoe and A. Trevino, Jr., "Determination of the Effect of Elevated Temperature Materials Properties of Several High Temperature Alloys," ASD TDR-61-529, June 1962, p 194-197. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1503, CINDAS/ USAF CROA Handbooks Operation, Purdue University, 1995, p 11
5tainless 5teel (55)/233
55.131 15-7 PH TH1050 stainless steel sheet, typical tensile stress-strain curves at room and elevated temperatures
1750
250
Room temperature
.¡¡;
200
1400
150
1050
Test direction: longitudinal. 0.5 h exposure. RambergOsgood parameters: n(room temperature) = 8.3, n(200 °P) = 6.6, n(400 °P) = 7.5, n(600 °P) = 5.5, n(800 °P) = 4.7, n(lOOO °P) = 6.6. Composition: Pe15Cr-7Ni-2.5Mo. UNS Sl5700
'"
a.
-'"
:2
Source: MIL-HDBK-5H, Dec 1998, p 2-181
en
en
~
100
700
1000 °F (538 OC)
~
50~--~~~--~-----+----~------~----4350
L-----~----~-----L----~------~--~O
2
4
6
8
10
12
Strain, 0.001 in.lin.
55.132 15-7 PH TH1050 stainless steel sheet, typical compressive stress-strain curves at room and elevaled temperatures
250.-----,-----,------,-----,------,-----.1750 Room temperature
0.5 h exposure. Ramberg-Osgood parameters: n(room temperature) = 9.3, n(200 °P) = 10, n(400 °P) = 11, n(600 °P) = 14, n(800 °P) = 12, n(1000 °P) = 6.3. Composition: Pe-15Cr-7Ni-2.5Mo. UNS S15700
~----+-----~-----+--~~~~~~--__41400
1050
.¡¡;
ro
a.
-'"
:2
en
en
~
~
700
r_--~~----~-----+----~------r_--~350
L-----~----~-----L----~
2
4
______
6 8 Strain, 0.001 in.lin.
~
10
__
~O
12
i'ií
Source: MIL-HDBK-5H, Dec 1998, p 2-181
234/5tainless 5teel (SS)
SS.133 15-7 PH TH1050 stainless steel sheet, typical compressive tangent modulus curves at room and elevated temperatures
Compressive tangent modulus, GPa 35 70 105 140 175 o 25or-----,------r-----,------,------r-----.
0.5 h exposure. Ramberg-Osgood parameters: n(room temperature) = 9.3, n(200 °F) = 10, n(400 °F) = 11, n(600 °F) = 14, n(800 °F) = 12,.n(lOOO °F) = 6.3. Composition: Fe-15Cr-7Ni-2.5Mo. UNS S15700 Source: MIL-HDBK-5H, Dec 1998, p 2-182 .¡¡;
150
..lo<
vi VI
$ 100 ~----1_----_+-----=~----~----~~~rlH700
50~----1_----_+------~----~--_r_+r-+_HH350
°0L-----~5------1~0------1~5----~20----~2~5L-~~3~
Compressive tangent modulus, 106 psi
/' ----
180 160
/ /
120
V V
~ ~ 100
L / /
~
80
o
/'
/ / L
60
20
V-/
/
140
40
SS.134 17-4 PH stainless steel bar, stress-strain curves for various heat treat conditions
1400
200
V
/
V
/
/ / / / V /
/
H900
i--
1260
-
980
~-
840
'"
[L
::2;
700 560 420
140
r- 2-4
Source: W.J. Lanning, "Torsion Properties of 17-4PH and 15-5PH Stainless Steel Bars," Advanced Materials Div., Arrnco Steel Corp., 16 March 1972. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1501, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 7
1120
280
Strain, 0.001 in./in.
Composition: Fe-17Cr-4Ni-4Cu. UNS S17400
H1050
o
vi VI
~
5tainless 5teel (55)/235
SS.135 17-4 PH stainless steel bar, typical stressstrain curves for various heat treat conditions
1400
200
Test direction: longitudinal. Bar thickness = 25.4-114.3 mm (1.000-4.500 in.). Ramberg-Osgood parameters: n(H900) = 11, n(H1025) = 24, n(HI150) = 13. Composition: Fe-17Cr-4Ni-4Cu. UNS S17400
1120
160
Source: MIL-HDBK-5H, Dec 1998, p 2-202
840
120
'"
'00 -'"
o.. :2
'"~
'" ~
é'i5
560
80
40~--~~----~----~------+-----~----~280
Strain, 0.001 in.lin.
SS.136 17-4 PH stainless steel bar, typical compressive stress-strain and compressive tangent modulus curves at room temperature for various heat treat conditions
Compressive tangent modulus, GPa
2ooor-----~35~--~7TO----~10~5----~1T40~--~17r5----~21~400
H1025
Test direction: longitudinal. Bar thickness: 25.4-114.3 mm (1.000-4.500 in.). Ramberg-Osgood parameters: n(H1025) = 22, n(H1150) = 13. Composition: Fe-17Cr4Ni-4Cu. UNS S17400
H1025
840 '00 -'"
Source: MIL-HDBK-5H, Dec 1998, p 2-202
'"
o.. :2
'"~
In
~
é'i5
560
~--~4------+----~------+-----~-----4280
2
4
6
8
10
20
25
Strain, 0.001 in.lin.
I o
5
I 10
15
Compressive tangent modulus, 106 psi
30
é'i5
236/Stainless Steel (SS)
SS.137 17-4 PH H900 stainless steel bar, typical tensile stress-strain curves at room and elevated temperatures
2oo,------,------,------,------,------,----__,14oo
1225
175~----_r------~----_r--~=-r_--
Test direction: longitudinal. Composition: Fe-17Cr-4Ni4Cu. UNS S 17400 125~----~------~L,~~------r_----_r----~875
11
900°F (482 OC)
'"
~
~ 100~----_r----~~~~_r------r_----_r----_4700 ~
~ w
Source: O.L. Deel and H. Mindlin, "Engineering Data on New Aerospace Structural Materials," AFML-TR-72-196, Vol 1, Battelle Columbus Laboratories, Sept 1972. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1501, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 11
~ w
75~----_r-T.~~~----_r------r_----_r----_4525
50~--~Mf,~----~----~------r_----_r----~350
25~~~-r------~-----r------r------r-----4175
°0L------2L------4L------6L------8~----~1~0----~1f
Strain, 0.001 in./in.
200
r------r------r------r------,-~---,----__,1400
175 f--~~t__~-.J__--+_----c~~::::::===t_--_11225
SS.138 17-4 PH H900 stainless steel bar, compressive stress-strain curves at room and elevated temperatures Composition: Fe-17Cr-4Ni-4Cu. UNS S17400 Source: O.L. Deel and H. Mindlin, "Engineering Data on New Aerospace Structural Materials," AFML-TR-72-196, Vol 1, Battelle Columbus Laboratories, Sept 1972. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1501, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 16
150
125 .¡¡¡
""gi 100 ~
(f)
75
50
~--~~------~----~------r_----_r----~350
25 ~~~~------~----_r------r_----_r----~175 O~-----L------4L------6L------8L-----~1LO----~1l 2 O Strain, 0.001 in./in.
5tainless 5teel (55)/237
200
1400
160
1120
/
120 ·00 -"
rñ
Il)
~
(J)
80
40
~
/
/
/
55.139 17-4 PH H 1000 stainless steel casting, typical tensile stress-strain curve at room temperature Casting thickness =9.525-76.2 mm (0.375-3.000 in.). Ramberg-Osgood parameter: n = 16. Composition: Fe17Cr-4Ni-4Cu. UNS S17400 Source: MIL-HDBK-5H, Dec 1998, p 2-203
840
&.
::¡¡;
/
~
e:! 560
é'ií
280
4
2
8
6
10
Strain, 0.001 in.lin.
200
o
35
"-..
160
~
120 ·00 -"
rñ
Il)
~
é'ií
80
40
Compressive tangent modulus, GPa 70 105 140
/
/
//
~
v
55.140 17-4 PH H1000 stainless steel casting, typical compressive stress-strain and compressive tangent modulus curves at room temperature
175
---
1120
r--- ~
Source: MIL-HDBK-5H, Dec 1998, p 2-203
.......
\
840
~
560
4
6
o
8
10
12
20
25
30
Strain, 0.001 in.lin.
o
I 5
10
15
Compressive tangent modulus, 106 psi
en o.. ::¡¡;
e:!
280
2
Casting thickness = 9.525-76.2 mm (0.375-3.000 in.). Ramberg-Osgood parameter: n = 13. Composition: Fe17Cr-4Ni-4Cu. UNS S17400
é'ií
238/5tainless 5teel (SS)
320 I
280
.J
-423
240
"'rñ"
i'"
- r--
--
....V-
160
1960
Composition: Fe-17Cr-4Ni-4Cu. UNS S17400
"""" -100·F (-73 ·C)
75·F (24 ·C)
~
:2 1120 gf
!'-
~ 840
80
560
40
280
0.12
0.08
0.04
0
books Operation, Purdue University, 1995, p 11
1400
.............
120
0
Souree: K.A. Warren and R.P. Reed, Tensile and Impact Properties of Selected Materials from 20 to 300 K, Monograph 63, National Bureau of Standards, 28 June 1963. As published in Aerospace Structural Metals Handbook, Vo12, Code 1501, CINDAS/USAF CRDA Hand-
1680
....... ,,320·F (-196 ·C)
'0;
SS.141 17-4 PH H1100 stainless steel bar, complete stress-strain curves at room and low temperatures
(-253 ·C)
I
200
2240
o
0.16
0.20
Strain, in.lin.
)/
280
240
/
'¡jj
'" ~
V
/
..".~-.-
. ., . .,,''''''''
120
/.
80
¿I.
V~
1400
'" :2 1120 gf ~
Iií 840
/
1
280
~--
4
8 6 Strain, 0.001 in.lin.
Curve 1,5.08 mm (0.200 in.) diam, condition A; curve 2, 2.032 mm (0.080 in.) diam, condition C; curve 3, 2.032 mm (0.080 in.) diam, condition CH900. Composition: Fe17Cr-7Ni-1Al. UNS Sl7700
1680
560
/
2
1960
a.
/
160
40
/
V/ /;'
200
"'rñ"
SS.142 17-7 PH stainless steel spring wire, tensile stress-strain curves at room temperature for various heat treat conditions
2240
320
10
Souree: "Armeo 17-7 PH Preeipitation-Hardening Stainless Steel, Bar, Rod and Wire," Bulletin No. S-2ge, Armeo Stainless Steel Div., April 1983. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1502, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 16
Stainless Steel (SS)/239
J/
l'
240
j ~-
200
.¡¡; 160
!en 120 80
/
/
/
P
I
,;;;;
11
- - - Longitudinal - - Tr¡nSverse
4
8
12
/ V (b)
/
t
200
.¡¡; 160
I
"'"
280
4
8
o
12
Strain, 0.001 in.lin.
h
/'*
¡~ /
r/
/'
55.144 17-7 PH stainless steel sheet, typical compressive stress-strain curves for heat treat condition RH950 (a) and TH1050 (b)
120
/
1/
- - - Longitudinal - - Tr¡nSverse
4
8
Strain, 0.001 in.lin.
12
560
280
/ O
4 (b)
Test direction: longitudinal and transverse. Sheet thickness = 1.27 mm (0.050 in.). Tested at room temperature. Composition: Fe-17Cr-7Ni-1Al. UNS S 17700
1400
840
I /
/
1680
1120 ti. ::2
1/
f¡
40
N
1960
240
80
1120 ti. ::2
Source: ''Armco 17-7 H and PH 15-7Mo," Armco Steel Corp., 1966. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1502, CINDAS/USAF CROA Handbooks Operation, Purdue University, 1995, p 16
560
280
en
1400
Test direction: longitudinal and transverse. Sheet thickness = 1.27 mm (0.050 in.). Composition: Fe-17Cr7Ni-IAl. UNS SI7700
840
/
O
Strain, 0.001 in.lin.
!
1680
I ---
{'
"'ui"
40
55.143 17-7 PH stainless steel sheet, typical tensile stress-strain curves for heat treat condition RH950 (a) and TH1050 (b)
1960
280
8
Strain, 0.001 in.lin.
o
12
N
Source: "Armco 17-7 H and PH 15-7Mo," Armco Steel Corp., 1966. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1502, CINOAS/USAF CROA Handbooks Operation, Purdue University, 1995, p 18
240/5tainless 5teel (SS)
320 Room JmperatuJ
280
I 1// IV
200 .¡¡; -'"
vi
~
1960
/V
240
In
SS.145 17-7 PH CH900 stainless steel sheet, tensile stress-strain curves at room and elevated temperatures under conditions of rapid heating, rapid loading, and short time at temperature
2240
160
120
_
800 'F (427 'C)
o
~
O
4
'"
o.. :2
1120 gf "al
~
840
1/ --
40
1400
1000 'F (538 'C)
PI
80
Sheet thickness = 1.016 mm (0.040 in.). Strain rate = O.l/s. Heated to test temperature in 10 s and held for 10 s prior to test. Composition: Fe-17Cr-7Ni-1Al. UNS S 17700
1680
1200 'F (649 'C)
Souree: J.R. Kattus, "Tensile and Creep Ruptnre Properties of Struetural Alloys under Conditions of Rapid Heating, Rapid Loading, and Short Times at Temperatnre," Southern Researeh Institute Report 3962-867-2-1 to International Niekel Co., 10 April 1959. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1502, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 19
560
280
8
12
16
20
24
Strain, in.lin.
SS.146 17-7 PH RH950 stainless steel sheet, tensile stress-strain curves at various temperatures
24or-------~-------.------_,------_,------__,1680
Sheet thickness = 1.27 mm (0.050 in.). Curve 1: room temperature; curve 2: 93 oC (200°F); curve 3: 204 oC (400 °F); curve 4: 316 oC (600°F); curve 5: 427 oC (800 °F); curve 6: 482 oC (900°F); curve 7: 538 oC (1000 °F). Composition: Fe-17Cr-7Ni-1Al. UNS Sl7700
~------+_------~-------+------_4--~~~1400
'"
o.. :2
840 vi
~
üí
~--~.~~------+_------4_------_r--------280
Strain, 0.001 in.lin.
Souree: Armco Precipitation Hardening Stainless Steels Technical Data Manual, Armeo Steel Corp., I Nov 1957. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1502, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 19
5tainless 5teel (55)/241
240 , - - - - , - - - - , . - - - - - , - - - - , - - - - - , 1680
SS.147 17-7 PH RH950 stainless steel sheet, compressive stress-strain curves at room and elevated temperatures
200 ~------~----~-4---~~~~~----~----~1400 600°F (316 OC)
Test direction: longitudinal. Sheet thickness = 1.575 mm (0.062 in.). Composition: Fe-17Cr-7Ni-lAl. UNS S 17700
160 ~------~-f-----4----.~_4------~~----~1120 .¡¡; -'" ui
'"
~
'"
120 ~------~-------4-+-----_4~------~----~840
Cií
o.. :2 ui
~
Cií 80
40
~~----+_~L---~--+---_4--~----~----~280
L-----~L_
_____
~~
_____ L_ _ _ _ _ __ L_ _ _ _
Strain, 0.001 in.lin.
~O
Source: J.R. Kattus, lB. Preston, and H.L. Lessley, "Determination of Tensile, Compressive, Bearing, and Shear Properties of Sheet Steels at Elevated Temperatures," WADC Technical Report 58-365, Nov 1958. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1502, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 24
242/Stainless Steel (SS)
55.148 17-7 PH RH950 stainless steel sheet, isochronous stress-strain curves
1400
200
160
1120
Sheet thiekness = 1.27 mm (0.050 in.). (a) 316 oC (600 °P). (b) 427 oC (800 °P). (e) 371 oC (700 °P). (d) 482 oC (900 °P). Composition: Pe-17Cr-7Ni-lAl. UNS Sl7700
840
Source: Armco Precipitation Hardening Stainless Steels Technical Data Manual, Arrnco Steel Corp., 1 Nov 1957. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1502, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 30
1000 h .¡¡;
120
'"
Q. ~
-'" vi
vi
"'~
li5
560
80
jg"' en
°oL-----~4------~8------1~20L-----~4------~8---"0
(a)
Strain, 0.001 in.lin.
(b)
Strain, 0.001 in.lin.
120.-------....-.,-,----,-,,-------, .----------r------,----,840
.¡¡;
80
560
'"
Q. ~
-'" vi
vi
"'~
li5
40
280
o 0L-----~4------~8----~1::'2 0L------.1.--------L----' O 4 8 (e) Strain, 0.001 in.lin. (d) Strain, 0.001 in.lin.
jg"' en
5tainless 5teel (55)/243
200
.¡¡;
SS.149 17-7 PH TH1050 stainless steel sheet, typical tensile stress-strain curves at room and elevated temperatures
1750
250
0.5 h exposure. Ramberg-Osgood parameters n(room temperature) = 12, n(200 °F) = 8.3, n(400 °F) = 9.0, n(600 °F)= 12, n(800 °F) = 8.3, n(900 °F) = 8.0, n(lOOO °F) = 7.7. Composition: Fe-17Cr-7Ni-1Al. UNS S 17700
1400
Room temperature
150 800 [' (427 ·C)
"".;
Source: MIL-HDBK-5H, Dec 1998, p 2-212 .;
~
iñ
900°F (482 OC)
100
700
~
1000 °F (538 OC) 350
50
~----~2------4L------~6----~8------1~0----~1f
Strain, 0.001 in.lin.
250
SS.150 17-7 PH TH1050 stainless steel sheet, typical compressive stress-strain curves at room and elevated temperatures
1750 Room temperature
0.5 h exposure. Ramberg-Osgood parameters: n(room temperature) = 9.3, n(200 °F) = 11, n(400 °F) = 9.3, n(600 °F) = 11, n(800 °F) = 8.3, n(900 °F) = 9.3. Composition: Fe-17Cr-7Ni-1Al. UNS S 17700
200
150
1050 al
~
D..
::;
.;
.;
~
iñ 100
700
~----~------r-----r-----+----~350
2
4
6
Strain, 0.001 ¡n.lin.
8
10
~
Source: MIL-HDBK-5H, Dec 1998, p 2-212
244/Stainless Steel (SS)
250 or-_ _--¡35_ _ _7To_ _ _1,o5_ _--,14_o_ _ _1,.7.:..5_ _-=,21~750
SS.151 17-7 PH TH1050 stainless steel sheet, typical compressive tangent modulus curves at room and elevated temperatures
200 1----.<::-+--'-~....,¡,~:...:-.~+-'::--c:=-~+--_+-----l1400
0.5 h exposure. Ramberg-Osgood parameters: n(room temperature) =9.3, n(200 °P) = 11, n(400 °P) =9.3, n(600 °P) = 11, n(800 °P) = 8.3, n(900 °P) =9.3. Composition: Pe-17Cr-7Ni-lAl. UNS S 17700
Compressive tangent modulus, GPa
Source: MIL-HDBK-5H, Dec 1998, p 2-213 .¡¡;
1050
150
c..'"
::¡;
"""
ui
rn ~
rn
Cií 700
100
~
501---~---+---~--~--+~-~~350
°0L---~5----~10-----1L5---~2~0-~~25--L-LJJ3~ 6
Compressive tangent modulus, 10 psi
280 .-------,-------,-------,------,--------, 1960
1_---~1_---1----1----~~--41680
1400
801-----1--
401---~
~--_4---_4---~---~280
2
6 4 Strain, 0.001 in.lin.
8
SS.152 17-7 PH TH1050 stainless steel sheet, tensile stress-strain curves at various temperatures RT, room temperature. Sheet thickness = 2.032 mm (0.080 in.) for low temperatures (below RT), 1.27 mm (0.050 in.) for RT and above. Curve 1: -253 oC (-423 °P); curve 2: -196 oC (-320 °P); curve 3: -79 oC (-110 °P); curve 4: RT; curve 5: 93 oC (200 °P); curve 6: 204 oC (400 °P); curve 7: 316 oC (600 °P); curve 8: 427 oC (800 °P); curve 9: 482 oC (900 °P); curve 10: 538 oC (1000 °P). Composition: Pe-17Cr-7Ni-lAl. UNS S 17700 Source: Armco Precipitation Hardening Stainless Steels Technical Data Manual, Arroco Steel Carp., 1 Nov 1957 andA.L. McGee, J.E. Campbell, R.L. Carlson, and G.K. Manning, "The Mechanical Properties of Certain Aircraft StructuraJ Metals at Very Low Temperatures," WADC TR 58-386, Nov 1958. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1502, CINDASIUSAF CRDA Handbaaks Operation, Purdue University, 1995, p 19
5tainless 5teel (55)/245
I~
180 160
Room
1120
SS.153 17-7 PH TH1050 stainless steel sheet, tensile stress-strain curves at room and elevated temperatures
980
Strain rate 0.0002/s. Composition: Fe-17Cr-7Ni-lAl. UNS Sl7700
1260
t~mperatulre
500°F (260 OC)
¡...-
140
/V 1/
120 .¡¡; -'" 100 ui
--
'1
'"
i
840
80
1000 °F (538 OC)
V
60
420 280
20
1500 °F (816 ° C ) _ 140
y--
2000
5
10
180 160
/
140
'1 1/ /
~ 100
.; 80 60
15
20 25 Strain, in.lin.
-
V __¡---
o~ (1093 ,b¡ 30
35
500 °F
(~60 ° C ) -
1120
Strain rate 0.002/s. Composition: Fe-17Cr-7Ni-lAl. UNS S 17700
980 840 1000 'F (538 'C)
V--
'"
700 ~
g¡ 560 (/) ~
'/
420
40
280 1500 'F (816 OC)
20
SS.154 17-7 PH TH1050 stainless steel sheet, tensile stress-strain curves at room and elevated temperatures
1260 Room temperature
(/V
120
'"
560 (/) ~
40
O O
~
'" m
700 ~
V
2000 °F
h093 'C)
~
8
16 24 Strain, 0.001 in.lin.
Source: A.c. Wilhelm and J.R. Kattus, "Determination of tbe Mechanical Properties of Aircraft Structural Materials at Very High Temperatures after Rapid Heating," Part 3, ''The Effects of Simultaneous Heating and Loading on tbe Tensile Properties of Typical Structural Alloys," WADC TR 57-647, Part 3, Nov 1960. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1502, ClNDAS/ USAF CRDA Handbooks Operation, Purdue University, 1995, p 20
32
140
Source: A.C. Wilhelm and J.R. Kattus, "Determination of tbe Mechanical Properties of Aircraft Structural Materials at Very High Temperatures after Rapid Heating," Part 3, "The Effects of Simultaneous Heating and Loading on tbe Tensile Properties of Typical Structural Alloys," WADC TR 57-647, Part 3, Nov 1960. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1502, ClNDAS/ USAF CRDA Handbooks Operation, Purdue University, 1995, p 20
246/Stainless Steel (SS)
. / 1-"""
//
140
f
100
r¡
80 60 40 20
500 'F (260 'C)
l/
120
~
980
Strain rate 0.02/s. Composition: Fe-17Cr-7Ni-1Al. UNS S 17700
Room temperature
160
.¡¡; .:.: ui !/)
1120
SS.155 17-7 PH TH1050 stainless steel sheet, tensile stress-strain curves at room and elevated temperatures
1260
180
-
/'""'
/
840 ,"-1000 'F (538 'C)
:i
560 jg
m
/
I I
~
'"
700 ~
Source: A.C. Wilhelm and J.R. Kattus, "Determination of the Mechanical Properties of Aircraft Structural Materials at Very High Temperatures after Rapid Heating," Part 3, "The Effects of Simultaneous Heating and Loading on the Tensile Properties of Typical Structural Alloys," WADC TR 57-647, Part 3, Nov 1960. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1502, CINDAS! USAF CRDA Handbooks Operation, Purdue University, 1995, p 21
420
1500 'F (816 'C)
...-
2000 'F (1093 'c) 5
10
15
20
25
30
280 140
35
Strain, in./in.
180
1260
160
1120
140
980
120
840
Specimens simultaneously loaded at strain rate of 0.0002/s and heated at rate shown. Composition: Fe17Cr-7Ni-1Al. UNS Sl7700
'"
700 ~
~ 100 ui !/)
¡
SS.156 17-7 PH TH1050 stainless steel sheet, tensile stress-strain curves with effect of various heating rates
ui !/)
80
560 jg
60
420
40
280
20
140
O O
m
5
10
15
20 Strain, in./in.
25
30
35
O
40
Source: A.C. Wilhelm and J.R. Kattus, "Determination of the Mechanical Properties of Aircraft Structural Materials at Very High Temperatures after Rapid Heating," Part 3, ''The Effects of Simultaneous Heating and Loading on the Tensile Properties of Typical Structural Alloys," WADC TR 57-647, Part 3, Nov 1960. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1502, CINDAS! USAF CRDA Handbooks Operation, Purdue University, 1995, p 21
Stainless Steel (SS)/247
180 Heating1rate,
160
.......... 840
g¡
lO
~ 100
700
I I
ui
'"~
Specimens simultaneously loaded at strain rate of 0.002/s and heated at rate shown. Composition: Fe-17Cr-7NiIAl. UNS SI7700
980
(
120
Cií
1120
20 (11)
140
SS.157 17-7 PH TH1050 stainless steel sheet, tensile stress-strain curves with effect of various heating rates
1260
°F/~ (OC/s)
80
ui
560 (J) ~'"
60
420
\
40
Source: A.e. Wilhelm and J.R. Kattus, "Determination of the Mechanical Properties of Aircraft Structural Materials at Very High Temperatures after Rapid Heating," Part 3, "The Effects of Simultaneous Heating and Loading on the Tensi1e Properties of Typical Structural Alloys," WADC TR 57-647, Part 3, Nov 1960. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1502, CINDAS/ USAF CRDA Handbooks Operation, Purdue University, 1995, p 22
I
20 00
5
10
15
20
25
30
35
0 40
Strain, in./in.
160,----,----,----r----,----r----,----r----,1120 Heating rate, °F/s (OC/s) ~--~----~---+----+---_+----+---_+--~980
1-+---"""'"1840
~~~----~--_+----+---~~--~~~--~420
~--_+----~~~~---_+----+_--~L---~--~140
20 Strain, in./in.
25
SS.158 17-7 PH TH1050 stainless steel sheet, tensile stress-strain curves with effect of various heating rates Specimens simultaneously loaded at strain rate of 0.02/s and heated at rate shown. Composition: Fe-17Cr-7NiIAl. UNS SI7700 Source: A.C. Wilhelm and J.R. Kattus, "Determination of the Mechanical Properties of Aircraft Structural Materials at Very High Temperatures after Rapid Heating;' Part 3, "The Effects of Simultaneous Heating and Loading on the Tensile Properties of Typical Structural Alloys," WADC TR 57-647, Part 3, Nov 1960. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1502, CINDAS/ USAF CRDA Handbooks Operation, Purdue University, 1995, p 22
248/Stainless Steel (SS)
240 ,..---,----,..-----r---,------¡----r----,168o
°F (24 °C)+---~---l1400 200 QF (~3 OC) 400°F (204 OC) 600 'oF (316 OC) 1120 160 ~-~-_+___j,r-----i'___t_--,V"""'_t___"_::____1'_700 °F (371°C)
200
~--+----+----+--75
Compressive yield strength ' "
I
800°F (427 OC)
~ ui IJ)
~
120
rn
80
Strain, 0.001 in./in.
SS.159 17-7 PH TH1050 stainless steel sheet, compressive stress-strain curves at room and elevated temperatures Test direction: longitudinal. Sheet thickness = 1.27 mm (0.050 in.). Specimens loaded at strain rate of 0.002/rnin. Composition: Fe-17Cr-7Ni-lAl. UNS S 17700 Saurce: B.A. Stein, "Campressive Stress-strain curves Praperties af 17-7 PH and AM 350 Stainless-Steel Sheet at Elevated Temperatures," NACA TN 4074, 19 Aug 1957. As published in Aerospace Structural Metals Handbook, Val 2, Cade 1502, CINDAS/USAF CROA Handbooks Operation, Purdue University, 1995, p 24
5tainless 5teel (55)/249
SS.160 17-7 PH TH1050 stainless steel sheet, isochronous stress-strain curves
, . - - - - - . - - - - - - - , - - - - , r - - - - - . - - - - - - , - - - - , 1120
Sheet thickness = 1.27 mm (0.050 in.). (a) 316 oC (600 °P). (b) 427 oC (800°F). (e) 371°C (700°F). (d) 538 oC (1000 °P). Composition: Pe-17Cr-7Ni-lAl. UNS SI7700
tIl
D..
1___-~ru-1I___--___\-___\ I___--+h~--f-'-"'~
560
::a: gf
~ 1---1----f------\----1 f---H'-------j-----+----1 280
' - -_ _----'_ _ _---1 _ _- ' L _ _ _--'-_ _ _-'-----"
4 8 Strain, 0.001 in.lin.
O (b)
O
4 8 Strain, 0.001 in.lin.
120,------,------¡----, r - - - - , - - - - - . - - - - , 840
560 .¡¡;
tIl
D..
.><
cñ
::a:
~
'" ~ en
cñ
'"
280
'--_ _----'L-_ _----'._---'
4 s: Strain, 0.001 in.lin.
L -_ _ _- ' -_ _ _-'-_...J
O (d)
4 8 Strain, 0.001 in.lin.
O
Source: Annco Precipitation Hardening Stainless Steels Technical Data Manual, Annco Steel Corp., 1 Nov 1957. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1502, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 31
250/Stainless Steel (SS)
SS.161 AM-350 annealed stainless steel sheet, tensile and compressive stress-strain curves at room and elevated temperatures
8o,-------,-------,-------,-------,-------,56o
Test direction: longitudinal. Sheet thickness = 1.626 mm (0.064 in.). Solid curves, tension; dashed curves, compression. Composition: Fe-17Cr-4Ni-3Mo. UNS S35000
.... 80 'F (27 'C) 60~----~*-----~+_~----+-------~------~420
:g¡
400 'F (204 'C)
gf 40 ~-rI-----_t_:#"--_____:;¡._tE...--600 'F (316 'C)---+-------l280 f!!
800 "F (427 'C) 1000 'F (538 'C) 1200 'F (649 'C)
Ci5
~ ui
_~
Source: R.O. Henníng and A.W. Brisbane, "MechanícaI Propertíes of AM-350 Potomac A, Potomac M and Vascojet 1000 Steel Alloys ín the Annealed Condítion," ASD-TDR-63-116, May 1963. As pubJíshed in Aerospace Structural Metals Handbook, Vol 2, Code 1504, CINDASI USAF CRDA Handbooks Operatíon, Purdue University, 1995, p 11
(J)
20~-~~+-+--~~~--~----+----~140
Strain x 0.001
SS.162 AM-350 double aged stainless steel sheet, compressive stress-strain curves at room and elevated temperatures
200,-------,-------,-------,-------,-------,1400 Room temperature
400 'F (204 'C) 600 'F (316 ~C)
Sheet thickness = 1.626 mm (0.064 in.). Composition: Fe-17Cr-4Ni-3Mo. UNS S35000
160 ~------+_------+-----~+--~-\-t.....,~~..., 1120
840
120 '00
a.'"
:2
-'" ui
ui (1)
'" ~
560
80
40~---A~~------+-------1--------r------~280
°0~------~2------~4------~6------~8~----~1~
Strain, 0.001 in.lin.
~
Source: "Room and Elevated Temperature Tensíle and Compressive Properties of Type AM-350," Data sheet 86-11457-350, Allegheny Ludlum Steel Corp., 1958. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1504, CINDASIUSAF CRDA Handbooks Operatíon, Purdue University, 1995, p 14
Stainless Steel (SS)/251
SS.163 AM-350 double aged stainless steel sheet, tensile stress-strain curves at room and elevated temperatures
2oor-------~------~------,_------_.~----_,1400
ROOm temperature
Sheet thickness = 1.626 mm (0.064 in.). Composition: Pe-17Cr-4Ni-3Mo. UNS S35000
1601-------+-------+---------'---+------'---\---:;;;74-------::::J 1120
840
120
'"
~
o. ::!:
rñ Ul
Source: "Room and Elevated Temperature Tensile and Compressive Properties of Type AM-350;' Data sheet 86-11457-350, Allegheny Ludlum Steel Corp., 1958. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1504, CINDASIUSAF CROA Handbooks Operation, Purdue University, 1995, p 11
rñ
Ul
~
~
Ci5
560
80
40~--_7.~}_-------~------~------~------~280
°0L-·------2L-------4~----~6------~8------~1~
Strain,
0.001 inJin.
240
200
80 'F (27 'C)
1680
SS.164 AM-350 20% CRT stainless steel sheet, tensile stress-strain curves at room and various temperatures
1400
CRT: annealed to condition H, cold roUed 20%, 3 h, tempered 441°C (825 °P), 3 h. Composition: Pe-17Cr4Ni-3Mo. UNS S35000
I
650 'F (343 'C)
160
1120
.¡¡; -'"
Source: Aerospace Structural Metals Handbook, Vol 2, Code 1504, CINDASIUSAF CROA Handbooks Operation, Purdue University,
'"
o. ::!:
rñ 120
840 Ulrñ
Ul
~
~
Ci5
Ci5
80
560
40
280
0
0
0.04
0.08 Strain, %
0.12
o 0.16
1995, P 12
252/Stainless Steel (SS)
1680
SS.165 AM-350 30% CRT stainless steel sheet, tensile stress-strain curves at room and various temperatures
200
1400
CRT: annealed to condition H, cold roUed 30%, 3 h, tempered 441°C (825°F), 3 h. Composition: Fe-17Cr4Ni-3Mo. UNS S35OO0
160
1120
Source: Aerospace Structural Metals Handbook, Vol 2, Code 1504, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, P 12
240 -110°F (-79 OC) 80°F (27 OC)
'"
a.
'00
.l<
:2 840 ui
gf 120
'"~
~
éñ
éñ 80
560
40
280
o o
0.04
0.08 Strain, %
0.12
o
0.16
SS.166 AM-350 SCT850 stainless steel sheet, tensile stress-strain curves at room and elevated temperatures
200,-------,-------,-------,-------,-------,1400
160~------+-------+-------~~~·
1120
120
840
Sheet thickness = 1.067 mm (0.042 in.). SCT, subcooled and tempered. Composition: Fe-17Cr-4Ni-3Mo. UNS S35000
'"
Il.
~ ui
:2 ui
éñ
rn
'"~
'"
~
560
80
40~--~~+_------+_------~------~------~280
Strain, 0.001 in.lin.
Source: "Room and Elevated Temperature Tensile and Compressive Properties ofType AM-350," Data sheet 86-11457-350, Allegheny Ludlum Steel Corp., 1958. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1504, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 11
5tainless 5teel (55)/253
SS.167 AM-350 SCT850 stainless steel sheet, typical tensile stress-strain curves at room and elevated temperatures
250 ~----'-----r---'-----'-----r----, 1750
0.5 h exposure. SCT, subcooled and tempered. RambergOsgood parameters: n(room temperature) = 10, n(400°F) = 7.0, n(600 °F) = 7.5, n(800 °F) = 6.5. Composition: Fe17Cr-4Ni-3Mo. UNS S35000
2oo1------+----+---+-----+----+-----1 1400
1------+----+--~r--~~=---+~-~1050
al
Source: MIL-HDBK-5H, Dec 1998, p 2-122
o..
:;: .,; IJ)
~
1------+--~~~~-+-----+----+-----1700
ro
r---.~---+----+-----+----+-----1350
~---L
__
~
_ _ _L -_ __ L_ _
~
__
~O
2
12 Strain, 0.001 inJin.
SS.168 AM-350 SCT850 stainless steel sheet, typical compressive stress-strain and compressive tangent modulus curves at room and elevated temperatures
Compressive tangent modulus, GPa
05=----_-..;.,14;..:0_ _ _1:..;.7.::..5_ _.=,21~ 750 250 0r----.--..:;3.::..5_ _ _7.:.,:0=----.__---.:.1-r:
0.5 h exposure. SCT, subcooled and tempered. RambergOsgood parameters: n(room temperature) = 9.3, n(400 °F) = 6.2, n(600 °F) = 6.8, n(800 °F) = 6.2. Composition: Fe-17Cr-4Ni-3Mo. UNS S35000
Room temperature
200 I---.:...:.=.:..r~::.==-=r----+_---,---+--=_----r-'--------l 1400
Source: MIL-HDBK-5H, Dec 1998, p 2-122 150
~
.,;
.,;
IJ)
~
IJ)
100
700
50r--~~---+---r---~---+~-+_1350
2
4
6
8
10
O 12
20
25
30
Strain, 0.001 inJin.
L
I
O
5
I 10
15
Compressive tangent modulus, 106 psi
~
254/Stainless Steel (SS)
55.169 AM-350 5CT850 stainless steel sheet, tensile stress-strain curves at room and low temperatures
280 ,--------,-------,-------,-------,-------,196o
240
Sheet thickness = 1.626 mm (0.064 in.). SCT850: annealed to condition L, subcooled -73 oC (-100 °P), 3 h, tempered 441-468 oC (825-875 °P), 3 h. Composition: Pe-17Cr-4Ni-3Mo. UNS S35000
~------~------~------~----~r-----~1680
200
.¡¡;
160
1120~
120
840
'" ~
80
560
40
280
::;:
"'
(J)
00
2
4
6
8
Source: R.L. McOee, J.E. Campbell, R.L. Carlson, and O.K. Manning, "The Mechanical Properties of Certain Structural Metals at Very Low Temperature," WADC-TR 58-386, June 1958. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1504, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 12
O
10
Strain, 0.001 in.lin.
240 ,--------,-------,-------,-------,---------, 1680
55.170 AM-350 5CT850 stainless steel sheet, compressive stress-strain curves at room and elevated temperatures
200~------~------~------~------r---~~1400
Sheet thickness = 1.067 mm (0.042 in.). Treatment SCT850: annealed to condition L, subcooled -73 oC (-100 °P), 3 h, tempered 441-468 oC (825-875 °P), 3 h. Composition: Pe-17Cr-4Ni-3Mo. UNS S35000 Source: "Room and Elevated Temperature Tensile and Compressive Properties of Type AM-350," Data sheet 86-11457-350, Allegheny Ludlum Steel Corp., 1958. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1504, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 14
~------r_~~L-r_------r-------r-----~560
~---A~~------~------r-------r-----~280
2
4 Strain, 0.001 in.lin.
Stainless Steel (SS)/255
SS.171 AM-350 SCT850 stainless steel sheet, isochronous stress-strain curves at various temperatures
200 ,---,-----,-----, r----r-----r----, r---,--,-------, 1400
f---+--I-+-~--lI----+-+--+-----,-1Hl
Sheet thiekness = 1.016-1.651 mm (0.040-0.065 in.). SCT850: annealed to eondition L, subeooled -73 oC (-100°F), 3 h, tempered 441-468 oC (825-875 °F), 3 h. (a) 316 oC (600°F); (b) 371°C (700 °F); (e) 427 oC (800°F). Composition: Fe-17Cr-4Ni-3Mo. UNS S35000
f---+----j---j1120
840
.¡¡;
'"
11..
-'"
::¡; rñ
rñ
'" ~
'"
~ 560
I-JL--f--+---/ f--+---+---+----II-JOL--f--+---I 280
4
8
4
Slrain, 0.001 in.lin. (b) Slrain, 0.001 in.lin. (e) Slrain, 0.001 in.lin.
Source: "Creep Data AM-350 and AM-355 Alloys," Data Sheet 119121658S ... ;' Allegheny Ludlum Steel Corp. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1504, CINDAS/USAF CRoA Handbooks Operation, Purdue University, 1995, p 19
256/Stainless Steel (SS)
240
1680
SS.l72 AM-355 CRT stainless steel sheet, tensile stress-strain curves at room and elevated temperatures
200
1400
160
1120
Test direction: (a) longitudinal and (b) transverse. Sheet thickness = 1.422 mm (0.056 in.). CRT: cold roUed and tempered. hardness = 50-51 HRC. (a) longitudinal (b) transverse. Composition: Fe-15.5Cr-4.5Ni-3Mo. UNS S35500
.¡¡;
'"gf ~
a.
:::¡; 840 .;
120
$'"
Cf)
80
560
40
280
2
4
(a)
6 8 Strain, 0.001 in.lin.
10
0 12
240
1680
200
1400
160
1120
a.
~
.;
'"
~
:::¡; 840 .;
120
'"
~ 80
560
40
280
2
lb)
4
6 Strain, 0.001 in.lin.
0 12
Source: Data sheet 121-12159-355, Allegheny Ludlum, 1959. As publíshed in Aerospace Structural Metals Handbook, Vol 2, Code 1505, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 11
Stainless Steel (SS)1257
2 4 o . - - - - - - - - , . - - - - - - , - - - - - - - r - - - - - - , 1680
55.173 AM-355 CRT stainless steel sheet, compressive stress-strain curves at room and elevated temperatures
200~----~------_+-~~--r~---~1400
Test direction: longitudinal. Sheet thickness = 1.422 mm (0.056 in.). CRT: cold roUed and tempered. Hardness = 50-51 HRC. Specimen size =68.58 x 15.875 x 1.422 mm (2.7 x 0.625 x 0.056 in.); gage length = 38.1 mm (1.5 in.). Composition: Fe-15.5Cr-4.5Ni-3Mo. UNS S35500
160 ~----~--~'--7F__?"'------+-----~ 1120
Source: Data sheet 121-12159-355, Allegheny Ludlum, 1959. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1505, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 14 80~---~~~-----_+------~-----~560
40~~~-_4--------_+------~----~280
°0L-----~4--------~8-----1~2---~1~
Strain, 0.001 in.lin.
258/Stainless Steel (SS)
SS.174 AM-355 SCCRT stainless steel sheet, tensile stress-strain curves at room and elevated temperatures
320 ,------r-----,------,------,------,------.224o
280
~----~------~----~----~----~~~~~1960
Test direction: (a) longitudinal and (b) transverse. Sheet thickness =0.457 mm (0.018 in.). SCCRT: subcooled, cold roUed, tempered. RT, room temperature. Composition: Fe-15.5Cr-4.5Ni-3Mo. UNS S35500
-I7''----''#--~----__:I1680
240
200
'"
.¡¡;
"'rñ" fJ)
~
o.. :2
.~_-,1120 ~ éñ
160
120
80
40
Strain, 0.001 in.lin.
(a)
2240
320 Room temperature
280
1960
240
1680
200
1400 tU
o.. :2
~ rñ 160
1120 gf
fJ)
~
~
éñ 840
80
40
2 (b)
Strain, 0.001 in.lin.
Source: "Room and Elevated Temperature Tensile and Compressive Properties of SCCRT AM-355," Data sheet 114-82158-355, Allegheny Ludlum Steel Corp., 1958. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1505, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 12
Stainless Steel (SS)/259
320
55.175 AM-355 5CCRT stainless steel sheet, compressive stress-strain curves at room and elevated temperatures
2240 Room temperature 1960
Test direction: (a) longitudinal and (b) transverse. Sheet thickness = 0.457 mm (0.018 in.). SCCRT: subcooled, cold roUed, tempered. RT, room temperature. Composition: Fe-15.5Cr-4.5Ni-3Mo. UNS S35500
1680
200
1400
.¡¡; -'" ui
c..
::¡;
1120
'"
~
gf ~
C/)
Cií 120
840
560
280
2
4
(a)
6 8 Strain, 0.001 in./in.
10
320
2240 Room temperature
.¡¡; -'" ui
'"~
280
1960
240
1680
200
1400
c..
::¡;
160
1120 ui en ~
Cií
Cií 120
840
80
560
40
280
O O
2
(b)
4
6 8 Strain, 0.001 in./in.
10
1i
Source: "Room and Elevated Temperature Tensile and Compressive Properties of SCCRT AM-355," Data sheet 114-82158-355, Allegheny Ludlum Steel Corp., 1958. As publisbed in Aerospace Structural Metals Handbook, Vol 2, Code 1505, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 14
260/5tainless 5teel (SS)
SS.176 AM-355 SeT stainless steel sheet,
1400
200
isochronous tensile stress-strain curves at various temperatures
I '/
160
~
120
t
/fj ~
y 1 - 1000 h
~
SCT: subeooled and tempered. (a) 316 oC (600°F). (b) 371°C (700 °F). (e) 427 oC (800°F). Composition: Fe-15.5Cr-4.5Ni-3Mo. UNS S35500
1120
840 ro a.
11
'f1-100h / 1000 h
:2
Source: "Creep Data AM-350 and AM-355 Alloys," Data sheet 119121658-5, Allegheny Ludlum Steel Corp., 1959. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1505, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 18
Ul
~
Ul
I
1ií 80
I
40
~
~
I
1/
11
f.-10h
p
560
1ií
100 h I 1000 h
,/
280
o
12 4 8 12 O 4 8 12 O 4 8 Strain, 0.001 in./in. Strain, 0.001 in./in. Strain, 0.001 in./in. (a)
(b)
(e)
SS.l77 AM-355 XH stainless steel sheet, tensile stress-strain curves at room and elevated temperatures
360r----,----,----,----,----,----,----,---, 2520 320~--~~--r---~----r----r~~r----r--~
2240
Test direetion: transverse. Sheet thiekness =0.203 mm (0.008 in.). Heat treatment: mill solution treated and water quenehed, tempered 399 oC (750 °F), 5 mino Hardness = 54 HRC. Composition: Fe-15.5Cr-4.5Ni3Mo. UNS S35500
1960 1680 ~ 200~--~----r----h~~~~-r----r----r--~
~
ro
1400g¡
Ul
1120 ~
1ií
840 560 280
2
4
8 10 6 Strain, 0.001 in./in.
14
O
16
Source: Data sheet 130-10859-355, Allegheny Ludlum, 1959. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1505, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 12
5tainless 5teel (55)/261
140r-.-----¡-------,------,-~~--~----_¡
980
120~------+_------1~~~~~-- 400°F
840
(204 OC)
100~------+_--~~~-------r------_r------_i
~
80~------+_-+,~--1--------r--_=
SS.178 AM-362 stainless steel bar, tensile stressstrain curves at room and elevated temperatures Bar diameter = 25.4 mm (1 in.). Heat treatment: 816 oC (1500 °F), 1 h, air cooled, 566 oC (1050 °F), 2 h. Composition: Fe-15Cr-7Ni-0.88Ti. UNS S36200
700
___r------_i 560 ~
:::¡;
! 00
Source: "Properties of AM 362 Maraging Stainless Steel," Sheet-I9711763-362, Allegheny-Ludlum Steel Co., Research Data Center, Nov 1963. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1512, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 13
!Ji ti)
60~------~~~--1--------r------_r------_i
!!1 420 é'i5
40~--~~+_------1-------~------~------_1
280
140
2
6
4
8
0 10
Strain. 0.001 in.lin.
120
100
80
40
20
SS.179 AM-363 stainless steel strip, tensile stressstrain curve at room temperature
840
/ V
I
/
/
/v----
Composition: Fe(0.04C)-11.5Cr-4Ni-0.3Ti 700
560
C.
:::¡;
420
!Ji
E 00
280
140
2
Source: "AM-363 Strip for Strnctural Applications," Preliminary Data Sheet, Allegheny Ludlum Steel Corp., 11 Feb 1963. As published in Aerospace Structural Metals Handbook. Vol 2, Code 1409, CINDAS/ USAF CRDA Handbooks Operation, Purdue University, 1995, p 2
4 Strain. 0.001 in.lin.
6
262/Stainless Steel (SS)
200
160
/
120
.¡¡;
"'.;" '"~
éií
80
40
/
V
/
v ---
SS.180 Custom 450 H900 stainless steel bar, typical tensile stress-strain curve at room temperature
1400
Test direction: longitudinal and long transverse. Bar thickness = 25.4-304.8 mm (1.000-12.000 in.). Ramberg-Osgood parameter: n = 16. Composition: Fe15Cr-6Ni-1.5Cu-l.1Ti-(Nb> 8C). UNS S45000
1120
Source: MIL-HDBK-5H, Dec 1998, p 2-135
840 ro a.
/
:2
.; 560
~
280
2
4
6
8
10
o
12
Strain, 0.001 in./in.
160
.¡¡;
/
120
"'.;" '"
~
80
40
SS.181 Custom 450 Hl050 stainless steel bar, typical tensile stress-strain curve at room temperature
1400
200
/
V
1120
~-
Source: MIL-HDBK-5H, Dec 1998, p 2-139
840 ro a.
/ /
:2
j 560
280
2
Test direction: longitudinal and long transverse. Bar thickness = 25.4-304.8 mm (1.000-12.000 in.). Ramberg-Osgood parameter: n = 26. Composition: Fe15Cr-6Ni-1.5Cu-l.1Ti-(Nb> 8C). UNS S45000
4
6
Strain, 0.001 in./in.
8
10
o
12
Stainless Steel (SS)/263
300
~
'" 200 ~ Q)
~
100
SS.182 Custom 455 annealed stainless steel bar, true stress-strain curves
2800
400
-- ---------=====
,r
-----
----
Heat treatment: annealed 816 oC (1500 °P), 1 h, water quenched; (solid curve): + aged 482 oC (900 °P), 4 h, air cooled; (dashed curve): + aged 510 oC (950 °P), 4 h, air cooled. Composition: Pe-(low C)-12Cr-8Ni-2Cu-l.l Ti(Nb + Ta). UNS S45500
2100
al
a.
:;¡;
1400 ~ Oí
I I I
Q)
~
11
Source: Private communication with N.B. Schmidt, Carpenter Technology Corp., Reading, PA, 8 Jan 1974, and impublished data sheets. As published in Aerospace Structural MetalslHandbook, Vol 2, Code 1514, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 6
700
I I 0.2
0.4
o
0.6
0.8
True slrain, In(-\IA¡)
SS.183 Custom 455 annealed stainless steel bar, typical stress-strain curves at room and elevated temperature
2240
320
280
1960
Test direction: longitudinal. Bar diameter = 19.05 mm (0.75 in.). Heat treatment: annealed plus aged 510 oC (950 °P), 4 h, air cooled. Composition: Pe-(low C)-12Cr8Ni-2Cu-l.lTi-(Nb + Ta). UNS S45500
Room temperature 240
] gf ~
¿
160
Cií 120
~
80
40
"
400°F (204 OC)
---~--/
200
/
¡..--600°F (316 0Q1.
V-- rsOo °F (427 OC)
/'
2
1400
~
:;¡; 1120
~
840
~
560
280
4
6
gf Cií
~
/
1680
8
Strain, 0.001 in.lin.
10
12
Source: O.L. Deel and H. Mindlin, "Engineering Data on New Aerospace Structural Materials," Technical Report AFML-TR-71-249, Battelle Columbus Laboratories, Dec 1971. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1514, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 10
264/Stainless Steel (SS)
SS.184 Custom 455 annealed stainless steel bar, typical compressive stress-strain and compressive tangent modulus curves at room and elevated temperatures
Compressive tangent modulus, GPa
10,-------.:2::.,4 960 28o o;------:,.35'------7,.:o--..:..10r:5_ _1.:..,4..:,.0_---.:1-,-75'----_.::.2r:
1
240
I-----t---+---="""'-.¡..==:----f--,~-+---+_---j
1680
Test direction: longitudinal. Bar diameter = 19.05 mm (0.75 in.). Heat treatment: annealed plus aged 510 oC (950°F), 4 h, air cooled. RT, room temperature. Composition: Fe-(low C)-12Cr-8Ni-2Cu-1.lTi-(Nb + Ta). UNS S45500
200 ~-~.........=-+==:::::i=n..c::t~....:::::~:;;;;=-I+---I1400
'00
160 1-----t---+--=-.t;:H------:;"c-+_--+--1I-+__++_---j 1120 &.
~
~
~
~
m1W
MO
I
Source: O.L. Deel and H. Mindlin, "Engineering Data on New Aerospace Structural Materials," Technical Report AFML-TR-71-249, Battelle Columbus Laboratories, Dec 1971. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1514, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 14
801-----t~~-+---r--+_--r+--1I-+__+I---__j560
401---.~---+--~--~-~+-~--j+----j280
~_~
__
~
_ _- L_ _- L_
4
2
6
_L~~~L-_~O
8
10
12
14
25
30
35
Strain, 0,001 inJin,
o
10
5
I
I
15
20
Compressive tangent modulus, 106 psi
250
200
/
150
~ oí
'"
~
I
100
50
V
/
/
v--
---
1400
Source: MIL-HDBK-5H, Dec 1998, p 2-146
V
a. ~
oí
'"
700
350
4
Test direction: longitudinal and long transverse. Bar thickness = 25.4-152.4 mm (1.000-6.000 in.). RambergOsgood parameter: n = 22. Composition: Fe-(low C)12Cr-8Ni-2Cu-1.lTi-(Nb + Ta). UNS S45500
1050 ro
/
2
SS.185 Custom 455 H950 stainless steel bar, typical tensile stress-strain curve at room temperature
1750
6 Strain, 0,001 inJin,
8
10
~
5tainless 5teel (55)/265
200
V(
150
~ ui !I)
~
/
---
V
f-
6 8 Strain, 0.001 in.lin.
10
950°F (510°C) 1000 01" (538 OC)
200
I 1050 °F (566 OC) 160
1680
55.187 Fe-17Cr-7Ni-Ti stainless steel sheet, typical tensile stress-strain curves at room temperature for different aging temperatures
1400
Sheet thickness = 1.651 mm (0.065 in.). Composition: Fe-17Cr-7Ni-Ti. UNS S17600
1120 al
.¡¡; !I)
~
N
350
240
""ui
al
c..
::. 700
4
2
1400
Source: MIL-HDBK-5H, Dec 1998, p 2-150
V
V
Test direction: longitudinal and long transverse. Bar thickness = 25.4-152.4 mm (1.000-6.000 in.). RambergOsgood parameter: n = 25. Composition: Fe-(low C)12Cr-8Ni-2Cu-l.lTi-(Nb + Ta). UNS S45500
1050
/
100
50
55.186 Custom 455 Hl000 stainless steel bar, typical stress-strain curve at room temperature
1750
250
c..
::.
120
840 ui !I)
i
ro
80
560
40
280
00
4
8 Strain, 0.001 in.lin.
12
O
16
Source: Contributions to the Metallurgy of Steel: High Temperature High Strength Alloys, AISI, Feb 1963, p 88. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1511, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 4
266/Stainless Steel (SS)
240 r------,------,------,------,------,------,1680
55.188 Fe-17Cr-7Ni-Ti stainless steel sheet, typical tensile stress-strain curves at room and elevated temperatures
200 ~----~------~----~----~~----~----~1400
Test direction: longitudinal and transverse. Sheet thickness = 1.626 mm (0.064 in.). Heat treatment: Solution annealed plus aged 538 oC (1000 °F), 0.5 h. Composition: Fe-17Cr-7Ni-Ti. UNS S17600
160 ~----~------~----~--~~~----~----~1120
Source: P.J. Hughes, J.E. Inge, and S.B. Prosser, "Tensile and Cornpressive Stress-Strain Curves Properties of Sorne High-Strength Sheet Alloys at Elevated Ternperatures," NACA TN 3315, Nov 1954, p 19. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1511, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 5
.¡¡; ~
'"
i
120
80
40
0
0
2
4
6
8
10
Strain, 0.001 in.lin.
1400.------r-----,------,------,------r-----~
55.189 Al 2205 stainless steel, true stress-strain curves at various temperatures Strain rate = 0.0167/s. Composition: Fe-22Cr-5.5Ni-3MoN. UNS S31803 Source: c.L. Beech, "Effect of Ternperature and Strain Rate on lhe Mechanical Properties and Deformation Behavior of a Duplex Stainless Steel," M.S. thesis, Colorado School of Mines, Golden, ca, 1989. As published in G. Krauss, Steels: Heat Treatment Processing and PrincipIes, 1990, p 394
400~----~------+-----_+------~----~~----~
200~----~----_4------+_----_+------+_----~
OL-____-L____ ______ ____ ______L __ _ _ _ O 0.05 0.10 0.15 0.20 0.25 0.30 True strain ~
~
~
~
Stainless Steel (SS)1267
SS.190 XM-27 stainless steel, typical tensile properties at elevated temperatures
Test temperature. 'C
8018
93
204
316
427
538
649
760
871
98%60
jJ .... o '\o
o 70
...
/
''O
/
~
¡... .o ....c
\
490
~
,
UTS
;'
60
50 .¡¡; -'" ~
o, 40 r:::
~
420
\
~ ¡.......,..
0.2% YS
n
I
30
,, ,,
350 280
1\\
~ 210
140
\
l\\~
10
~
O
70
~
o
160
140
y
120
/
I
100
/ 1/
"#. ¿ .Q
80 iií el r:::
o
¡¡j
60
40
\..s
20
200
400
600
800
/
1000
/ 1200
Test temperature. 'F
~
r:::
\~\
20
oO
Short-time tests on high-chromium ferritic samples show pronounced decrease in strength with increasing temperature aboye 538 oC (1000 °F). Increase in strength at 427-538 oC (800--1000 °F) is due to precipitation hardening, which goes with the 475 oC (885°F) embrittlement phenomenon typical of high-chromium ferritic stainless steels. UTS, ultimate tensile strength; YS, yield strength. UNS S44627
\
/
1400
1600
1800
Source: F.K. Kies and C.D. Swartz, High Temperature Properties of High Purity Ferritic Stainless Steel, J. Test. Eva/., Vol 2 (No. 2), 1974, P 118-124. As published in E-Brite Alloy Product Data, Allegheny Ludlum Steel Corp., 1980, p 14
268/Stainless Steel (SS)
70
.--
60
50
'00 40
'"gf
SS.191 409 stainless steel sheet, room temperature longitudinal stress-strain
490
/
I
"""-
420
\\
350
280 ~ ~
~
éií 30
210
20
140
10
70
0.05
0.10
0.20
0.15
0.25
0.30
f éií
Sheet thickness = 1.499 mm (0.059 in.). Tests were run per ASTM Standard E 8. Standard flat samples 2 x 12.7 mm (0.5 in.) wide. Data shown are typical and should not be construed as maximum or minimum values for specification or for final designo Data on any particular piece of material may vary from those shown .. UNS S40900 Source: Courtesy Allegheny Ludlum in private cornmunication, March 2002
o
0.35
Strain, in.lin.
60
50
I
/
/
L
-""\
",.--
420
350
280 ~
'00 40
'"
f éií
SS.192 439 stainless steel sheet, room temperature longitudinal stress-strain
490
70
~
rñ ti) ~
30
210 éií
20
140
10
70
0.05
0.10
0.15
0.20 Strain, in.lin.
0.25
0.30
0.35
o
0.40
Sheet thickness = 1.549 mm (0.061 in.). Tests were run per ASTM Standard E-8. Standard flat samples 2 x 12.7 mm (0.5 in.) wide. Data shown are typical and should not be construed as maximum or minimum values for specification or for final designo Data on any particular piece of material may vary from those shown. UNS S43035 Source: Courtesy Allegheny Ludlum in private cornmunication, March 2002
Tool Steel (TS)/269
Tool Steel (TS) 140o,------------,------------,-----------,
1400,------------.------------,-----------,
A2
D2
1200~-----------~------------~----------4
1200~----------~------------r-~~~~--~
1000~-----------~------------~~~--~--4 •••••••••••••••••••: .............................................................. .
................. _~~
o" .............................................................
ca
~
800
/f
:!\. . . . ..
~
~
~
600
(
800
¡
~ ~ ~ 600~~.:-,1~/'----------r-----------~----------~
:i
~
1000 ,...................
/'"
~
400~-----------~~--------~r-----------~
400~+---------~------------r-----------~
200~----------~------------r------------
200~~--------~------------~----------~
o ./ o
°0L------------0.L.1----------~0~.2----------~0.3
0.1
True strain
1400r------------,~--------_.------------.
01
M2
1200~---T--~···~···~·~-···~··-···~···~···~·~..~ ...~ ...~~ ...-.. ~----------~
. .....
1000
-
i /
1000
~ 800~~~1J'~---------~------------~----------~ ~
1200~----------~----------~----------~
..........................
f·······:
~
0.3
(b) 1400r------------~----------_,~----------,
/f
0.2 True strain
(a)
.
....... .................................
............
/f (\..../ __ ~ 800~:~--==~~~~--~~~==~==---------1
~
~
600~-----------~------------~----------~
.~
600~----------~----------~~--------~
~
~ 400H-----------~~----------~----------~
400~----------~----------~~--------~
200ij------------~------------~----------~
200~----------~----------~~--------~
°OL----------~OL.1----------~0~.2----------~0.3 True strain
(e)
0.1 (d)
0.2
0.3
True strain
1400r------------,------------,-----------, W1 1200~-----------+------------r-~--------~
..... ...•....•........: ....
o · . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ..
/f
1000
¡--.......
00"
• •0
____ -
~ 800f.!~r~~-------r------------r-----------~
f 600~i+~-----------r------------~----------~ Q)
~
400~----------~------------~----------~
200H-----------~------------~----------~
°0~----------~OL.1----------~OL.2----------~0.3 (e)
True strain
TS.OOl Tool steel, uniaxial compressive true stress-strain curves Solid curves, quasi-static strain rate ~O.OOlls; dashed curves, dynamic strain rate = 2000/s. Quasi-static tests used a servohydraulic machine. High-rate tests used a compression split Hopkins pressure bar. Specimens were 4-6 mm diam, 8-12 mm long. Compositions: A2 (UNS T30102), Fe-1C-5.1Cr-1.15Mo-0.3V; D2 (UNS T30402), Fe-1.5C-12Cr-0.95Mo; M2 (UNS T11302), Fe-1.0C-0.27Mn-0.3Si-4.1Cr-5Mo-6.12W-1.98V; 01 (UNS T31501), Fe-0.92C-1.2Mn-0.5Cr-0.5W; W1 (UNS T72301), Fe1.1 C-0.25Mn-0.25Si. Source: G. Subhash, Dynamic Indentation Testing, Mechanical Testing and Evaluation, Vol 8, ASM Handbook, 2000, p 525
270/Tool 5teel (T5)
1S.002 D2 high-carbon high-chromium cold-work tool steel, torsional stress-strain curves with effed of tempering temperature
4or------------r----------~~----------_.400
2
3
Specimens air cooled 10 10 oc and then tempered: curve 1,175 oC, 60.6 HRC; curve 2, 290 oC, 58.2 HRC; curve 3,400 oC, 57.3 HRC. Typical composition: Fe-2.1C12.5Cr-0.3Ni. UNS T30402
30~------~--_+------------~----------__4300
E
Z
~
20 I----f--------+------------+----------___i 200
~
~
Source: Teledyne VASCO data. As published in G.A. Roberts, G. Krauss, and RL. Kennedy, Tool Steels, 5th ed., ASM Intemational, 1998, p 213
~
~
~
10~~---------+------------~------------4100
200 100 Deformation, degrees
308
1S.003 D3 high-carbon high-chromium cold-work tool steel, torsional stress-strain curves with effed of tempering temperature
40r------------,~----------_r----------__.400
Specimens quenched in oil at 970 oC to maximum hardness and then tempered: curve 1, 175 oC, 64.5 HRC; curve 2, 290 oC, 60.5 HRC; curve 3, 400 oC, 59 HRC. Typical composition: Fe-1.6C-13Cr-0.75Mo-0.3Y. UNS T30403
301------~~~-+------------+----------___i300
¿
E
~
z ~
20 I----f--------+------------+-------------j 200
~
~ ~
~
~
10~L----------+------------~----------~100
200 100 Deformation, degrees
308
Source: Teledyne VASCO data. As published in G.A. Roberts, G. Krauss, and RL. Kennedy, Tool Steels, 5th ed., ASM Intemational, 1998, p 213
Tool Steel (TS)/271
T5.004 H-11 Mod chromium hot-work tool sfeel bar, true tensile and compressive stress-strain curves
2520
360
320
2240 ro ::¡:
'00
!l.
.><
.,!Ji
.,!Ji
~
~
o
CIl :J
CIl :J
.=
.= 280
1960
Bar diameter = 51 mm (0.2 in.) for tension, 80458 mm (0.333 in.) for compression. Heat treatment: 1010 oC (1850 °P), 2 h, oil quenched, triple tempered, 566 OC (1050 °P), 1 h, air cooled. Data points: triangle, compression using special machine for alignment and Teflon lubricant; circle, tensile with intermittent die drawing to eliminate necking; square, tensile with data corrected for necking. Composition: Pe-004C-5Cr-l.3Mo-0.5V. UNS T20821 Source: R. Chait, Factors Influencing the Strength Differential in High Strength Steels, Metal/. Trans., Vol 3, Feb 1972, p 365-371. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1218, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 22
240 L-_ _---L_ _- L_ _--L_ _- ' -_ _'--_---Lc:--_--:-' 1680 O 0.1 0.2 0.3 0.4 0.5 0.6 0.7 True strain
500
400
------
Compressio~..-'
g¡
~
/P
,,/
~-
2800
...c
)--":fension
}/
300
gf ~
1ñ CIl
~
200
100
T5.005 H-11 Mod chromium hot-work tool steel bar, true tensile and compressive stress-strain curves
3500
I
V
2100
.,!Ji
~
CIl
1400 ~
I
700
5
&.
::¡:
10
15
True strain x 0.001
20
Bar diameter 51 mm (0.2 in.). Specimen machined from ausformed 15.748 mm (0.62 in.) diam bar. Consumable electrode vacuum melted bar hot worked at 1093 OC (2000 °P) from 63.5-38.1 mm (2.5-1.5 in.) diam, air cooled, double annealed 704 oC (1300 °P), 3 h, 649 oC (1200 °P), 2 h, 1038 oC (1900 °P), 1 h, air cooled to 566 oC (1050 °P), roUed to 83% plastic deformation at 566 oC (1050 °P), oil quenched, double tempered, 538 oC (1000 °P), 2 h to 60 HRC. Data points: triangle, compression; circle, tension. Ultimate strength = 2570 MPa (373 ksi); tensile yield strength = 2026 MPa (294 ksi); reduction in area = 33%. Composition: Pe-004C-5Cr1.3Mo-0.5V. UNS T20821 Source: J.E. Matheny, Jr., "Low Cycle Fatigue Properties of the Ausformed Steel," University of Illinois, T & A.M. Report No. 308, Feb 1968. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1218, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, P 22
272/Tool Steel (TS)
320
-3200F(-19~
280
~-110OF(-79oe)
240
y
200 .¡¡;
""ui (J)
~
160
120
80
40
/ V
/
)
V
Room
t~mperature
2240
TS.006 H-ll Mod chromium hot-work tool steel
1960
sheet, tensile stress-strain curves at room and low temperatures
Preheated 788 oC (1450 °P), 20-30 min, 1010 oC (1850 °P), 20 min, air cooled, triple tempered, 524 oC (975 °P), 1 h (each). After second temper, sheet ground to 1.524 mm (0.060 in.) to remove decarburization. Composition: Pe-OAC-5Cr-l.3Mo-0.5Y. UNS T20821
1680
1400 ro
a.
:2
g¡
1120
/
~ 840
Source: L.P. Rice, J.E. Cambell, and W.F. Simmons, "Evaluation of the Effects ofVery Low Temperature on Properties of Aircraf! and Missile Metals," WADD TR 60-214, Feb 1960. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1218, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 27
560 280
4
8
12
Strain, 0.001 in.lin.
TS.007 H-ll Mod chromium hot-work tool steel,
240 ,-------,-------,--------,-------,-------,1680
200
tensile stress-strain curves at room and elevated temperatures
Reat treated to 50 RRC; ultimate tensile strength = 1791 MPa (260 ksi). Composition: Pe-OAC-5Cr-l.3Mo-0.5Y. UNS T20821
~------+-------~----~-+~~--~~--~~1400
500, 650 °F (260, 343 °e) 800°F (427 °e) 900°F (482 °e)
160 ~------+--------I------,,¡L~--z~.-L;.7"!""'-------I1120
it.
.¡¡;
""ui (J)
~
:::; 120 ~------+-----~A-~~~~------~----~~840 ui
~
en
íi5 80 ~------+-~~~~~~---+------~--------I560
40
~--,f~~~~---I--------+------~--------I280
0 ~------~2------~4--------L6------~8------~1~ 0 Strain, 0.001 in.lin.
Source: "Vascojet 1000 for Ultra High Strength Structural Requirements," Vanadium Alloys Steel Co., 1959. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1218, CINDASI USAF CRDA Handbooks Operation, Purdue University, 1995, p 27
Tool Steel (TS)/273
8o,-------------,------------,-------------,56o
1S.008 H-ll Mod chromium hot-work (annealed) tool steel sheet, tensile stress-strain curves at room and elevated temperatures
Room temperature
,
400°F (204 OC) 600 °F, (316 oC) 800 'F (427 OC)
Sheet thickness = 1.626 mm (0.064 in.). Composition: Pe-0.4C-5Cr-1.3Mo-0.5V. UNS T20821
60~------~--~~--~~----_+-------------1420
tu
~
g 40 1-----I---I---I-",L--l-----------___1----------------1 280
~
~
Source: R.G. Henning and A.W. Brisbane. "Mechanical Properties of AM 350, Potomac A, Potomac M, and Vasco Jet-l000 Stee1 Alloys in the Annealed Condition," ASD TDR-63-116, May 1963. As published in Aerospace Structural Metals Handbook, Voll, Code 1218, CINDAS! USAF CRDA Handbooks Operation, Purdue University, 1995, p 27
,,;
~
1200 °F (649 'C) 20~~+_--_.~___1~----------_+-------------1140
8
4 Stwain, 0.001 in.lin.
320
1S.009 H-ll Mod chromium hot-work tool steel
2240
sheet, tensile stress-strain curves at room and elevated temperatures Room temperature
240
600 'F (316 OC)
1680
I
800 'F (427 OC) .¡¡;
"',,;" ti)
~
I
tu
c..
::;:
1000 'F (538 OC) 160
1120
g
~ 80
560
°0L-------4L-------8L-------1~2------~16~----~2~ Strain, 0.001 in.lin.
Sheet thickness = 2.286 mm (0.090 in.). Heat treated to ultimate tensile strength of 1929 MPa (280 ksi): 1010 oc (1850 °P), 30 min, air cooled, 538 oC (1000 °P), 2 x 3 h, 552 oC (1025 °P), 2 x 3 h. Composition: Pe-0.4C-5CrI.3Mo-0.5V. UNS T20821 Source: "AISI H 11 or Potomac A," Data Sheet, Allegheny Ludlum Steel Corp., Sept 1959. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1218, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 27
274/1001 Steel (TS)
360 320
f/~
280
g¡
2240
:::--'-'-110 °F (-79 OC)
~
V
240
T5.010 H-11 Mod chromium hot-work tool steel bar, tensile stress-strain curves at room and low temperatures
2520
/;-423 °F (-253 oC) -320°F (-196 oC)
t:--
Sheet thickness = 19.05 mm (0.75 in.). Reat treatment: 1010 oC (1850 °P), 1 h, air cooled, tempered twice 552 oC (1025 °P), 0.75 h, air cooled. Composition: Pe-004C5Cr-1.3Mo-0.5Y. UNS T20821
1960
70°F (21°C)
1680
1
ro
200
1400 ~
~ 1ií 160
~'"
1120
120
840
80
560
40
280
0.04
o
0.16
0.12
0.08
Source: K.A. Warren and R.P. Reed, Tensile and Impact Properties of Selected Materials from 20 to 300 °K, Monograph 63, National Bureau of Standards, 28 lune 1963. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1218, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 28
Strain, in./in.
280
1960
T5.011 H-11 Mod chromium hot-work tool steel bar, effect of strain rate on tensile yield strength at room and elevated temperature
270
' 1 1890
Bar diameter = 2504 mm (1 in.). Reat treatment: 1010 oC (1850 °P), 1 h, air cooled, tempered twice 566 oC (1050 °P), 1 h, air cooled. Composition: Pe-004C-5Cr1.3Mo-0.5Y. UNS T20821
260
Room temperature
T
}~ 1
1
1
ffi 1
l
~ 1820
~
:2 ~
1750
~
g> ~
"O
16801 ~ .¡¡; e
600°F (316 OC) 230
•
••
•
~
•
1610
1540
220
-
10
3
10
2
0.1
Elastic strain rate, in./in./s
1470 10
Source: D.P. Kendall, and T.E. Davidson, "The Effect of Strain Rate on Yielding of High Strength Steels," Report WVT 6618, Watervliet Arsenal, May 1966; D.P. Kendall, "The Effect of Strain Rate and Temperature on Yielding in Steels," Report WVT 7061, Watervliet Arsenal, Nov 1970. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1218, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 33
Tool 5teel (15)/275
T5.012 H-11 Mod chromium hot-work (annealed) tool steel sheet, compressive stress-strain curves at room and elevated temperatures
8o.---------,---------,----------r---------,56o
Sheet thickness = 1.626 mm (0.064 in.). Composition: Fe-0.4C-5Cr-1.3Mo-0.5Y. UNS T20821
60~--------+---------+_--~~--~--~----~420
Room temperature I
400°F (201°C) 600 °F (316 OC) 800°F (427 OC) 1000 °F (538 OC)
g¡ gf 40
~
ca
~
f-----_'-7"F-:;..-:¡,....-~------'-+_--------_+_--------__l 280 ui
~
4
2
Source: R.G. Henning and A.W. Brisbane, "Mechanical Properties of AM 350, Potomac A, Potomac M, and Vasco Jet-1000 Steel AIloys in the Annealed Condition," ASD TDR -63-116, May 1963. As published in Aerospace Structural Metals Handbook, Vol 1, Code 1218, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 33
6
Strain, 0.001 in.lin.
40f-------t------~~~-----l
T5.013 L-type low-alloy special-purpose tool steel, torsional stress-strain curves with effect of tempering temperature
f-------t---------l400 2
Specimens quenched in oil at 815 oC and then tempered: curve 1, 150 oC; curve 2, 175 oC; curve 3, 230 oc. (a) Ltype with vanadium. (b) Without vanadium E
¿
z
~
~
~
m m E- 20 ~+----~------j--------j I--+-----+------__j 200 E-
r+------~------~-----__j
Hr------r-----~100
o 0L.-.-----10'-0-------20'-0------30--'0 o (a)
Deformation, degrees
100
(b) Deformation, degrees
Source: Teledyne VASCO data. As published in G.A. Roberts, G. Krauss, and R.L. Keimedy, Tool Steels, 5th ed., ASM International, 1998, p 154
276/1001 5teel (15)
T5.014 L6 low-alloy special-purpose tool steel, torsional stress-strain curves with effect of tempering temperature
4or--------,---------,---------,--------~400
1--------t-----2
Specimens quenched in oil at 790 oC and then: curve 1, no tempering, 62.3 HRC; curve 2, tempered at 190 oC, 58.1 HRC. Composition: Fe-0.70C-0.55Mn-0.85Cr1.40Ni-0.25Mo. UNS T61206
30r------.~~-------+---------+--------~300
E
Z gi 20 1-----¡~--_I--------__+------_+----___1200 gi ~
Source: Teledyne VASCO data. As published in G.A. Roberts, G. Krauss, and R.L. Kennedy, Tool Steels, 5th ed., ASM International, 1998, p 163
~
~
~
10~----_I------+-----+----~100
100
200
300
Deformation, degrees
T5.015 1.1 % carbon W-type water-hardening tool steel, torsional stress-strain curves with effect of tempering temperature
300
,..- ... 3
'iij
"a. 200 ~
i ID
.o
¡¡::
E
t
/:2
~
4 _5
Brine quenched 788 oC (1450 °F) and tempered at: curve 1, as quenched; curve 2, 100 oC (212°F); curve 3, 150 oC (300 °F); curve 4, 175 oC (350°F); curve 5, 205 oC (400 °F); curve 6,260 oC (500°F); curve 7, 315 oC (600 °F), curve 8, 370 oC (700°F), curve 9, 425 oC (800 °F). The toughness of the tool steel is measured in the torsion test as deformation in radians versus the stress in the extreme fibers. 0.4 radian s is about 23°.
,..--- 6
7
~ V
/' 8
9
Source: G.A. Roberts, G. Krauss, and R.L. Kennedy, Tool Steels, 5th ed., ASM International, 1998, p 137
:J
E
.~
100
./"
:2
0.4
0.8
1.2
1.6
Deformation in radians
2.0
2.4
2.8
Nonferrous Metals
1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1
Cast Aluminum (CA)1279
Cast Aluminum (CA) CA.001 124EG-T5 aluminum permanent mold casting, tensile stress-strain curves, monotonic and cyclic
1000
Gerrnan casting material, Al-Si12-Cu-Ni-Mg with T5 tempero Tested at room temperature. Reference ASTM E 466 for cyclic force-controlled constant-amplitude fatigue test practices.
800
ro
600
a.
Source: John Deere Materials Data, Deere & CO., Moline, IL, p Bl3
::¡;
'"
~
400
... V
200
V
~
~~
--
¡...--
~
Monotonic _.. ----- ...... -_ .. ........ -............ ............ ........-- ........--
.' l& .' .. .....' .,.
V
4
2
6
10
8
12
14
16
18
20
Strain x 0.001
70
~Isand
490
CA.002 201.0-T6 aluminum casting, tensile stressstrain curves, various casting processes
420
Effect of casting process. Reat treatment: 2 h at 504-521 oC (940-970 °P), 14 h at 529 oC (985 °P), water quench, 24 h at room temperature, plus 20 h at 154 oC (310 °P), air cooled. Average mechanical properties for permanent mold castings: ultimate tensile strength, 450 MPa (65.2 ksi); tensile yield strength, 402 MPa (58.3 ksi). Average mechanical properties for sand castings: ultimate tensile strength, 394 MPa (57.1 ksi); tensile yield strength, 372 MPa (53.9 ksi). Average mechanical properties for insulated mold castings: ultimate tensile strength, 359 MPa (52.1 ksi); tensile yield strength, 349 MPa (50.6 ksi). UNS A02010
permanLt
60
~
/, lP~
50
g¡
40
~ (fl
30
20
10
/
V
Insulated
/ V
350
140
70
2
4
6 Strain, 0.001 in./in.
8
10
O
12
Source: "Mechanical Properties of Premium Aluminum Casting Alloys with Various Cooling Rates," Olin Corp., Jan 1973. As published in Cast Aluminum Section, Structural Alloys Handbook, Vol 3, CINDAS/ Purdue University, 1994, p 24, 67
280/Cast Aluminum (CA)
490
CA.003 201.0-T6 aluminum casting, compressive stress-strain curves, various casting processes
420
Effect of casting process. Heat treatment, 2 h at 504-521 oC (940-970 °F), 14 h at 529 oC (985°F), water quench, 24 h at room temperature, plus 20 h at 154 oC (310 °F), air cooled. Average compressive yield strength: permanent mold castings, 433 MPa (62.8 ksi); sand castings, 396 MPa (57.5 ksi); insulated mold castings, 382 MPa (55.4 ksi). UNS A02010
70
--i; ~
permanJnt
60
50
.¡¡; 40 -"
:i ~
éñ
30
20
10
/
/
V
50
2
'-.......
"::
350
280
¡f :2
:i 210
~
éñ
Source: "Mechanical Properties of Premium Aluminum Casting Alloys with Various Cooling Rates," Olin Corp., Jan 1973. As published in Cast Aluminum Section, Structural Alloys Handbook, Vol 3, CINDASI Purdue University, 1994, p 24, 67
140
4
6 8 Strain, 0.001 in./in.
Compressive tangent modulus, GPa 28 42 56
1---
--
~ t:--
-"
Insulated
r
- -
.¡¡; 40
'" ~
-
70
14
60
/
~-
10
o
12
CA.004 201.0-T6 aluminum casting, compressive tangent modulus curves, various casting processes
70
Permanent Sand
~ F===::::
Effect of casting process. Heat treatment, 2 h at 504-521 oC (940-970 °F), 14 h at 529 oC (985°F), water quench, 24 h at room temperature, plus 20 h at 154 oC (310 °F), air cooled. UNS A02010
420
--
350
280
¡f :2
30
210
20
140
10
70
2
4 6 8 10 6 Compressive tangent modulus, 10 psi
o
12
'"
~
Source: "Mechanical Properties of Premium Aluminum Casting Alloys with Various Cooling Rates," Olin Corp., Jan 1973. As published in Cast Aluminum Section, Structural Alloys Handbook, Vol 3, CINDASI Purdue University, 1994, p 24, 68
Cast Aluminum (CA)/281
70
60
¿
r
50
.¡¡; 40
/
-'"
¡i ~
en 30
20
10
------
permaneJ
CA.005 201.0-T7 aluminum casting, tensile stressstrain curves, various casting processes
420
Effect of casting process. Reat treatment, 2 h at 504-521 oc (940-970 °P), 14 h at 529 oC (985 °P), water quench, 24 h at room temperature, plus 5 h at 188 oC (370 °P), air cooled. Average mechanical properties for permanent mold castings: ultimate tensile strength, 439 MPa (63.7 ksi); tensile yield strength, 403 MPa (58.5 ksi). Average mechanical properties for sand castings: ultimate tensile strength, 385 MPa (55.8 ksi); tensile yield strength, 374 MPa (54.2 ksi). Average mechanical properties for insulated mold castings: ultimate tensile strength, 345 MPa (50.6 ksi); tensile yield strength, 344 MPa (49.9 ksi). UNS A02010
Sand Insul~
350
¡..---
280 ~ :2 210
V
/
490
~'"
140
Source: "Mechanical Properties of Premium Aluminum Casting Alloys with Various Cooling Rates," Olin Corp., Jan 1973. As published in Cast Aluminum Section, Structural Alloys Handbook, Vol 3, CINDAS!Purdue University, 1994, p 24, 67
70
V
4
2
6
8
o
10
12
Strain, 0.001 in.lin.
70
--:;::::~
60
50
J
.¡¡; 40 -'"
'"
~'"
en 30
I
20
10
I
perman~nt :::::-----r
Sand
~ted
490
CA.006 201.0-T7 aluminum casting, compressive stress-strain curves, various casting processes
420
Effect of casting process. Reat treatment, 2 h at 504-521 oC (940-970 °P), 14 h at 529 oC (985 °P), water quench, 24 h at room temperature, plus 5 h at 188 oC (370 °P), air cooled. Average compressive yield strength: permanent mold castings, 429 MPa (62.2 ksi); sand castings, 407 MPa (59.1 ksi); insulated mold castings, 377 MPa (54.7 ksi). UNS A02010
350
l'
280 ~ :2
/
210
140
/
70
2
4
6 8 Strain, 0.001 in.lin.
10
o
12
~'"
Source: "Mechanical Properties of Premium Aluminum Casting Alloys with Various Cooling Rates," Olin corp., Jan 1973. As published in Cast Aluminum Section, Structural Alloys Handbook, Vol 3, CINDAS! Purdue University, 1994, p 24, 67
282/Cast Aluminum (CA)
14
60
50
Compressive langenl modulus, GPa 28 42 56
~
"---~
'00 40
-'"
CA.007 201.0-T7 aluminum casting, compressive tangent modulus curves, various casting processes
70
----- --Permanenl
~nd
r.--,. Insulaled
Effect of casting process is illustrated. Heat treatment, 2 h at 504-521 oC (940-970 °P), 14 h at 529 oC (985 °P), water quench, 24 h at room temperature, plus 5 h at 188 oC (370 °P), air cooled. UNS A02010
420
350
8:
280
:2 ,,;
,,;
~ rJ)
~
30
210
20
140
10
70
2
4
6
8
6
Source: "Mechanical Properties of Premium Aluminum Casting Alloys with Various Cooling Rates," Olin Corp., Jan 1973. As published in Cast Aluminum Section, Structural Alloys Handbook, Vol 3, CINDAS/ Purdue University, 1994, p 24, 68
o
10
12
Compressive langenl modulus, 10 psi
Permanenl
40
280
~ ;...-
~
30 '00 -"
,,;
'" ~ 20
10
CA.008 201.0-T43 aluminum casting, tensile stressslrain curves, various casting processes
350
50
/
/
r
Sand
~ ~:ed
210
:2
140
70
2
'"
Il.
4
6 8 Slrain, 0.001 in./in.
10
o
12
N
Effect of casting process. Heat treatment, 2 h at 504-521 oC (940-970 °P), 14 h at 529 oC (985 °P), water quench, 24 h at room temperature, plus 0.5 h at 154 oC (310 °P), air cooled. Average mechanical properties for permanent mold castings: ultimate tensile strength, 407 MPa (59.0 ksi); tensile yield strength, 250 MPa (36.2 ksi). Average mechanical properties for sand castings: ultimate tensile strength, 356 MPa (51.7 ksi); tensile yield strength, 243 MPa (35.3 ksi). Average mechanical properties for insulated mold castings: ultimate tensile strength, 273 MPa (39.6 ksi); tensile yield strength, 225 MPa (32.6 ksi). UNS A02010 Source: "Mechanical Properties of Premium Aluminum Casting Alloys with Various Cooling Rates," Olin Corp., Jan 1973. As published in Cast Aluminum Section, Strurtural Alloys Handbook, Vol 3, CINDAS/ Purdue University, 1994, p 24, 67
Cast Aluminum (CA)/283
Perman~
40
30
I
~
'" U)
~
ro
20
10
CA.009 201.0-T43 aluminum casting, compressive stress-strain curves, various casting processes
350
50
/ V
t r:::::
F- Sand
I-¡";;;Iated
1-:=
280
-
210
'"
a.
::¡;
'"
140
~
Effect of casting process. Heat treatment, 2 h at 504-521 oC (940-970 °F), 14 h at 529 oC (985°F), water quench, 24 h at room temperature, plus 0.5 h at 154 oC (310 °F), air cooled. Average compressive yield strength: permanent mold castings, 272 MPa (39.4 ksi); sand castings, 266 MPa (38.6 ksi); insulated mold castings, 238 MPa (34.5 ksi). UNS A02010 Source: "Mechanical Properties of Premium Aluminum Casting Alloys with Various Cooling Rates," Olin Corp., Jan 1973. As published in Cast Aluminum Section, Structural Alloys Handbook, Vol 3, CINDAS/ Purdue University, 1994, p 24, 67
70
4
2
8
6
10
Strain, 0.001 in.lin.
50
40
o
14
30
'"
70
"-
-----
Effect of casting process is illustrated. Heat treatment, 2 h at 504-521 oC (940-970 °F), 14 h at 529 oC (985°F), water quench, 24 h at room temperature, plus 0.5 h at 154 oC (310 °F), air cooled. UNS A02010
Permanent Sand 210
::¡;
~
éií
20
140
10
70
I 4 6 8 10 6 Compressive tangent modulus, 10 psi
'"
a.
Insulated
U)
2
CA.010 201.0-T43 aluminum casting, compressive tangent modulus curves, various casting processes
84 350
280
~~
~ .¡¡; .:.:
Compressive tangent modulus, GPa 28 42 56
~'"
Source: "Mechanical Properties of Premium Aluminum Casting Alloys with Various Cooling Rates," Olin Corp., Jan 1973. As published in Cast Aluminum Section, Structural Alloys Handbook, Vol 3, CINDAS/ Purdue University, 1994, p 24, 68
284/Cast Aluminum (CA)
80
60
20
CA.Oll A201.0-T7 aluminum casting, typical tensile stress-strain curve
560
/ 1/ 2
v
v-- -
420
ro
a.
::¡;
Designated area, at room temperature. Ramberg-Osgood parameter, n(tension) = 14. S basis design properties (originally presented in ksi) for strength class 1 and 2, designated area within casting: ultimate tensile strength, 414 MPa (60 ksi); tensile yield strength, 345 MPa (50 ksi); compressive yie1d strength, 352 MPa (51 ksi). UNSA12010
280 rñ
~
en
Source: MIL-HDBK-5H, Dec 1998, p 3-463, 3-465
140
4
10
8
6
Strain, 0.001 in./in.
CA.012 242.0-T5 aluminum permanent mold casting, tensile stress-strain curves, monotonic and cyclic
1200
1000
Cyclic
800 ro
o..
::¡;
rñ 600
ti)
~
U5 400
200
/
V 2
¿ /-4
V ...............
6
/
V
/
L
/
......... ...........
Monotonic
10 12 Strain x 0.001
AI-Cu-Ni-Mg system. Tested at room temperature. Reference ASTM E 466 for cyclic force-controlled constant-amplitude fatigue test practices. UNS A02420 Source: John Deere Materials Data, Deere & Co., Moline, IL, p C13
............ .......... ................ .............
8
V
14
16
18
20
Cast Aluminum (CA)/285
CA.OH A332.0-T5 (PC) aluminum permanent mold casting, tensile stress-strain curves, monotonic and cyclic
1200
1000
Al-Si-Ni-Mg system. Tested at room temperature. Reference ASTM E 466 for cyc1ic force-controlled constant-amplitude fatigue test practices. UNS A13320 replaced by UNS A03360
800 ro
o..
Source: John Deere Materials Data. Deere & Co., Moline, IL, p D14
~
rñ 600 CI)
~ 400 Cyclic
200
~:::-.... ••••.•
M~~otonic
/-" ......
/,#
4
2
6
8
10
12
14
16
18
20
Strain x 0.001
CA.014 E332.0-T5 aluminum permanent mold casting, tensile stress-strain curves, monotonic and cyclic
1200
1000
Al-Si-Ni-Mg system. Tested at room temperature. Reference ASTM E 466 for cyc1ic force-controlled constant-amplitude fatigue test practices.
800
Source: John Deere Materials Data, Deere & Co., Moline, IL, p Fl3
ro
o..
~
rñ 600
CI)
~ en
400 Cyclic
200
vv-/'
I ~f.,---.......................... ¡..--••••••••••••• M~~~tonic
."
•
6
8
10
12
Strain x 0.001
14
16
18
20
286/Cast Aluminum (CA)
1200
1000
800
V
l1.
::¡;
g 600
(J)
400
/
V
V
v.----'
200
2
/
/
Tested at room temperature. Reference ASTM E 466 for cyc1ic force-controlled constant-amplitude fatigue test practices. UNS A63320 replaced by UNS A03320
V
Source: John Deere Materials Data, Deere & Co., Moline, IL, p Al4
........... Monotonic _.......... ....... --- ...........
............. .-.. -.. - .......... -
........
4
/
/
V
CA.015 F332.0-T5 (SR) aluminum permanent mold casting, fensile sfress-sfrain curves, monotonic and cyclic
6
10 12 Strain x 0.001
8
14
16
18
20
1200r---~--~--.---.---.---~---r---.---,--~
800~--+---+---+---+---+-~+---~--~---r---
ro
a.
::¡;
600~--~--+---+---+---+---4---4---~--~--~
~
ro
400~--~--~--+---+---+---4---4---~---r--~
200
/'"
oV O
2
~
4
:'::~: --_ ...... _.. -.. --- ----_ .... oo-, ••••••• -•• -. Monotonic
6
8 10 12 Strain x 0.001
14
16
18
20
CA.016 354.0-T5 aluminum permanent mold casting, fensile sfress-strain curves, monofonic and cyclic
354.0-T5 casting material, Al-Si-Cu-Mg system. Tested at room temperature. Reference ASTM E 466 for cyclic force-controlled constant-amplitude fatigue test practices. UNSA03540 Source: John Deere Materials Data, courtesy of Deere & Co., Moline, IL, p E12
Cast Aluminum (CA)/287
50
40
(
V
L---
~
~
1---
--
.¡¡; 30
2
lO
n.
::¡;
Q)
1-
Specimen size: 6.25 mm (0.250 in.) diam, 31.75 mm (1.25 in.) gage length. UNS A33550
280
210
"'
CA.017 C355.0-T61 aluminum casting, tensile uniaxial true stress-strain curve
350
20
140
10
70
0.10
0.20
0.30
0.40
True strain
0.50
0.60
o
0.70
E (J)
Source: J. Mattavi, "Low Cycle Fatigue Behavior Under Biaxia1 Strain Distribution," TP-67 -16-T, Hamilton Standard, Sept 1967. As published in Cast A1uminum Section, Structural Alloys Handbook, Vol 3, CINDASlPurdue University, 1994, p 70
288/Cast Aluminum (CA)
30
25
CA.018 356.0-T6 aluminum casting, tensile stress strain curves at several temperatures
245
35 80°F 27 oC)
,--
I
-
'\
210
300°F [149 oC) 175
"""'\
450°F [232 oC 140
20
ro
o..
Effect of strain rate and temperature. Strain rate is 1.0 S-l. Hold times at given temperatures: 1800 s (top); 10 s (bottom). Material was solution heat treated at 540 oC (1000 °F), water quenched, and aged at 154 oC (310 °F) for 3 h. UNS A03560
:2
10
--
Ir
5
105 cñ IJ) ~
éií 70
600°F [316 oC)
--~
35
o
o 30
25
20
/'
rr
~
210 1
50 0 °F [266 oC)
T T
175
--x 4do °F [20~ oC)
140 ro
o..
:2
'í
105 IJ) cñ
600°F [316 oC
~
éií
10
70
5
35
0.01
0.02
0.03
0.04 0.05 Strain, in./in.
0.06
0.07
0.08
o
0.09
Source: H.E. Dedman, EJ. Wheelan, and E.J. Kattus, "Tensile Properties of Aircraft-Structural Metals at Various Rates of Loading after Rapid Heating," WADC TR-58-440, Southem Research Institute, Part 1, Nov 1958. As published in Cast Aluminum Section, Structural Alloys Handbook, Vol 2, CINDASlPurdue University, 1994, p 71
Cast Aluminum (CA)/289
30
300'~ (149 ,¿)
25 20
IÍ I{
V
175
450 'F (232 'c)
Source: R.E. Dedman, E.J. Wheelan, and EJ. Kattus, "Tensile Properties of Aircraft-Structural Metals at Various Rates of Loading after Rapid Reating," WADC TR-58-440, Southern Research Institute, Part 1, Nov 1958. As published in Cast Aluminum Section, Structural Alloys Handbook, Vol 2, CINDASlPurdue University, 1994, p 71
70
-
600 'F 316'C)
5 /'
35
o
o
30
20
Effect of strain rate and temperature. Strain rate is 0.01 S-l. Ho1d times at given temperatures: 1800 s (top); 10 s (bottom). Material was solution heat treated at 540 oC (1000 °P), water quenched, and aged at 154 oC (310 °P) for 3 h. UNS A03560
140
10
25
CA.019 356.0-T6 aluminum casting, tensile stress strain curves at several temperatures
210
210 ~
f/
3JO'F .(1 d9'C)
175
~ 450 'F (232 'c)
140
'"
Il.
:::¡
105 600'F (316'C) 10
70
5
35
0.02
0.03
0.04
~
U5
/'
0.01
(1)
0.05
Strain, in./in.
0.06
0.07
0.08
o
0.09
290/Cast Aluminum (CA)
25
CA.020 356.0-16 aluminum casting, tensile stressstrain curves at several temperatures
210
30
f
80°F J7 OC)
'T
// Yr- ~
175
X 300 T(149t
20
140 lo Io 450 F (232 C)
.
a.
::¡;
105 ui
'"~
Effect of strain rate and temperature. Strain rate is 0.00005 S-l. RoId times at given temperatures: 1800 s (top); 10 s (bottom). Material was soIution heat treated at 540 oC (1000 °P), water quenched, and aged at 154 oC (310°F) for 3 h. UNS A03560
Uí 10
----
5
o 30 25 20
~ ui
~ 15
f
/
300
l
35
~316°1)
o 210 175
(149 OC) 140
450°F (232 oC
5
.
a.
::¡;
105 ui
'"
~
(IJ
10
Source: H.E. Dedman, EJ. Wheelan, and EJ. Kattus, "Tensile Properties of Aircraft-Structural Metals at Various Rates of Loading after Rapid Heating," WADC TR-58-440, Southem Research Institute, Part 1, Nov 1958. As published in Cast Aluminum Section, Structural Alloys Handbook, Vol 2, CINDASlPurdue University, 1994, p 71
70
- --0.01
0.02
0.03
70 35
160~ °F (31r OC) 0.04
0.05
Strain, in./in.
0.06
0.07
0.08
o
0.09
Cast Aluminum (CA)1291
70
60
V
./
50
'00 40
""rñ
E en 30
20 K
~
/
420
Chill cast aluminum. Hardness, 41 HRB. UNS A03560
280
Room temperature
210
20
140
10
70
0.06
0.09
0.12
~
;:¡; rñ
~
0.03
Source: K.A. Warren and R.P. Reed, Tensile and Impact Properties of Selected Materials from 20 to 300 K, Monograph 63, National Bureau of Standards, June 1963. As published in Structural Alloys Handbook, Vol 3, CINDASlPurdue University, 1994, p 70
76K 195 K
~~
CA.021 356.0-T6 aluminum casting, tensile stressstrain curves at low temperature
350
~
t-----
490
~
O
0.15
Strain, in.lin.
CA.022 A356-T6 aluminum cast cylinder, monotonic tensile stress-strain curve
300
250
/; ~
200
~
y
.--
......
,
Near-net-shape casting formed by pouring molten alloy, 704 oC (1300 °F) into investment molds at room temperature (X), 538 oC (1000 °F) (Y), and 982 oC (1800 °F) (Z). Three different cooling rates create different microstructures. Curves are results from one laboratory. Property values are average s from seven labs as part of a round-robin test programo Young's modulus, GPa (psi x 106), X, 70 (10.1), Y, 70 (10.1), Z, 71 (10.3); yield strength 0.2% MPa (ksi), X, 229 (33.3), Y, 224 (32.5), Z, 217 (31.5); ultimate strength MPa (ksi), X, 283 (41.1), Y, 266 (38.6), Z, 252 (36.6); strain hardening exponent (n), X, 0.083, Y, 0.087, Z, 0.091; strain hardening coefficient K, MPa (ksi), X, 388 (56.4), Y, 397 (57.6), Z, 382 (55.4). UNS A13560
Z
!
ro :::¡;
o..
gf
-
-
x
~:: f:-': ,
150
1/ ~
100
V 50 ~
1/ 5
10
15 Strain x 0.001
20
25
30
Source: Fatigue and Fracture Toughness of A356-T6 Cast Aluminum Alloy, R.1. Stephens, Ed., SP-760, Society of Automotive Engineers, 1988.
292/Cast Aluminum (CA)
50
350
40
280
CA.023 A356.0-T6 aluminum casting, tensile stressstrain curves, various casting processes
~ermanent
30
20
10
/
V
~
~ V
\sand
\
210 \
ti!
c..
Insulated
::¡;
g 140
Source: "Mechanical Properties of Premium Aluminum Casting Alloys with Various Cooling Rates," Olin Corp., Jan 1973. As published in Cast Aluminum Section, Structural Alloys Handbook, Vol 3, CINDAS/ Purdue University, 1994, p 24,66
70
4
2
6
10
8
Effect of molding process. Reat treatment, 12 h at 538 oC (1000 °P), water quench, 12-24 h delay at room temperature, 3 h at 154 oC (310 °P), and air cooled. Average mechanical properties for permanent mold castings: ultimate tensile strength, 299 MPa (43.4 ksi); tensile yield strength, 215 MPa (31.2 ksi). Average mechanical properties for sand castings: ultimate tensile strength, 253 MPa (36.7 ksi); tensile yield strength, 223 MPa (32.3 ksi). Average mechanical properties for insulated mold castings: ultimate tensile strength, 219 MPa (31.7 ksi); tensile yield strength, 205 MPa (29.8 ksi). UNS A13560
o
12
Strain, 0.001 in.lin.
40
/
30 '00 ~
,¡¡
'" ~ 20
10
CA.024 A356.0-T6 aluminum casting, compressive stress-strain curves, various casting processes
350
50
/
V
f
----~---
280 f- Permanent f- Sand Insulated
210
V--
gf 140
70
2
4
6 Strain, 0.001 in.lin.
8
rf. ::¡;
Effect of molding process. Reat treatment, 12 h at 538 oC (1000 °P), water quench, 12-24 h delay at room temperature, 3 h at 154 oC (310 °P), and air cooled. Average compressive yield strength: permanent mold castings, 219 MPa (31.7 ksi); sand castings, 245 MPa (35.6 ksi); insulated mold castings, 192 MPa (27.9 ksi). UNSA13560
10
o
12
~
Source: "Mechanical Properties of Premium Aluminum Casting Alloys with Various Cooling Rates," Olin Corp., Jan 1973. As published in Cast Aluminum Section, Structural Alloys Handbook, Vol 3, ClNDAS/ Purdue University, 1994, p 24, 66
Cast Aluminum (CA)/293
50
o
14
Compressive tangent modulus, GPa 56 28 42
CA.025 A356.0-T6 aluminum casting, compressive tangent modulus curves, various casting processes
70
280
40
30
~
'" ~
en
20
Effect of molding process. Heat treatment, 12 h at 538 oC (1000 °P), water quench, 12-24 h delay at room temperature, ,3 h at 154 oC (310 °P), and air cooled. UNS A13560
~"-...
1---;:: "'" 1----~-¡......
210
--.!:.ermanent
~ulated
--
:--
~
::i:
r-
Source: "Mechanical Properties of Premium Aluminum Casting Alloys with Various Cooling Rates," Olin Corp., Jan 1973. As published in Cast Alurninum Section, Structural Alloys Handbook, Vol 3, CINDAS/ Purdue University, 1994, p 68
~
r--
140
ro
r70
10
4
2
6
8
10
Compressi\le tangent modulus, 106 psi
50
o
14
Compressive tangent modulus, GPa 28 42 56
CA.026 A356.0-T6P aluminum casting, typical tensile and compressive stress-strain and tangent modulus curves
70
280
40 Compression \
.¡¡;
'<~
30
-'"
'" ~
en
20
10
/
/
v:
V
210
Tension
V1---1---
~
"\
140
70
2
4
6
ro
c..
::i:
8
Strain, 0.001 in./in. Compressive tangent modulus, 106 psi
10
I
Tested at room temperature. Ramberg-Osgood parameters, n(tension) = 10, n(compression) = 9.2. In the temper designation, T6P, P indicates a difference in the standard procedure or difference in the minimum tensile requirements as compared to the Aluminum Association's limits. S basis values for A356.0-T6P per AMS 4218: Ultimate tensile strength, 220 MPa (32 ksi); tensile and compressive yield strength, 152 MPa (22 ksi). UNS A13560 Source: MIL-HDBK-5H, Dec 1998, p 3-482, 3-483
294/Cast Alurninurn (CA)
350
50
40
/
30
-
v---
280
210
I
.¡¡; .l<
CA.027 A356.0-T6P aluminum casting, fuI! range tensile stress-strain curve
,f ::;;;
~
~
Uí
140
20
o o
0.02
o
0.06
0.04 Strain, in.lin.
0.08
CA.028 A357.0-T6 aluminum cast plate, tensile stress-strain curves
420
60
50
('
..---
-
%
1-- 0.001
in.lin. 280
I V
ca
O-
::;;; 210
~
(J)
140
/
v
70
2
Sand cast plate thickness: 6.35 mm (0.25 in.). The full range strain is given in % (top curve) and the expanded range strain is in 0.001 in./in. (bottom curve). Composition: Al-7.0Si-0.6Mg-0.ITe-Be. UNS A13570
350
/'
40
10
Source: MIL-HDBK-5H, Dec 1998, p 3-482, 3-483
70
10
20
Uí
Tested at room temperature. X indicates fracture. In the temper designation T6P, P indicates a difference in the standard procedure or difference in the minimum tensile requirements as compared to the Aluminum Association's limits. S basis values for A356.0-T6P per AMS 4218: ultimate tensile strength, 220 MPa (32 ksi); tensile and compressive yield strength, 152 MPa (22 ksi). UNS A13560
4
6
8
Strain, % and 0.001 in.lin.
10
Source: "Deve1opment: Premium Alloy Castings of Alloy A357.0-T6," A1coa, Pittsburgh, PA, 1971. As pub1ished in Aerospace Structural Metals Handbook, Vo15, Code 3109, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 24
Cast Aluminum (CA)/295
40
/
30 ·00
..>< u)
'"~
éñ
20
/
10
v
~
~
1280
v
210
~-
4
6 8 Strain, 0.001 in./in.
10
O 12
350
40
280
.L-~
30
'"~
éñ
20
/
/
Source: MIL-HDBK-5H, Dec 1998, p 3-485, 3-486
140 éñ
50
·00
Class 2 alloy casting, designated area, at room temperature. Ramberg-Osgood parameter, n(tension) = 16. S basis design properties (originally presented in ksi) for strength class 2, designated area within casting: ultimate tensile strength, 345 MPa (50 ksi); tensile and compressive yield strength, 276 MPa (40 ksi). UNS A13570
70
2
..>< u)
&.
:2
IV
10
CA.029 A357.0-T6 aluminum casting, typical tensile stress-strain curve
350
50
? ----
~
+--
Permanent
Sand
210 -
4
6 8 Strain, 0.001 in./in.
ro
o.
Insulated
:2
gf ~ 140
70
2
CA.030 A357.0-T6 aluminum casting, tensile stressstrain curves, various casting processes
10
O 12
en
Effe:ct of molding process. Reat treatment, 12 h at 538 oC (1000 °F), water quench, 12-24 h delay at room temperature, 5 h at 177 oC (350°F), and air cooled. Average mechanical properties for permanent mold castings: ultimate tensile strength, 316 MPa (45.8 ksi); tensile yield strength, 243 MPa (35.2 ksi). Average mechanical properties for sand castings: ultimate tensile strength, 268 MPa (38.9 ksi); tensile yield strength, 229 MPa (33.2 ksi). Average mechanical properties for insulated mold castings: ultimate tensile strength, ·179 MPa (26.0 ksi); tensile yield strength, 179 MPa (26.10 ksi). UNS A13570 Source: "Mechanica1 Properties of Premium A1uminum Casting Alloys with Various Coo1ing Rates," 01in Corp., Jan 1973. As published in Cast Aluminum Section, Structural Alloys Handbook, Vol 3, CINDAS/ Purdue University, 1994, p 24, 66
296/Cast Aluminum (CA)
350
50
CA.031 A357.0-T6 aluminum casting, compressive stress-strain curves, various casting processes
Permanent \. 40
280
~->::::::f-
~ ~~sulated Sand
30
'"~
<ñ
I
20
10
/
50
40
30 '00
'"
a.
:2
/
~
Source: "Mechanical Properties of Premium Aluminum Casting Alloys with Various Cooling Rates," Olin Corp., Jan 1973. As published in Cast Aluminum Section, Structural Alloys Handbook, Vol 3, CINDAS/Purdue University, 1994, p 24, 66
70
2
o
210
Ir
~
Effect of molding process. Reat treatment, 12 h at 538 oC (1000 °P), water quench, 12-24 h del ay at room temperature, 5 h at 177 oC (350 °P), and air cooled. Average compressive yield strength: permanent mold castings, 256 MPa (37.2 ksi); sand castings, 240 MPa (34.8 ksi); insulated mold castings, 232 MPa (33.7 ksi). UNS A13570
14
~
4
6 8 Strain, 0.001 in./in.
Compressive tangent modulus, GPa 28 42 56
10
o
12
CA.032 A357.0-T6 aluminum casting, compressive tangent modulus curves, various casting processes
70
Effect of molding process. Reat treatment, 12 h at 538 oC (1000 °P), water quench, 12-24 h delay at room temperature, 5 h at 177 oC (350 °P), and air cooled. UNS A13570
280
~r---
_ _ Permanent
r-::::::::: ~
-'"
~
'~"
<ñ
210
F==:::
:2
ro1--
~
CJ)
20
140
10
70
2
'"
a.
4 6 8 10 Compressive tangent modulus, 106 psi
o
12
Source: "Mechanical Properties of Premium Aluminum Casting Alloys with Various Cooling Rates," Olin Corp., Jan 1973. As published in Cast Aluminum Section, Structural Alloys Handbook, Vol 3, CINDAS/ Purdue University, 1994, p 24, 68
Cast Aluminum (CA)/297
60
420
50
40
20
10
I 1/
/
---
r-
-
140
70
o 4
2
6 8 Strain, 0.001 in.lin.
10
40
I
30
V
v-~
CA.034 D357.0-T6 aluminum casting, typical tensile stress-strain curve
~
280
210
1/
""!Ji 1/)
~
Ci5 20
10
12
350
50
.¡¡;
Source: "Development: PremiumAlloy Castings of Alloy A357.0-T6," Aleoa, Pittsburgh, PA, 1971. As published in Aerospace Structural Metals Handbook, Vo15, Code 3109, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 29
280
o
O
Sand cast plate thickness: 6.35 mm (0.25 in.). Composition: AI-7.0Si-0.6Mg-0.ITe-Be. UNS A13570
350
J
/ V
CA.033 A357.0-T6 aluminum cast plate, compressive stress-strain curve
/
IJ..
:2
140
/
70
2
ro
Designated area, at room temperature. Ramberg-Osgood parameter, n(tension) = 16. B basis design properties (originally presented in ksi) for designated area within casting: ultimate tensile strength, 338 MPa (49 ksi); tensile and compressive yield strength, 285 MPa (41 ksi). UNSA43570
4
6 8 Strain, 0.001 in.lin.
10
~ Ci5
Source: MIL-HDBK-5H, Dec 1998, p 3-488, 3-489
1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1
1
1
Wrought Aluminum (WA)1299
Wrought Aluminum (WA) WA.OO1 Heat-treafable aluminum alloys, true stressstrain curves 560 ~------~--------~~~---+--r-------~420
X2020-T6, 2014-T4, 2024-T36, 2024-T86, 6061-0, 6061-T4, 6061-T6, 6063-T6, 7075-0, 7075-T6, 7079-T6, 7178-T6
~------~--------+----+---+--~--~~-1140
~-7~--~--------+----+---+--+-------~70
8L--------L--------L---~---L--L-------~56
0.01
0.02
0.04 0.06 True strain, in./in.
0.08 0.1
0.2
98
14
./
12
/
10
/'
I~ ~
V
84
T~"""
.,...o- )-"U'"
70 Nominal
IV
, ,\
\
{
4
I
~
.ryC'
2
o
V
O O
"\
.,.....o-" >--'"
Yield strength
I I I
1
28
14
O
0.04 0.08 0.12 0.16 0.20 0.24 0.28 0.32 0.36 0.40 0.44 Slrain, in./in. 0.4 0.8 1.2 1.6 2.0 2.4 2.8 Strain, 0.001 in./in.
WA.002 1060-0 aluminum alloy rod, tensile stressstrain curves The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essentially identical for both the true and nominal curves. Test specimen diam, 12.7 mm (0.5 in.). Gage length: 203.2 mm (8 in.). Nominal tensile strength, 67.2 MPa (9.75 ksi). True tensile strength, 86.2 MPa (12.5 ksi). Nominal yield strength (0.2% offset), 21 MPa (3.0 ksi). Elongation (in 50.8 mm, or 2 in.), 42.7%. Reduction of area, 91 %. True strain at maximum load, 24.8%. A loglog plot of the stress-strain curve would yield a slope (n) of 0.22 in the area of uniform plastic deformation. UNSA91060 Souree: Alcoa, A1uminum Research Laboralory, New Kensinglon, PA, Oel1951
300/Wrought Aluminum (WA)
14
12
/~
10
~
rñ 8
'"
1ñ
6
IL
~
4
2
I
I o
18
V
~
/
0.04
0.08
0.4
0.8
0.16 0.20 Strain, in./in. 2.0 1.2 1.6 Strain, 0.001 in./in.
8
o
'"
~
Q)
42 ~ e
~ 28
2.4
2.8
'\.
/
.,/'
\
~
~
I 1o 0.32 3.2
126
WA.004 1060-H18 aluminum alloy rod, tensile stress-strain curves
112
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essentially identical for both the true and nominal curves. Test specimen diam, 12.7 mm (0.5 in.). Gage length: 203.2 mm (8 in.). Nominal tensile strength, 119 MPa (17.2 ksi). True tensile strength, 121 MPa (17.5 ksi). Nominal yield strength (0.2% offset), 108 MPa (15.6 ksi). Elongation (in 50.8 mm, or 2 in.), 6.7%. Reduction of area, 79%. True strain at maximum load, 2.0%. A log-log plot of the stress-strain curve would yield a slope (n) of 0.02 in the area of uniform plastic deformation. UNS A91060
~~ strength 98 84
\
ro
Il.
70 \
~
'"~
1ñ
56 .l!! \ \
11
V
0.28
.¡¡;
,, , ,,
42
28
I
I
14
1
O
0.01
0.02
0.03
O
0.4
0.8
1.2
0.04 0.05 0.06 0.07 Strain, in./in. 1.6 2.0 2.4 2.8 Strain, 0.001 in./in.
0.08
0.09
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essentially identical for both the true and nominal curves. Test specimen diam, 12.7 mm (0.5 in.). Gage length: 203.2 mm (8 in.). Nominal tensile strength, 73.1 MPa (10.6 ksi). True tensile strength, 87.6 MPa (12.7 ksi). Nominal yield strength (0.2% offset), 57 MPa (8.2 ksi). Elongation (in 50.8 mm, or 2 in.), 31.1 %. Reduction of area, 90%. True strain at maximum load, 18.0%. A loglog plot of the stress-strain curve would yield a slope (n) of 0.14 in the area of uniform plastic deformation. UNS A91060 Source: Alcoa, Aluminum Research Laboratory, New Kensington, PA, July 1954
14
\
I
~
0.24
-..., ~o~inal
I
::l
I
56 :2 rñ
Yield strength
0.12
V
""_10
2
ro
Il.
I
.¡¡;
4
~1\ \
~
6
.,...~
70
\ \ \
12
.l!! .¡¡; e
Nominal
"'"'
{
14
84
\
~
/
16
~
~ f.--
L
~
.l!! .¡¡; e
WA.003 1 060-H12 aluminum alloy rod, tensile stress-strain curves
98
O
0.10
e ~
Source: A1coa, Aluminum Research Laboratory, New Kensington, PA, July 1954
Wrought Aluminum (WA)/301
16
14
V
/ ~~
12
cñ 8
~ .¡¡; <=
¡!!1 6
WA.005 1100-0 aluminum alloy rod, tensile stressstrain curves
98
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essentially identical for both the true and nominal curves. Test specimen diam, 12.7 mm (0.5 in.). Gage length: 203.2 mm (8 in.). Nominal tensile strength, 84.8 MPa (12.3 ksi). True tensile strength, 103 MPa (15.0 ksi). Nominal yield strength (0.2% offset), 33 MPa (4.8 ksi). Elongation (in 50.8 mm, or 2 in.), 30.0%. Reduction of area, 88%. True strain at maximum load, 20.0%. A loglog plot of the stress-strain curve would yield a slope (n) of 0.22 in the area of uniform plastic deformation. UNSA91100
Nominal
-
'"\
84
\
70 a. '" :2
~
f ¡
..l<
~ 1i)
.....--
/,
10 .¡¡; U)
~
112
:i
56 ~
~ .¡¡; <=
42 ¡!!1 ..k,
Yield strength
4
2
28
~
/
V o
Souree: Aleoa, Aluminum Researeh Laboratory, New Kensington, PA, luly 1954
14
I I 1
0.04
0.08
0.4
0.8
0.112
0.16 0.20 Strain, in.lin. 1.2 1.6 2.0 Strain, 0.001 in.lin.
0.24
0.28
o
0.32
2.4
20
WA.006 11 00-H12 aluminum alloy rod, tensile stress-strain curves
140
~
Nominal
~,
.1l ~
15
f
/
V
r-tr
,,
strength
105
,,
a.'"
:2
\
o
o
0.01
~ .¡¡; <=
\ \
¡!!1
\ \
\ \ \ \ \ \
V
O
())
70 11;
\
I
5
:i
~
0.02
0.03
2
3
0.04 0.05 Strain, in.lin.
4
5
Strain, 0.001 in.lin.
0.06
0.07
0.08
35
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essentially identical for both the true and nominal curves. Test specimen diam, 12.7 mm (0.5 in.). Gage length: 203.2 mm (8 in.). Nominal tensile strength, 111 MPa (16.1 ksi). True tensile strength, 108 MPa (15.7 ksi). Nominal yiéld strength (0.2% offset), 99.3 MPa (14.4 ksi). Elongation (in 50.8 mm, or 2 in.), 8.5%. Reduction of area, 76%. True strain at maximum load, 3.4%. A loglog plot of the stress-strain curve would yield a slope (n) of 0.05 in the area of uniform plastic deformation. UNSA91100 Source: Aleoa, Aluminum Researeh Laboratory, New Kensington, PA, luly 1954
o
0.09
302/Wrought Aluminum (WA)
20
f 15
.T - -
Nominal
V
~~ slrenglh
cl
I I
5
~
\ \ \ \
0.02
0.01
O
105
\
\ \ \ \ \ I 35 I I I I I I 1 o 0.07 0.06
V
o
WA.007 11 OO-H16 aluminum alloy rod, tensile stress-strain curves
140
____True
o
2
0.03 0.04 Slrain, in.lin.
3
0.05
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essentially identical for both the true and nominal curves. Test specimen diam, 12.7 mm (0.5 in.). Gage length: 203.2 mm (8 in.). Nominal tensile strength, 132 MPa (19.2 ksi). True tensile strength, 135 MPa (19.6 ksi). Nominal yield strength (0.2% offset), 122.7 MPa (17.8 ksi). Elongation (in 50.8 mm, or 2 in.), 6.8%. Reduction of area, 79%. True strain at maximum load, 1.7%. A log-log plot of the stress-strain curve would yield a slope (n) of 0.02 in the area of uniform plastic deformation. UNS A91100 Souree: Aleoa, Aluminum Researeh Laboratory, New Kensington, PA, July 1954
4
Slrain. 0.001 in.lin.
WA.008 11 OO-H18 aluminum alloy rod, tensile stress-strain curves
210
30
--
True
25
p-
(
~ 20 cñ
~
I
~
.~
15
~
10
5
o
/ V
O
o
175 Nominal
V
/~ ~dSlrenglh
gf ~
"'"
1/
0.01
en
a..
140 :;¡
1ií ~
105 .~
~
\ \ \ \ \
70
\ \
\ \
35
\
\ \ \ )..
0.02 2
0.04 0.03 Slrain. in.lin.
3
4
Slrain, 0.001 in.lin.
0.05 5
0.06
O 0.07
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essentially identical for both the true and nominal curves. Test specimen diam, 12.7 mm (0.5 in.). Gage length: 203.2 mm (8 in.). Nominal tensile strength, 171 MPa (24.8 ksi). True tensile strength, 175 MPa (25.4 ksi). Nominal yield strength (0.2% offset), 157 MPa (22.8 ksi). Elongation (in 50.8 mm, or 2 in.), 6.6%. Reduction of area, 72%. True strain at maximum load, 2.0%. A log-log plot of the stress-strain curve would yield a slope (n) of 0.06 in the area of uniform plastic deformation. UNSA91100 Souree: Aleoa, Aluminum Researeh Laboratory, New Kensington, PA, July 1954
Wrought Aluminum (WA)/303
20
1-::::::::
r
~
L ~d
~
strength
15
1/
140
Nominal
True_
~
"'~\
105
1\ \
\ \ I
J
¡
5
o
O
O
0.01
I
35
I I I 2
0.03
0.04 0.05 0.06 Strain, in.lin. 345 Strain, 0.001 in.lin.
0.07
0.08
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essentially identical for both the true and nominal curves. Test specimen diam, 12.7 mm (0.5 in.). Gage length: 203.2 mm (8 in.). Nominal tensile strength, 125 MPa (18.2 ksi). True tensile strength, 138 MPa (20.0 ksi). Nominal yield strength (0.2% offset), 119 MPa (17.2 ksi). Elongation (in 50.8 mm, or 2 in.), 8.6%. Reduction of area, 78%. True strain at maximum load, 3.9%. A log-log plot of the stress-strain curve would yield a slope (n) of 0.06 in the area of uniform plastic deformation. UNSA91100 Source: A1coa, Aluminum Research Laboratory, New Kensington, PA, July 1954
1 0.02
WA.009 1100-H26 aluminum alloy rod, tensile stress-strain curves
O
0.09
304/Wrought Aluminum (WA)
WA.Ol0 2014-T6 aluminum alloy, ciad 2014-T6,
Temperature, oc
801r8________,93~_______2,0-4--------3T16--------,42ko
room-temperature tensile properties
Effect of exposure to elevated temperature. Composition: Al-4.5Cu-lMn-lSi-O.5Mg. UNS A92014 ~ u.~
ro c.. ::;;:
-
60 ~--------+_--~~L-+---~~--~--------~420
u.z
,5
~e ~
..
el
~
1ií
~
.$
ro E
@
40 ~--------+_---------''II-----T-------~--''r_----~ 280
::l
5
•
0.5 h o 100 h 1000 h
.
20
L---------L---------~--------~--------~140
80 ,---------,---------,---------,---------,540
420
60
ro c.. ::;;:
~
u.1':'
u.1':'
.c c, e
280
40
.c
g, ~
~
1ií
1ií
"C
ID
"C
~
>=
140
20
OL---------L---------~--------~--------~O
1"1 l· ;P--E I O
OO
200
400
Temperature, °F
600
800
Source: Metallic Materials & Elements for Flight Vehicle Structures, MIL-HDBK-5, Dept. of Defense, FSC 1500, Aug 1962. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3201, CINDAS! Purdue University, 1995, p 19
Wrought Aluminum (WA)/305
WA.011 2014-16 aluminum alloy, ciad 2014-16, bar, tensile stress-strain curves
8o,-------r-------,-------,-------,-------,56o -320°F (-196 OC)
Tested at various temperatures. Bar diameter: 19.05 mm (0.75 in.). Composition: AI-4.5Cu-1Mn-1Si-0.5Mg. UNSA92014
70r---~--+-----r------_+--------~~--~490
Exposure:
- - - Yo h
..,. - --100°F (-73 OC)
- - - 10 min
""
Room Temperature
60~------~------+-----~+-~--~~~~~420
50~------+--------h~~~-+~~~~~------4350
m Q.
::2
: 40
~
Source: "Phase II-Cryogenic Properties of 2014-T6 and A-286," Bell Aerosystems Co., BLR61-35(M) Rev. A, 29 June 1962. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3201, CINDASlPurdue University, 1995, p 19
1---------+----~L.L------:~....¡,~:::==-I---------l280 ~ ~
30r-------r-~~~t-------+_------+-----__1210
500°F (260 OC) 20r-----~~~~~-+-------_+--------r-----~140
10~~~=i--==~~-------t-----_i------~70
600 °F(316 OC) OL-------L-------~-------L-------L-----~O
O
0.002
0.004
0.006
0.008
0.010
Strain, in.lin.
50
WA.012 2014-16 aluminum alloy, ciad 2014-16, isochronous tensile stress-strain curves
350 Shorttime
,.
40
""
----...... ........ ---
""
Tested at 205 oC (400°F). Composition: AI-4.5Cu-1MnISi-0.5Mg. UNS A92014 280
1h 10 h
30
210
'00
m
Q.
""uien ~ 20
::2 ui en
100 h 140 1000 h
10
70
°0~----------~0-.0~0-4-----------0-.0~0-8----------~0.of2 Strain, in.lin.
~
Source: P.M. Howell and G.W. Stickley, "Isochronous Stress-Strain Curves for Several Heat-Treated Wrought Aluminum Alloys at 300 and 400 F," Aleoa Research Laboratories, 29 Apri11958. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3201, CINDAS/ Purdue University, 1995, p 25
306/Wrought Aluminum (WA)
80 Rolled
60 t~3
20
in. (76 mm)
V
V
/
WA.013 2014-T6 aluminum alloy, dad 2014-T6, rolled bar, rod, and extrusions, tensile and compressive stress-strain curves
560
b~r, rod, and shapes
-- '=-- -
:.--
r, thickness. Composition: Al-4.5Cu-lMn-lSi-0.5Mg. UNSA92014
420
'"
o.. :2
280 '"
~
140 - - - Tension - - Compression
I
o
o
80,-------,-------,--------,-------,-------,560 Extrusion
0.500 in. (12.7 mm) Area ~ 25 in? (161 cm 2) t>
60~------+-------~----~~~~--~------~420
t= 0.125-0.499 in. (3.175-12.675 mm)
g¡ gf 40 ~
I--------+-----~'+---------+------__t------__I
'"
~
280 '" w
~
W 20~----_7~------~-------+------~------~140
°0~-----~2-----~4~------~6-----~8------~1~·
Strain. 0.001 in.lin.
Source: Metallic Materials & Elements for Flight Vehicle Structures, MIL-HDBK-5, Dept of Defense, FSC 1500, Aug 1962. As published in Aerospace Structural Metals Handbook, Vo13, Code 3201, CINDAS/ Purdue University, 1995, p 18
Wrought Aluminum (WA)/307
WA.014 2014-T6 aluminum alloy, ciad 2014-T6, rolled and drawn rod, effect of exposure to elevated temperature on tensile properties
Temperature, oC
150
95
205
20
"'"~ "" ~~ '"
Exposure time • 30 min ... 96 h • 10,000 h
._ 60
'"
c.. :2 ::J
420 lJ..:5 Ol
c
~ 280
'~
"'-----
I
80
g¡
315
--......
""-
-
260
E
S 140 560
420 c.. '" :2
~ " "~ ~ """ "
:5
g> 40
~
"O
a;
>=
20
'--o
é ¿
;¡
20
.~ c
....-'
o
~
¿-
Ol C
¡fi ~oo
200
300
-
400
_..... 500
Exposure temperature, °F
%l
600
700
Tested at room temperature. Composition: Al-4.5CulMn-lSi-O.5Mg. UNS A92014 Source: Report on the Elevated Temperature Properties of Aluminum and Magnesium Alloy, STP 291, ASTM, Oc! 1960. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3201, CINDAS/ Purdue University, 1995, p 22
308/Wrought Aluminum (WA)
Temperature,
oc
WA.015 2014-T6 aluminum alloy, ciad 2014-T6, forged rod, effect of exposure to elevated temperature on tensile properties
80r1_5________,95__________ 2or5_________3,1_5________-,42~60
~ -=-
~
Tested at room temperature. Composition: Al-4.5CulMn-lSi-O.5Mg. UNS A92014
ro
60 f-----------I------\---,-''-;t---------'''rl----------l 420
~ -=-
~
~
~
~ e
~ e
o
0
~
~
2
2
~ 40
280 ~
~
S
~
Exposure time .30 min
S
A 100 h • 1000 h 010,000 h 20L---------~---------L--------~--------~140
80
560
60
420 ro
a..
~
:;¡;
-=-
-=-
~ .s:: C, e
~
~
~
i
'E, 280
40
"O
"O
Ci
Ci
;;:
;;:
140
20
0L---------L---------L---------L-------~0
80
560
40
280
E E
~ .~ N .~
e
~
e o
(
1iiOl e o
1_
-
[jJ
o
O
200
... ~
./-:
400 Exposure temperature, °F
V 600
? o
800
Source: Report on the Elevated Temperature Properties of Aluminum and Magnesium Alloy, STP 291, ASTM, Oct 1960. As published in Aerospace Structural Metals Handbook, Vo13, Code 3201, CINDAS! Purdue University, 1995, p 22
Wrought Aluminum (WA)/309
WA.016 2014-T6 aluminum alloy, ciad 2014-T6, sheet, effect of exposure and test temperature on compressive yield strength
Test temperature, oC 80~15 ________~95__________ 20~5_________3,1_5________-,42~60
Thickness: 1.626 mm (0.064 in.). Composition: Al4.5Cu-1Mn-1Si-0.5Mg. UNS A920l4
g¡
60 1-----------''''''-=''------+------\--------1420 ~
Source: D.E. Miller, "Determining Physical Properties of Ferrous and Non-Ferrous Structural Sheet Materials at Elevated Temperatures:' AFTR 6517, Pt 3, Dec 1953. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3201, CINDASlPurdue University, 1995, p 22
Exposure • 1/2 h o 100 h A 1000 h 200
.----
80
60
400 Tes! temperature, °F
~-r-
808
600
WA.017 2014-T6 aluminum alloy, ciad 2014-T6, sheet, uniaxial and biaxial stress-strain curves
560
x Biaxial2:1 Uniaxial
~ 13.5%
Test direction: longitudinal. Typical for sheet thickness 3.18 mm (0.125 in.). Composition: AI-4.5Cu-1Mn-1Si0.5Mg. UNS A92014
x 420
Biaxial1:1
i -¡¡;
280
.§" e
.§. -¡¡; e
·E o
Z
20
140
2
4 6 Nominal principal strain, %
8
Source: E.L. Terry and S.W. McClaren, "Biaxial Stress and Strain Data on High Strength Alloys for Design of Pressurized Components," ASD-TDR-62-401, Chance-Vought Corp., 1962. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3201, CINDAS/ Purdue University, 1995, p 18
310/Wrought Aluminum (WA)
WA.018 2014-T6 aluminum alloy, dad 2014-T6, sheet, tensile stress-strain curves
7o.---.---,----r---r---.---,---,----r---r-~490
Room Temperature
Tested at room and elevated temperatures. Sheet thickness: 1.626 mm (0.064 in.). Composition: Al-4.5Cu-lMnlSi-0.5Mg. UNS A92014
60~--+_--~--~---r---+--~--~_=~~--r-~420
350
·00 40 ~--+_--~--~+-~~-+---+---t---~-1-~ 280
rf.
"""
:2
~
~~
éií 30
Source: D.E. Miller, "Deterrnining Physical Properties of Ferrous and N on-Ferrous Structural Sheet Materials at Elevated Temperatures," AFTR 6517, Pt 3, Dec 1953. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3201, CINDAS/Purdue University, 1995, p 19
210 éií
500°F (260 OC) 10r-~~~~~+--r+---+---+--+_--+_--+_~
600°F (316 OC)
70
0~0---L---L2---L3---L4---L5---L6---L7---L8---L9--~1~ Strain, 0.001 in./in.
560
WA.019 2014-T6 aluminum alloy, dad 2014-T6, sheet, compressive stress-strain curves
490
Tested at room and elevated temperatures (1/2 hour at temperature). Sheet thickness: 1.626 mm (0.064 in.). Composition: Al-4.5Cu-lMn-lSi-0.5Mg. UNS A92014
Room temperature
420 350
'"
~
:i
$
o..
40 ~-+_-+_-~--/-*--7I"'-----+-~---t---t--~ 280
:2 ui U)
~ 210 500°F (260 OC) 140
Strain, in./in.
Source: D.E. Miller, "Deterrnining Physical Properties of Ferrous and Non-Ferrous Structural Sheet Materials at Elevated Temperatures," AFTR 6517, Pt 3, Dec 1953. As published in Aerospace Structural Metals Handbook, Vo13, Code 3201, CINDAS/Purdue University, 1995, p 22
Wrought Aluminum (WA)/311
100~--------r---------r---------~--------'
700
80~--------~--------~--------+_------__1
560
WA.020 2014-T6 aluminum alloy, ciad 2014-T6, sheet, short-time total strain curves
Tested at 150-315 oC (300-600 °P). Therrnal expansion included. Sheet thickness: 1.016 mm (0.040 in.). Composition: AI-4.5Cu-1Mn-1Si-0.5Mg. UNS A92014
300°F (149 0C) ______-+_______-+______- j 420
60
..
40
o
•
0.27% 280
400°F (204 oC)
I
500 °F (260 OC)
~ 20~---------~1----------+--~~~-+--------1 ~
'"
l.A. Van Echo, W.F. Wirth, and W.F. Simmons, "Short-Time Creep Properties of Structnral Sheet Materials for Aircraft & Missiles," AFTR 6731, Pt II1, May 1955. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3201, CINDASlPnrdue University, 1995, p 25
Jl.
::;;
140
rñ CI)
~
iñ
C/l
10~--------~--------~~~---+_------__1
70
8~--------~--------+_--~~~+_------__1
56
Total strain
• 2% o 3% ... 5% v 7%
6
42
28 10
4~-----~--------~--------~--------J
10-2
10-3
10- 1
Time, h
80
----
560
WA.021 2014-T4 aluminum alloy rod, tensile stressstrain curves
490
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essentially identical for both the true and nominal curves. YS, yield strength. Test specimen diam, 19.05 mm (0.75 in.). Gage length: 203.2 mm (8 in.). Nominal tensile strength, 448 MPa (65.0 ksi). True tensile strength, 517 MPa (75.0 ksi). Nominal yield strength (0.2% offset), 302 MPa (43.8 ksi). Elongation (in 50.8 mm, or 2 in.), 16.8%. Reduction of area, 32%. True strain at maximum load, 14.1 %. A log-log plot of the stress-strain curve would yield a slope (n) of 0.21 in the area of uniforrn plastic deforrnation. UNS A92014
True
70
~ / ' f,.-<>./
60
~ 50
~
(
rñ CI)
'"
~ 40 .!!1
I
'00 e
~ 30
-
'/ ~
Nominal
420 I I I I I I
~~ Yield strength
I
I I
V
20
I I I I I I
I
10
o
V
350
rñ CI)
280 ~CI) .!!1 '00 e 210 ~
140 70
I I 1
O
0.02
0.04
0.06
o
2
4
6
0.08
0.10
Slrain, in.lin.
8
10
Strain, 0.001 in.lin.
0.12
0.14
0.16
& ::;;
O 0.18
Sonrce: Alcoa, Aluminum Research Laboratory, New Kensington, PA, June 1953
312/Wrought Aluminum (WA)
--
80
70
r
60
gj
--~
e
30
10
o
l:Í
280 ~ (J) ~
'00
e 210 ~
140
70
Source: Alcoa, Aluminum Research Laboratory, New Kensington, PA, July 1954 0.02
0.04
0.06 0.08 Strain, in.lin. 4 6 8 Strain, 0.001 in.lin.
2
(a)
0.12
10
12
560
70
r
60
~
.~
50
I
~ 40 ~
'00
e
30
20
10
-~ ~
Nominal
l:Í ())
~
I
I V o
/
V
490
.r...-of' ~
~---420
Yield strength
350 rf.
:2
'"
280 ~ ti)
/
~
'00
e 210 ~
140
70
0.02
0.04
2
4
0.06 Strain, in.lin.
0.08
6
8
Strain, 0.001 in.Jin. (b)
o
0.10
80
gj
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essentially identical for both the true and nominal curves. YS, yield strength. Test direction: (a) longitudinal; (b) transverse. Test specimen thickness, 15.9 mm (5/8 in.). Gage 1ength: 203.2 mm (8 in.). Nominal tensi1e strength, 473 MPa (68.6 ksi). True tensi1e strength, 514 MPa (74.6 ksi). Nominal yield strength (0.2% offset), 436 MPa (63.2 ksi). Elongation (in 50.8 mm, or 2 in.), 9.0%. Reduction of area, 23%. True strain at maximum load, 8.6%. A log-log plot of the stress-strain curve would yield a slope (n) of 0.08 in the area of uniform plastic deformatíon. UNS A92014
:2
11
I V
490
350 rf.
I
~
'00
WA.022 2014-T6 aluminum alloy plate, tensile stress-strain curves
420
Yield strength
/
'" I!! tí 40
20
~
-
1/
50
~
~ Nominal
560
o
0.10
0.12
10
12
Wrought Aluminum (WA)/313
WA.023 2014-T6 aluminum alloy, ciad 2014-T6, sheet, tensile stress-strain curves
700
100
80
Tested at room temperature. Typical for sheet thickness 1..016-6.325 mm (.0 ..04.0-.0.249 in.). Ramberg-Osgood parameter: n(longitudinal, tension) = 27; n(long transverse, tension) = 2.0. UNS A92.o14
560
Longitudinal
Source: MIL-HDBK-5H, 1 Dec 1998
..1 60
~ ui
'" ~
ro
40
20
V
V 2
V
~
Long
tr~nsverse
420
CIl
Il..
:2
~
!!:! 280
ro
140
4
8
6
10
o
12
Strain, 0.001 in./in.
14
Compressive tangent modulus, GPa 28 42 56
80
-- /' --V V
60
""rñ ~'"
ro
40
20
Tested at room temperature. Test direction: L, longitudinal. Typical for thickness :::::76.2.0 mm (:::::3 ..0.0.0 in.). Ramberg-Osgood parameter: n(L, tension) = 31; n(L, compression) = 25. UNS A92014
560
Longitudinal, compression
'0;
WA.024 2014-T6 aluminum alloy rolled bar, rod, and shapes, tensile and compressive stress-strain and compressive tangent modulus curves
70
¿:. :::'---¡:-ongitudinal, co~pression
r--
2
4
Source: MIL-HDBK-5H, 1 Dec 1998
Longitudinal, tension 420 CIl
Il..
:2
1'\
8 6 10 Strain, 0.001 in./in. 6 Compressive tangent modulus, 10 psi
280
140
o
12
~
ro
314/Wrought Aluminum (WA)
14
Compressive tangent modulus, GPa 28 42 56
80
Tested at room temperature. Test direction: L, longitudinal. Typical for extrusion thickness 3.175-12.675 mm (0.125-0.499 in.). Ramberg-Osgood parameter: n(L, tension) = 23; n(L, compression) = 15. UNS A92014
560 L, compression
"-.....r--
60 '¡;¡ -'" ","
'"~
i'ií
40
20
WA.025 2014-T6 aluminum alloy extrusion, tensile and compressive stress-strain and compressive tangent modulus curves
70
V
V 2
L, compression
V
---b:: r----
Source: MIL"HDBK"5H, 1 Dec 1998 420
L, tension
!""----
~
ro a. ::;¡;
~ 280 i'ií
140
6 8 10 Strain, 0.001 in./in. Compressive tangent modulus, 106 psi 4
o
12
90
630
WA.026 2014-T6 aluminum alloy forging, tensile stress-strain curves (full range)
80
560
Tested at room temperature. Typical. UNS A92014
Longitudinal 70
r
60
g¡
I
-
.-+
-
-
--
Long transverse
420
50
ro 350 ~
40
280 ]
30
210
20
140
10
70
'"
~
Source: MILBDBK"5H, 1 Dec 1998
490
uf
en
o
O
0.02
0.04
0.06 0.08 Strain, in./in.
0.10
0.12
o
0.14
Wrought Aluminum (WA)/315
WA.027 2014-T62 aluminum alloy extrusion, tensile and compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
o
14
28
42
56
70
84
8or------r-----,------.------.------~----_,560
Tested at room temperature. Test direction: L, longitudinal; LT, long transverse. Typical for extrusion thickness ::;;12.675 mm (::;;0.499 in.). Ramberg-Osgood parameter: n(L, tension) =29; n(LT, tension) = 17; n(L, compression) = 29; n(LT, compression) = 32. UNS A92014 Source: MIL·HDBK-5H, 1 Dec 1998
~
g ~
~
::i:
40 f------t-------Ff------+------+------+-__I-----j 280
uf
~
Cií
20f---~A_----__I------+------+------+-__I-----j140
L-----~2------~4------~6------~8------1~0--~~1~
Strain, 0.001 in.lin. 6 Compressive tangent modulus, 10 psi
80
WA.028 2014-T651 aluminum alloy plate, tensile stress-strain curves
560
Tested at room temperature. Typical for plate thickness 6.35-50.80 mm (0.250-2.000 in.). Ramberg-Osgood parameter: n(longitudinal, tension) = 30; n(long transverse, tension) = 19. UNS A92014
LOngitudin~1"""
Long transverse
60
20
/
/
Source: MIL-HDBK-5H, 1 Dec 1998 ro
o..
::i:
280
V 2
4
420
140
6 Strain, 0.001 in.lin.
8
10
uf
~
316/Wrought Aluminum (WA)
WA.029 2014-T651 aluminum alloy plate, compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
8oFo----~1r4----~28~----~42~----~56L---~T_----~M560 LT, compression
Tested at room temperature. Test direction: L, longitudinal; LT, long transverse. Typical for plate thickness 6.35-50.80 mm (0.250-2.000 in.). Ramberg-Osgood parameter: n(L, compression) = 15; n(LT, compression) = 18. UNSA92014 Source: MIL-HDBK-5H, 1 Dec 1998
20~----~----_1------+_----_+------+__+--~140
°0L-----~2------~4------~6------~8------1~0--L-~1;
Strain, 0.001 in./in. 6 Compressive tangent modulus, 10 psi
r- --
80
70
f.---
60
LOngit~n~_ t---
.,-Long transverse
x
560
WA.030 2014-T651X aluminum alloy extrusion, tensile stress-strain curve (full range)
490
Tested at room temperature. Typical for extrusion thickness 12.70-19.025 mm (0.500-0.749 in.). UNS A92014
420
Source: MIL-HDBK-5H, 1 Dec 1998
50
350
gf 40
280
30
210
20
140
10
70
'"
~
[L
::¡;
~ m
rñ
'" ~
m
o
O
0.02
0.04
0.06
0.08
Strain, in./in.
0.10
0.12
o
0.14
Wrought Aluminum (WA)/317
WA.031 2014-T652 aluminum alloy forging, tensile stress-strain curves (full range)
490
70 Longitudinal
60
{
~
-==- --"'x' . . . . . . .....
~
Long transverse :---
Source: MIL-HDBK-5H, 1 Dec 1998
50
350
'00 40
280
'"!Ji
~
:::; !Ji
~
ro
Tested at room temperature. Typical. UNS A92014
420
\
30
210
20
140
10
70
0.02
0.04
0.06
0.08
0.10
0.12
ro~
o
0.14
Strain, in.lin.
WA.032 2014-T652 aluminum alloy hand forging, tensile and compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
O
14
28
42
56
70
84
8or-----.------,------~----~----~-------560
Tested at room temperature. Test direction: L, longitudinal; LT, long transverse; ST, short transverse. Typical for forging thickness 50.825-76.20 mm (2.001-3.000 in.). Ramberg-Osgood parameter: n(L, tension) = 18; n(LT, tension) = 18; n(ST, tension) = 13; n(L, compression) = 17; n(LT, compression) = 18; n(ST, compression) = 22. UNSA92014
~
:i ~
&.
:::; 40 I------f----Hr----t_--_+--__I-+-__J 280
:i
ro~
00
201---~--_+---t_--_+--__I-+-__J140
"---------'2-----...L4------.L6------8L------110---'------'120 Strain, 0.001 in.lin. 6 Compressive tangent modulus, 10 psi
Source: MIL-HDBK-5H, 1 Dec 1998
318/Wrought Aluminum (WA)
WA.033 2017-T4 aluminum alloy rolled and drawn rod, tensile stress-strain curves 80 True 70
./
60
]1 50
~
tl
40
~
f
'c;; e
30
20
10
f
./"
I
!
0.04
50
I
O
0.06
--
0.08 0.10 Strain, in./in.
0.12
/
Y
0.14
l'
~
I
/f
~
O O
:
280
210
Nominal
'c;; e ~ 40
/ V
Yield strength
350
Aleoa, Aluminum Research Laboratory, New Kensington, PA 140
1
0.02
ID
10
420
I I I I I I
70
ui U)
20
\
/ f
Yield strenglh
I I I
0.16
630
WA.034 X2020-T6 aluminum alloy extruded bar, tensile stress-strain curves
560
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essentially identical for both the true and nominal curves. Test specimen diam, 12.7 mm (0.500 in.). Gage length: 50.8 mm (2 in.). Nominal tensile strength, 552 MPa (80.0 ksi). True tensile strength, 586 MPa (85.0 ksi). Nominal yield strength (0.2% offset), 514 MPa (74.5 ksi). Elongation (in 50.8 mm, or 2 in.), 8.5%. Reduction of area, 16%. True strain at maximum load, 6.0%. A log-log plot of the stress-strain curve would yield a slope (n) of 0.06 in the area of uniform plastic deformation.
490
420
I I
.
a..
:2 350 ui U)
I
~
tí 280 ~ U) e ~ 210
140
1
2
o
0.18
70
0.02
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essentially identical for both the true and nominal curves. YS, yield strength. Test specimen diam, 12.7 mm (0.5 in.). Gage 1ength: 203.2 mm (8 in.). Nominal tensile strength, 459 MPa (66.5 ksi). True tensile strength, 514 MPa (74.5 ksi). Nominal yield strength (0.2% offset), 302 MPa (43.8 ksi). Elongation (in 50.8 mm, or 2 in.), 16.7%. Reduction of area, 38%. True strain at maximum load, 14.8%. UNS A92017
I I
r
30
'\
!
~ 60
tl
490
Nominal
¡,....o-¡,....o-
I I I I I I
Tru.:..-
70
H-
I
90
80
l.--
~~....o-
~
~
~
~
V
560
0.04
0.06 0.08 Slrain, in.lin. 6 8 4 Strain, 0.001 in.lin.
o
0.10
0.12
10
12
Source: Aleoa, Aluminum Research Laboratory, New Kensington, PA
Wrought Aluminum (WA)/319
WA.035 2024-T3 and 2024-T4 aluminum alloy, ciad 2024, rolled bar, extrusion, and sheet, complete tensile stress-strain curves
700
100 1
1
"\ 118 in. (3.175 mm) thick extrusion, T4 condition
80
.¡¡;
60
-"
ui
'"~
éií
40
f
~ V
~
\
Test direction: longitudinal. Composition: AI-4.5Cu1.5Mg-O.6Mn. UNS A92024
560
' \ Sheet, T3 condition
-
420
Rolled bar, T4 condition
rf.
Souree: AJ. MeEvily, Jr., W. Illig, and R.F. Rardrath, "Statie Strength of Aluminum-Alloy Speeimens Containing Fatigue Craeks," NACA TN3816, Oet 1956. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3203, CINDASlPurdue University, 1995, p 15
:2 ui
280
20
~
140
2.5
5
7.1>
10 12.5 Strain, %
15
17.5
o
20
WA.036 2024-T3 aluminum alloy, true-stress, truestrain curves
100.-------------,---·----------,--------------,700
Composition: AI-4.5Cu-I.5Mg-O.6Mn. UNS A92024 50
350
.¡¡;
a. :2
-'"
ui
ui
'"
~
'"
~
Q)
:::J
t=
Souree: G.W. Brown and R. Ikegami, The Fatigue of Aluminum Alloys Subjeeted to Random Loading, Exp. Mech., Vol lO, Aug 1970, p 321-327. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3203, CINDASlPurdue University, 1995, p 16
20
140
Q)
2
1-
10~----------~------------_+------------_170
5L---L---~--~---_L---~--~--~--
10- 3
10- 2
10- 1 True strain, in.lin.
___ L_ __J35 1
320/Wrought Aluminum (WA)
70
~
60
~~
50
.¡¡¡
40
/
"'g" 1!
1ií 30
20
10
/
V
Short transverse
'/
420
Composition: Al-4.5Cu-l.5Mg-O.6Mn. UNS A92024
350
Source: D.J. Brownhill et al., "Mechanical Properties, Including Fracture Toughness and Fatigue, COITosion Characteristics and FatigueCrack Propagation Rates of Stress-Relieved Aluminum Hand Forgings," AFML-TR-70-1O, Aleoa Research Laboratories, Feb 1970. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3203, CINDAS/ Purdue University, 1995, p 16
280 rf. ::2:
~
210 1ií
V
140
70
2
WA.037 2024-T852 aluminum alloy hand forgings, tensile stress-strain curves
490
Lon~itudinal
____ ___ Tran~verse
4
6 8 Strain, 0.001 in./in.
10
o
12
Wrought Aluminum (WA)/321
WA.038 2024-T6 and 2024-T852 aluminum alloy forgings, effects of heat treatment on tensile properties
70 r-------,--------,-------,-------,--------, 490
'iu __-+---
Test direction: short transverse. Composition: Al-4.5Cu1.5Mg-O.6Mn. UNS A92024
65~--~~~------~------~~~--~~----~455
~
~
::¡¡:
~ 60 1-------,;9--------__/-------_j_------___1I---------1 420 =-
~ 00
~
~ 55~------+_------__/-------_j_------___1---------1385
50L-------~------~-------~------~L-----~350
6
~
1--;--~
2
4 6 Cold reduction, %
8
10
Source: J.H. Hull and SJ. Erwin, How Deformation Affects the Mechanical Properties of Aluminum Forgings, Met. Eng. Quart., Vol 12, Nov 1972, P 1-6. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3203, CINDASlPurdue University, 1995, p 16
322/Wrought Aluminum (WA)
Exposure temperature,
oc
8o-r15---------,95----------2or5---------3,1-5--------4~2~60
WA.039 2024-T4 aluminum alloy, effects of exposure to elevated temperature on tensile properties
Tested at room temperature. Composition: Al-4.5Cu1.6Mg-O.6Mn. UNS A92024 Source: "2024-T4 Products," AJeoa Research Laboratory Data Sheet, Sept 1957. As pub1ished in Aerospace Structural Metals Handbook, Vol 3, Code 3203, CINDAS/Purdue University, 1995, p 16
• y"
h
0100 h '" 1000 h 20L---------~---------L--------~--------~140
60,---------,----------,---------,----------¡420
OL---------L---------L---------L-------~O
n· ·bbJ::: O
200
400
Exposure temperature, °F
600
I 800
Wrought Aluminum (WA)/323
Exposure lemperalure,
95
• '00
""'- 60
" \
o,
\
~
Cií
*
Tested at room temperature. Composition: AI-4.5Cu1.5Mg-O.6Mn. UNS A92024
E 40
~
Tesled al room lemperalure
I
• 1/2 h 0100 h .1000 h
8: 420
o,
'"
e
~
-
Cií al
280 1ií
E
......... i'- ___o
I
20
:::?!_
~ .c
\
\\
e
:5
WA.040 2024-T81 aluminum alloy, effecls of exposure to elevated temperature on tensile properties
315
.\ ~ \
~ .c
oc
205
:5
140
80r----------.----------.-----------~----~--_,560
60
420
'"
c..
'00
:::?!
"'" .--:ce
~
!:!:.
.c
.c
g> 40
280
~
g> ~
Cií
Cií
"O
"O
a;
a;
:;:
:;: 20
140
O~--------~----------~----------L----------"O
1:"----1"-~I"" J;J;~---o---__ -~ I O
200
400
Exposure lemperalure, °F
600
800
Source: "2024-T81," Aleoa Research Laboratory Data Sheet, July 1957. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3203, CINDASlPurdue University, 1995, p 17
324/Wrought Aluminum (WA)
Exposure temperature,
95
oc
205
WA.041 2024-T86 aluminum alloy, effeds of exposure to elevated temperature on tensile properties
315
.... ~
~
~
~
~ 60~--------1--------1~+------*~----------1420 ~ ~ ~
~
~ e ~
~
W ~
W
.~ 40
280 ~
5
5
Tested at ro9m temperature
• Y:. h O 100 h ... 1000 h 2oL---------~----------~--------~--------~140
80,---------,----------,---------,----------,560
420
60
o..'"
~
:2
~
>-
>-
~
~
~
~
g> 40 ~
280
g> ~
"O
"O
:;:
:;:
Cii
Cii
140
20
0L---------L---------L---------L-------~0
flL----' O
L--..-l.L~---p~--~I
200
400
Exposure temperature, °F
600
800
Tested at room temperature. Composition: Al-4.5Cu1.5Mg-O.6Mn. UNS A92024 Source: "2024-T86," Aleoa Research Laboratory Data Sheet, July 1957. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3203, CINDAS/Purdue University, 1995, p 17
Wrought Aluminum (WA)/325
80
LO~git~al
70
60 50 ·00
"'ui" rn ~
I
40
1Short transverse
20
/
490
Composition: AI-4.5Cu-l.5Mg-0.6Mn. UNS A92024
420 350
o..'"
Source: DJ. Brownhill et al., "Mechanical Properties, Inc1uding Fracture Toughness and Fatigue, Corrosion Characteristics and FatigueCrack Propagation Rates of Stress-Relieved Aluminum Hand Forgings," AFML-TR-70-1O, Aleoa Research Laboratories, Feb 1970. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3203, CINDAS/ Purdue University, 1995, p 17
;:¡;
280 ui
~
Ci.í
v
30
WA.042 2024-T852 aluminum allay hand fargings, campressive stress-strain curves
Transverse
/
Ci.í
10
/ V
/
~
560
210 140
/
70
2
4
6 8 Strain, 0.001 in./in.
10
12
WA.043 2024-T3, 2024-T6, 2024-T81, and 2024-T86 aluminum allay sheet and plate, tensile stress-strain curves
80r---r---r-~---,---,---,---,---.---.---.---,560
T86 70
490
Tested at various temperatures; 30 min exposure. RT, room temperature; 93 oC (200 °P); 100 oC (212 °P); 150 oC (300 °P); 205 oC (400 °P); 260 oC (500 °P); 315 oC (600 °P); 363 oC (685 °P). Composition: AI4.5Cu-l.5Mg-0.6Mn. UNS A92024
60 50
350
l1.
;:¡;
280 ui
~
30
210
20
140
10
70
Strain, 0.001 in./in.
Source: "Tensile Stress-Strain Curves for 2024," Alcoa Research Laboratories Data Sheets, Oct and May 1957. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3203, CINDAS/ Purdue University, 1995, p 18
326/Wrought Aluminum (WA)
WA.044 2024-T4 aluminum alloy bar and extrusions, tensile stress-strain curves
60 . - - - - - , - - - - - - - r - - - - - , - - - - - , - - - - - - , 4 2 0 Room temperature
Tested at various temperatures. Extrusion dimensions: 6.35 X 38.1 mm (0.25 x 1.5 in.). Composition: AI-4.5Cu1.5Mg-0.6Mn. UNS A92024
I
50 I-----t----+------:;;>"""-::;t;.--'F 200°F (93 oC)
350
300 °F (149 oC) 400°F (204 OC)
Source: S.A. Gordon, R. Simon, and W.P. Achbach, "MaterialsProperty-Design Criteria for Metals," WADC TR 55-150, Pt 4, Oct 1956. As published in Aerospace Structural Metals Handbook, Vo13, Code 3203, CINDAS/Purdue University, 1995, p 19
40 .¡¡;
""ui
~
30
20
1-----,#7~---r---~----+___---~140
600°F (316 oC) 10~~~~+_---~---~----t_---~70
°0L----~2-------4L-------~6--------~8------~1~
Strain, 0.001 in.lin.
70
60
50
'00
""ui
40
---r------
./
r;¿ .,.
te~perature
¡..--
r-
~
-
-
Room
~
WA.045 2024-T4 aluminum alloy sheet, complete tensile stress-strain curves
Tested at various temperatures. Test direction: transverse. Thickness: 1.626 mm (0.064 in.). Composition: AI4.5Cu-l.5Mg-0.6Mn. UNS A92024
420 300°F (149 oC)
400°F (206 oC)
t--
490
--!---...
350
280
g: ;¡;
~O
°F(260 OC)
¡i ~
210 éñ
éñ 30
20
140
10
70
0.02
0.04
0.06 Strain, in.lin.
0.08
0.10
o
0.12
Source: "Correlation of Infonnation Available on the Fabrication of Aluminum Alloys, Section IV," Case Institute Final Report to Nat. Def. Res. Comm., 15 Sept 1944. As published in Aerospace Structural Metals Handbook, Vo13, Code 3203, CINDAS/Purdue University, 1995, p 19
Wrought Aluminum (WA)/327
WA.046 2024-T3, 2024-T4, and 2024-T351 aluminum alloy sheet and plate, effects of temperature on tensile properties
Temperature, ·C
-15
-130
100-240
~ ~~
...
.... ;::: ......
.::-
--... -
95
205
315
Tested at -195 to 370 oC (-320 to 700°F) after 10,000 h exposure. Composition: Al-4.5Cu-l.5Mg-lMn. UNSA92024
Ftu ~~ ...
.... 1-1== Ft y
~
Source: "Aluminum Standards and Data," The Aluminum Association, 6th ed., March 1979. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3203, CINDASlPurdue University, 1995, p 19
~~ ,~
'~
• Sheet, T3 '" Plata, T4 and T352
'~
o
~
o
120
/
. ~I)O
-200
o
-.- / ' 200 Temperatura, °F
~
400
/ 600
800
328/Wrought Aluminum (WA)
WA.047 2024-T6 aluminum alloy, isochronous stress-strain curves in tension
6or------r-----,------,-----~------r_----,420
Shorttime
---
........
Tested at 150 oC (300 °P) (top) and 205 oC (400 °P) (bottom). Composition: Al-4.5Cu-l.5Mg-IMn. UNSA92024
50~----~----_i----~~~~----~~--__t~~~350 ;'
~
;'
40r------r----~+_~~-T--~~~~~~------~280
~
~
gf 30 1---------++-----/----J,L---F--+....."------+--------1-------l210 ~
:2
w
~
00
10r-~~-+------+_-----+------~----~------~70
o
O
2
4
6 8 Strain, 0.001 in./in.
10
0 12
420
60
350
50 Short time
... ........ ----
40 ;'
~
~
280
;'
'c;; -'"
Jl
al
a.
;'
:2
;'
30
210
~
(/)
100 h 140
20 1000 h
70
10
O O
2
4
6 Strain, 0.001 in./in.
8
10
O
12
Source: "Isochronous Stress-Strain Curves for Several Heat-Treated Wrought Aluminum Alloys at 300 and 400 F," Aleoa Research Laboratories, 29 April 1958. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3203, CINDASlPurdue University, 1995, p 24
Wrought Aluminum (WA)/329
-
60
--
WA.0482024-T81 aluminum alloy, isochronous stress-strain curves in tension
420
50
350
40
280
Tested at 150 oC (300 °P) (top) and 205 oC (400 °P) (bottom). Composition: Al-4.5Cu-l.5Mg-lMn. UNSA92024
ro
.c;;
Q.
::¡¡;
-'"
gf 30
210 tñ (/)
~
~
é'i5
(f)
140
20
10~~~~----~r-----~----~------+-----~70
2
4
6
8
10
Strain, 0.001 in.lin .
60
.------,------,-~--_r----~r_----,420
--
50~-----+_----~------+_----_+------~~--4350
Short ,,time .,/ .,/
~----~----~~----~~--~------+---~~280
6 Strain, 0.001 in.lin.
8
10
Source: "Isochronous Stress-Strain Curves for Several Heat-Treated Wrought Aluminum Alloys at 300 and 400 F," Alcoa Research Laboratories, 29 April 1958. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3203, CINDAS/Purdue University, 1995, p 25
330/Wrought Aluminum (WA)
WA.049 2024-T86 aluminum alloy, isochronous stress-strain curves in tension
490
70
--
60
Tested at 150 oC (300°F) (top) and 205 oC (400°F) (bottom). Composition: AI-4.5Cu-l.5Mg-lMn. UNS A92024
420
350
50
280 ¡f ::;;
'00 40
'"rñ '"~
rñ
U5 30
210
20
140
10
70
O O
2
4
6
8
10
'"~
U5
O
12
Strain, 0.001 in./in.
70
490
60
420
50
350
280 ¡f ::;;
'00 40
'"rñ
'" ~
(J)
rñ
30
210
20
140
10
70
2
4
6 8 Strain, 0.001 in./in.
10
O
12
'"~
U5
Source: "Isochronous Stress-Strain Curves for Several Heat-Treated Wrought Aluminum Alloys at 300 and 400 F," Alcoa Research Laboratories, 29 April 1958. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3203, CINDASlPurdue University, 1995, P 25
Wrought Aluminum (WA)/331
80 True
70 60 ~
'"~
50
~
I
üí
~ 40 e
/'
V L,..--o-"
--
,...,.... v
v ~
-o-'
m
o..
vi
~~"oOO"
~
Yield strength
280 'iij J!1 e
~
210 140
/¡
10
o
O
o
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essentially identical for both the true and nominal curves. YS, yield strength. Test specimen thickness, 12.7 mm (0.5 in.). Gage length: 44.45 mm (1.75 in.). Nominal tensile strength, 464 MPa (67.3 ksi). True tensile strength, 546 MPa (79.2 ksi). Nominal yield strength (0.2% offset), 314 MPa (45.5 ksi). Elongation (in 50.8 mm, or 2 in.), 20.0%. Reduction of area, 27%. True strain at maximum load, 16.3%. A log-log plot of the stress-strain curve would yield a slope (n) of 0.21 in the area of uniform plastic deformation. UNS A92024
350 :2
~
20
490 420
I
30
WA.050 2024-13, aluminum alloy plate, tensile stress-strain curves
Nominal
~
/
~
560
70
0.02 0.04 0.06 0.08 0.10 0.12
Souree: Alcoa, Aluminum Researeh Laboratory, New Kensington, PA, Aug 1954
O
0.14 0.16 0.180.20 0.22
Strain, in.lin. 2
4
8
6
10
12
14
16
18
20
22
Strain, 0.001 in.lin.
Compressive tangent modulus, GPa
8oor------~14~----2~8~----~4~2----~5T6~--~7TO~--~8~4 560
60r-----~----~,-----1_----~------+_----~420
L, tension
LT, compression
--l---,~-I
LT, tension ::----I--L, c~mpression
20r-----~----~------4_----_+------+_~--_4140
2
6 8 10 Strain, 0.001 in.lin~ 6 Compressive tangent modulus, 10 psi 4
WA.051 2024-13 aluminum alloy sheet, tensile and compressive stress-strain and compressive tangent modulus curves Tested at room temperature. Test direction: L, longitudinal; LT, long transverse. Typical for sheet thickness ~6.325 mm (~0.249 in.). Ramberg-Osgood parameter: n(L, tension) = 50; n(LT, tension) = 12; n(L, compression) = 15; n(LT, compression) = 11. UNS A92024 Souree: MIL-HDBK-5H, 1 Dee 1998
332/Wrought Aluminum (WA)
WA.052 2024-T3 aluminum alloy sheet, tensile and compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
o
14 28 42 56 70 84 80.-----,------,------,------,------,-----,560
Tested at room temperature. Test direction: L, longitudinal; LT, long transverse. Typical for sheet thickness 1.60-6.325 mm (0.063-0.249 in.). Ramberg-Osgood parameter: n(L, tension) = 50; n(LT, tension) = 15; n(L, compression) = 13; n(LT, compression) = 19. UNSA92024
60~----~----~------~-----+------~----~420
LT, compression
--+--:::::I:t:::::='" I L, compression g 40 L~~~==::=:j¿~~~§;;:~~~~L~~ite~n:s~io~n~ 280 :-ro
gj
!l..
~ w
m w
Source: MIL-HDBK-5H, 1 Dec 1998
20~----~----~------~-----+------~----~140
\ \
/
/
, I I
2
10 6 8 Strain, 0.001 in.lin. 6 Compressive tangent modulus, 10 psi 4
WA.053 2024-T351 aluminum alloy, ciad 2024T351, plate, tensile and compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
14
28
42
56
70
84
r------r-----,------,------,------r-----~420
280
40
ro
.¡¡;
!l..
-'"
g
~
Tested at room temperature. Test direction: L, longitudinal; LT, long transverse. Typical for plate thickness 12.70-50.80 mm (0.500-2.000 in.). Ramberg-Osgood parameter: n(L, tension) = 42; n(LT, tension) = 9.0; n(L, compression) = 9.0; n(LT, compression) = 12. UNS A92024 ~
30
210 .; f/) ~ en
20
140
10~~--~----~------+_----_+------~_r--~70
Strain, 0.001 in.lin. 6 Compressive tangent modulus, 10 psi
Source: MIL-HDBK-5H, 1 Dec 1998
Wrought Aluminum (WA)/333
WA.054 2024-T351X aluminum alloy extrusion, compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
14 28 42 56 70 84 ,------r-----,------,------,------,------,42o
Tested at room temperature. Test direction: L, longitudinal; LT, long transverse. Typical for extrusion thickness 6.35-19.02 mm (0.250-0.749 in.). RambergOsgood parameter: n(L, compression) = 16; n(LT, compression) = 17. UNS A92024
280
Source: MIL-HDBK-5H, 1 Dec 1998
'iñ
ro eL.
!Ji
210 !Ji
.><
~
~'"
'"~
UJ
Cií 140
L------2L-----~4~----~6------~8------1~0--~~1~
Strain, 0.001 in.lin. 6 Compressive tangent modulus, 10 psi
334/Wrought Aluminum (WA)
90
630
WA.055 2024-T36 aluminum alloy extruded plate, tensile stress-strain curves
80
560
Upper curve test direction, longitudinal; lower curve test direction, transverse. The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essentially identical for both the true and nominal curves. YS, yield strength. Test specimen thickness, 12.7 mm (0.5 in.). Gage length: 44.45 mm (1.75 in.). Nominal longitudinal values: Tensile strength, 496 MPa (72.0 ksi). True tensile strength, 546 MPa (79.2 ksi). Nominal yield strength (0.2% offset), 450 MPa (65.2 ksi). Elongation (in 50.8 mm, or 2 in.), 13.2%. Reduction of area, 20%. True strain at maximum load, 9.2%. A log-log plot of the stress-strain curve would yield a slope (n) of 0.10 in the area of uniforrn plastic deforrnation. UNS A92024
70
r
60
490
l..--o-"
t,.-o"""
420
I I
V
'~" 1ñ
~ 40
~
30
/ V
O
_L
I I I
V
I I I
I I I
I I I
O
0.02
0.04
O
2
4
&.
:::¡; 350 "," ti)
I I
I
!!!
10
Yield strength
I
~
20
I I
0.06 0.08 Strain, in.lin.
6
i
280 ~
ti)
c:::
~ 210
140
70
Source: Alcoa, Aluminum Research Laboratory, New Kensington, PA
o
0.10
0.12
0.14
10
12
14
8
Strain, 0.001 in.lin.
630
90
80
..........: ~
/ !
60 .¡¡;
""
~
r.J-
/
V"
!,..o-o-<>""
..ro.
1ñ
~ .¡¡; 40
30
O O O
:::¡; 350
~
I I
280 ~
!!!
I I
V
I V
ca
O-
I
/
c:::
~
420
Yield strength I
V
'"~
490
I
-'"
10
560
~
70
20
-
~
~ 210
I I I
140
I I I
70
I I 1
0.02
0.04
2
4
0.06 0.08 Strain, in.lin. 6 8 Strain, 0.001 in.lin.
o
0.10
0.12
0.14
10
12
14
Wrought Aluminum (WA)/335
14
Compressive tangent modulus, GPa 28 42 56
50
I
40
20
10
V
---"'" ? K ---1/
L, compression
__
70
WA.056 2024-T4 aluminum alloy rolled bar, rod, and shapes, tensile and compressive stress-strain and compressive tangent modulus curves
L, tension
350
Tested at room temperature. Test direction: L, longitudinal. Typical for thickness ::;;139.70 mm (::;;5.500 in.). Ramberg-Osgood parameter: n(L, tension) = 50; n(L, compression) = 10. UNS A92024
280
Source: MIL-HDBK-5H, 1 Dec 1998
I
1--- L, compression
~
:2
~
210
i
f\
(f)
140
/
V
70
2
6 8 Strain, 0.001 in.lin. 6 Compressive tangent modulus, 10 psi 4
10
WA.057 2024-T42 aluminum alloy, ciad 2024-T42, plate, tensile and compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa O 14 28 42 56 70 84 50r-·-----,------r-----,------,------,------,350 L and LT, compression __,,::::::::::::=F~ L, tension LT, tension
Tested at room temperature. Test direction: L, longitudinal; LT, long transverse. Typical for plate thickness 12.70-25.40 mm (0.500-1.000 in.). Ramberg-Osgood parameter: n(L, tension) = 17; n(LT, tension) = 16; n(L, compression) = 19; n(LT, compression) = 19. UNSA92024
40r------r----~~~~~----_4------1_----~280
.¡¡;
30
210
a.'"
"'
:2
~
!J)
!J)
Cñ
20
140
10r--f---r----~-------~-----+------+r-----470
°O~----~-----L----~------~-----U----~o
2
4
6 8 10 Strain, 0.001 in.lin. 6 Compressive tangent modulus, 10 psi
12
~
Source: MIL-HDBK-5H, 1 Dec 1998
336/Wrought Aluminum (WA)
WA.058 2024-T42 aluminum altoy extrusion, compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
o
14
28
42
56
70
84
6or-----,-----~----_,~--~T_----~----~420
Tested at room temperature. Test direction: L, longitudinal; LT, long transverse. Typical for extrusion thickness :2:38.10 mm (:2:1.500 in.). Ramberg-Osgood parameter: n(L, compression) = 32; n(LT, compression) = 19. UNSA92024
350
280
40
Source: MIL-HDBK-5H, 1 Dec 1998 ro
·00 -'"
o.. ::¡;
gf 30
210 ui Ul
~
2!
en
1i5 20
140
10
70
6
4
2
10
8
Strain, 0.001 in.lin. 6 Compressive tangent modulus, 10 psi
WA.059 2024-T42 aluminum altoy, ciad 2024-T42, sheet, compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
60 o
14
28
42
56
70
84
420
50
350
40
280
Tested at room temperature. Typical for sheet thickness 1.829-6.325 mm (0.072-0.249 in.). Ramberg-Osgood parameter: n(longitudinal, compression) = 17; n(long transverse, compression) = 17. TensiIe yield strength: Iongitudinal, 324 MPa (47 ksi); long transverse, 317 MPa (46 ksi). UNS A92024 ro
o.. ::¡;
·00 -'"
210 oí
gf 30
'" ~
2!
1i5 20
140
10
70
2
4
6
8
Strain, 0.001 in./in. 6 Compressive tangent modulus, 10 psi
10
o 12
Source: MIL-HDBK-5H, 1 Dec 1998
Wrought Aluminum (WA)/337
Temperature, 'C
-15 100
40
150
205
260
315
370
425
WA.060 2024-T62 aluminum alloy (all products), effect of temperature on ultimate tensile strength
Up to 10,000 h exposure. UNS A92024 Source: MIL-HDBK-5H, 1 Dec 1998
ooL----1Loo----2~00----3~0-0----4~0-0---5~OLO----60LO----70LO--~800 Temperature, °F
Temperature, 'C
-15
40
95
150
205
260
315
370
425
100r---~~~~---'----'-----'----r----r---~
WA.061 2024-T62 aluminum alloy (all products), effect of temperature on tensile yield strength
Up to 10,000 h exposure. UNS A92024 Source: MIL-HDBK-5H, 1 Dec 1998
°0L-·---10LO----2~00----3~O-O---4~O-O---5~O-O----60LO----70LO--~800 Temperature, °F
338/Wrought Aluminum (WA)
WA.062 2024-T62 aluminum alloy plate, tensile and compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
8oor-----,14r---~2,8~----4~2~--~5T6----~7rO----~84560
Tested at room temperature. Test direction: L, longitudinal; LT, long transverse. Typical for plate thickness 6.350-25.40 mm (0.250-1.000 in.). Ramberg-Osgood parameter: n(L, tension) = 28; n(LT, tension) = 24; n(L, compression) = 22; n(LT, compression) = 22. UNS A92024
L and LT, compression
60
tension 420 I~::--':~f::::~~~~~§~~~~~~Lr' LT, tension
~
&
Source: MIL-HDBK-5H, 1 Dec 1998
:¡;
gj' 40 j---------+------Ht'-------+------+------ft------j 280 '" ~ ~
w
00
20~----~----~------+_----_+------~----~140
2
~
-15
-::.::¡ 100
40
!:S.c ii
10 8 6 Strain, 0.001 in.lin. 6 Compressive tangent modulus, 10 psi 4
-
Temperature,
95
~
Ol
c:
~
~ .¡¡;
150
80
c:
E
260
315
370
425
,
~
Source: MIL-HDBK-5H, 1 Dec 1998
Yoh 2h 100 h
60
1000 h
Ol
c:
"fa Cll
-" ~
~
40
Cll
a. E .$ E o
e
a
20
Cll Ol
J!l c:
~
Cll
Il.
o o
100
200
300
400
WA.063 2024-T81, 2024-T851, 2024-T851O, and 2024-T8511 aluminum alloy (all products), effect of temperature on bearing ultimate strength
Up to 1000 h exposure. UNS A92024
10 h
.$
''§*
oc
205
500
Temperature, °F
600
700
800
Wrought Aluminum (WA)/339
--r-...... ~
WA.064 2024-T81, 2024-T851, 2024-T851O, and 2024-T8511 aluminum alloy (all products), effect of temperature on bearing yield strength
Temperature, oC
-15 100
40
95
150
205
\\
260
315
370
425
Up to 1000 h exposure. UNS A92024 Y:zh 2h
Source: MIL-HDBK-5H, 1 Dec 1998
10 h 100 h 1000 h
o
O
100
200
300
400
500
600
700
800
Temperature, °F
WA.065 2024-T851 aluminum alloy plate, tensile stress-strain curves
8or-.-----,-----,------,------,------,-----~560
Longitudinal, tension
Tested at room temperature. Test direction: L, longitudinal; LT, long transverse. Typical for plate thickness 6.350-25.40 mm (0.250-1.000 in.). Ramberg-Osgood parameter: n(L, tension) = 22, n(LT, tension) = 18. UNSA92024
60~--~~~~~~~-.~~~_4~~--+_~~~420
Source: MIL-HDBK-5H, 1 Dec 1998
~ gf 40
~
8:. ::a:
~~~-t--~~---Tlr___~~-+-~~__t~~~+_~~~ 280 ui
ro~
20~~~~~~~~~~-+---~_4~~~+_~~~140
°0~·----~2~----~4~----~6------~8------1~0----~1;
Strain, 0.001 in.lin.
340/Wrought Aluminum (WA)
WA.066 2024-T851 aluminum alloy plate, compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa 100
o
14
28
42
84
70
56
80
-
----... -'\ /
60
..><
rñ rJ)
g (f)
40
20
Tested at room temperature. Typical for plate thickness 6.350-25.40 mm (0.250-l.000 in.). Ramberg-Osgood parameter: n(L and LT, compression) = 17. UNS A92024
560
~;::::v/~ .¡¡;
700
V
/
2
Source: MIL-HDBK-5H, 1 Dec 1998
420
o..
::¡;
280
1 (f)
140
10 6 8 Strain, 0.001 in./in. 6 Compressive tangent modulus, 10 psi
4
90
80
-
o
12
630
WA.067 2024-T851 aluminum alloy sheet, tensile stress-strain curves (full range)
560
Tested at room temperature. Typical for sheet thickness 6.350-38.075 mm (0.250-l.499 in.). UNS A92024
490
Source: MIL-HDBK-5H, 1 Dec 1998
Longitudinal 70
60 .¡¡; ..><
r-
--C;g
tr~nsverse~
-
....
I'-"x 420
350 ~
50
rñ rJ)
:i
~
Ci5 40
280
30
210
20
140
10
70
O O
0.02
0.04
0.06 0.08 Strain, in./in.
0.10
0.12
o
0.14
g
(f)
Wrought Aluminum (WA)/341
80
~
~
70
]l 50
I
ui U>
Q)
~ 40
I
~ .¡¡; c:
30
20
10
I V
O O
210 ~
140
70
0.10
0.1~
10
12
560
f--",,-
""1
Ñominal
-'"
ui U>
Q)
~ 40 ~ .¡¡; c:
30
Source: Alcoa, Aluminum Research Laboratory, New Kensington, PA
0.06 0.08 Strain, inJin. 468 Strain, 0.001 inJin.
:/
.¡¡; 50
f
O
~
~ .¡¡; c:
0.04
~
f
: I I I
0.02
r-
00
:i
280
,
2
I
350 ~ ::lE
I I I
I I
60
10
Test directions: upper curve, longitudinal; lower curve, transverse. The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essentially identical for both the true and nominal curves. YS, yield strength. Test specimen thickness, 12.7 mm (0.5 in.). Gage length: 44.45 mm (1.75 in.). Nominal tensile strength, 517 MPa (75.0 ksi). True tensile strength, 534 MPa (77.5 ksi). Nominal yield strength (0.2% offset), 493 MPa (71.5 ksi). Elongation (in 50.8 mm, or 2 in.), 5.1 %. Reduction of area, 17% (top), 11 % (bottom). True strain at maximum load, 3.6%. A log-log plot of the stress-strain curve would yield a slope (n) of 0.06 in the area of uniform plastic deformation. UNSA92024
I I
Tr~
20
J1
.
80
~
490
420
I
V
O
70
,/
WA.068 2024-T86 aluminum alloy extruded plate, tensile stress strain curves
Yield strength
\
60
~
I
\
~
560
/
/
/
,rr
~
490
Yield strength
420
t
350 ~ ::lE
I I I
ui U>
I
280 ~
I I
~ .¡¡; c:
U>
210 ~
I I I I I I
140
70
I I 1
0.02 2
0.04
0.06 0.08 Strain, inJin. 468 Slrain, 0.001 inJin.
0.10
0.1~
10
12
342/Wrought Aluminum (WA)
Temperature, oc
-15
40
95
150
205
260
315
370
425
100r---~----'----'----'----'----'-----r---,
WA.0692024-T861 aluminum alloy sheet, effect of temperature on tensile ultimate strength
Up to 10,000 h exposure. UNS A92024 Source: MIL-HDBK-5H, 1 Dec 1998
'hh 10 h 100 h
100
200
300
400
500
600
700
800
Temperature, °F
Temperature, oC 1001~5~~4~0__~9T5__~1T50~__2TO~5___2,6_0___3,1_5___3,7_0__-.425
WA.070 2024-T861 aluminum alloy sheet, effect of temperature on tensile yield strength
Up to 10,000 h exposure. UNS A92024 Source: MIL-HDBK-5H, 1 Dec 1998
100
200
300
400
500
Temperature, °F
600
700
800
Wrought Aluminum (WA)/343
WA.071 2024-13 (top) and 2024-136 (bottom) aluminum alloy, dad sheet, tensile and compressive stress-strain curves
60~-------'-------'--------r-------r-------,420
40
T
~-------+-------~~~--~----~-+--~--~280 ~
~
Il..
::;;;
ui
'" ~
20
~----~~-------r------_r------_+------~140
~
--Tension - - - - Compression O~------~------~-------L-------L------~O
8o,-------,-------,--------,-------,-------,56o
L
~ ~ !!? 40
~------+__----___,I''-r------_r------_+------~
280
W
~ ::;;; ~ ~
W
20~----·-74_------4_------_r------_+------~140
~------L-------L---
2
4
____L __ _ _ _~_ _ _ _ _ _~O
6
Strain, 0.001 in.lin.
8
10
Test direction: L, longitudinal; T, transverse. Composition: AI-4.5Cu-I.5Mg-O.6Mn. UNS A92024 Source: LJ. Klinger and G. Sachs, Dependence of the Stress-Strain Curves of Cold Worked Metals upon the Testing Direction, J. Aer. Sci., Vol 15, 1948, p 151. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3204, CINDAS/Purdue University, 1995, p 3
344/Wrought Aluminum (WA)
420
60
¿
~
~ _'IJ
_....0........
.
• ..--:-
--
-
...
Composition: Al-4.5Cu-l.5Mg-O.6Mn. UNS A92024
-o
.00.063 in. "'0.081 in. "'0.091 in. -0.125 in.
Source: LJ. Klinger and G. Sachs, Dependence of lhe Stress-Strain Curves of Cold Worked Metals upon lhe Testing Direction, J. Aer. Sci., Vol 15, 1948, P 151. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3204, 1995, CINDASlPurdue University, p 4
(1.60 mm) (2.06 mm) (2.31 mm) (3.18 mm)
30
210
60
420 ro o.. :::;;
....... - Str~tching in 16ngitudinal d1irection o Stretching in transverse direction
~ ~
~
el
el
-0---
~ 50
;;; "O
-
..P- ....
ID
-
':;;'
........ .JJ
al
.~ 40
... •
'"c.~
E
8
WA.072 2024-T4 aluminum alloy, ciad 2024-T4, sheet, effect of stretching on tensile (top) and compressive (bottom) yield strengths
~
--
~
..;--
e
350 ~
~
~
J...
...
"O
ID
':;;'
~
280'¡¡¡ ~
c.
E
O
Ü
30
O
2
3 Stretch, %
4
5
6
210
Wrought Aluminum (WA)/345
80.--------.-------,-------~------_.------_,
560
WA.073 2024-T81 (top) and 2024-T86 (botlom) aluminum alloy, dad 2024-T81 and 2024-T86, sheet, tensile stress strain curves
RT
Tested at room and elevated temperature, 30 mino RT, room temperature. Sheet thickness 1.626 mm (0.064 in.). Composition: AI-4.5Cu-I.5Mg-0.6Mn. UNS A92024
420 200°F (93 OC)
a.
~
:2 ~ 40~------+-----_.~~----~------~------~ 280 cñ
'"
~
~
ro
(f)
20~----_.~~----~-------~------~------~
o
140
O
80
560
RT 60
420
a.
~ ~ 40
:2 280 cñ
'"~
~
ro 20
140
Strain. 0.001 inJin.
Source: D.E. Miller, "Determination of Physical Properties of Ferrous and Nonferrous Structural Sheet Materials at Elevated Temperatures," WADC AF TR No. 6517, Pt. 3, June 1954. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3204, CINDAS/Purdue University, 1995, p 4
346/Wrought Aluminum (WA)
.¡¡;
WA.074 2024-T3 aluminum alloy, ciad 2024-T3, sheet, tensile stress-strain curves
350
50
40
280
30
210
Tested at room and elevated temperatures 30 mino exposure at elevated temperature. Sheet thickness: 1.626 mm (0.064 in.). Composition: Al-4.5Cu-1.5Mg-0.6Mn. UNSA92024
C\l
Cl.
::;;
.><
ui ti)
'" ti)
~
~ 140
20
10~--~~~4---------~--------~--------~70
700'F (371 'C)
oOL---------~2----------4~--------~6--------~80
Strain,
0.001 in.lin.
Source: D.D. Doerr, "Determination of Physical Properties of Ferrous and Nonferrous Structural Sheet Materials at Elevated Temperatures," WADC AF TR No. 6517, Pt. 1, Supo 1, Feb 1953. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3204, CINDAS! Purdue University, 1995, p 4
Wrought Aluminum (WA)/347
WA.075 2024-n aluminum alloy, dad 2024-n, sheet, effect of exposure and test temperature on tensile properties
Temperalure, oc 80r15~ ________9~5__________ 20,5_________3,1_5________-,42~60
Sheet thickness: 1.626 mm (0.064 in.). Composition: A14.5Cu-1.5Mg-0.6Mn. UNS A92024 60 ~--~~~r;--------+---------+-------~420 ·00
"'" ....::.
:E
!:S""
!:S""
t
¡::
~
rf.
40 ~--------~--------~+_--~----_+--------__1280
~g '"
~
~
·00
¡::
·00
~ ~
~
¡::
Ji¡'"
"*E
5 20 ~--------~----------+_~~----~~------__11405 • Y2h o 100 h A 1000 h Y2h
•
O ~------~---------L---------L------~O
60 r---------r---------r---------~------__,420
~
!?40
D.. '" :E • ~·--------~---=~~--+_--------_+--------__1280!?
:g,
t
t:
t:
~
~
.., "tí
:!2
Qi .;;' ~
<1>
.;;'
·00 20
~--------~--------~~------~~----------1140~
'"t:
t:
¡!!1
¡!!1
OL---------~--------L---------L-------~O
Temperalure, °F
Source: Strength data: D.D. Doerr, "Deterrnination of Physical Properties of Ferrous and Nonferrous Structural Sheet Materials at Elevated Temperatures," WADC AF TR No. 6517, PI. 1, Sup. 1, Feb 1953. Elongation data: D.E. Miller, "Deterrnination of Physical Properties of Ferrous and Nonferrous Structural Sheet Materials at Elevated Temperatures," WADC AF TR No. 6517, PI. 3, lune 1954. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3204, CINDASlPurdue University, 1995, p 4. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3204, CINDASlPurdue U niversity, 1995, P 4
348/Wrought Aluminum (WA)
WA.076 2048-T851 aluminum alloy plate, tensile stress-strain curves
7o.------,------~----_,------~------~----~490
Room temperature
Test direction: longitudinal. Typical for plate thickness 76.2 mm (3 in.). Composition: AI-3.3Cu-1.5Mg-0.4Mn. UNSA92048
60~----~----~------+---~~----~~----~420
.¡¡;
40 1-----___+-------J'Ifc,tL---_+-----_I_---___j-----_I 280
~
~ ~
00
~ Uí 30
00
~~~~
Source: O.L. Deel, P.E. Ruff, and H. Mindlin, "Engineering Data on New Aerospace Structural Materials," Data Sheet F33615-72-C-1280, Technical Report AFML-TR-73-114, Battelle Memorial Institute, Columbus, OH, June 1973. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3223, CINDASlPurdue University, 1995, p 2
~
00
210
20~----~~--~------+_----_+------~----_I140
101--I.~---+-----+-----+-----I-------j------I70
oo~------L------L----~------~-----L----~O
2
4
6
8
10
12
Strain, 0.001 in./in.
WA.077 2048-T851 aluminum alloy plate, tensile stress-strain curves
70.------,------,------,------,------,------,490 Room temperature
Test direction: transverse. Typical for plate thickness 76.2 mm (3 in.). Composition: AI-3.3Cu-1.5Mg-0.4Mn. UNSA92048
60~----~----~------+_--~~~~~~~--_I420
350
.¡¡;
40
¡.......-----+------.JI--/----_+------+------~----_I
280
~
~ ~
00
~
~~~~
Uí 30
~ 210 Uí
20¡.......----~&L--~------+_----_+------+-----~140
10¡.......~~~----~~----+------+------+-----~70
~-----L2------~4------~6------~8~----~1LO----~1~ Strain, 0.001 in./in.
w
Source: O.L. Deel, P.E. Ruff, and H. Mindlin, "Engineering Data on New Aerospace Structural Materials," Data Sheet F33615-72-C-1280, Technical Report AFML-TR-73-114, Battelle Memorial Institute, Columbus, OH, June 1973. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3223, CINDAS/Purdue University, 1995, p 3
Wrought Aluminum (WA)/349
WA.078 2048-T851 aluminum alloy plate, compressive stress-strain curves
7o,-----,------,------,------,------,------, 490 RT
Test direction: transverse. RT, room temperature. Typical for pI ate thickness 76.2 mm (3 in.). Composition: AI3.3Cu-1.5Mg-04_Mn. UNS A92048
420
.¡;;
50~----_+------~~~~~~~_r-
350
40
280
I__-----+-----h~'----__+---__b~~-I__---_I
-'"
'"~
ro
~
::¡;
Source: O.L. Deel, P.E. Ruff, and H. Mindlin, "Engineering Data on New Aerospace Structural Metals," Data Sheet F33615-72-C-1280, Technical Report AFML-TR -73-114, Battelle Memorial Institute, June 1973. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3223, CINDASlPurdue University, 1995, p 4
30~----+~~~~--~-----r---~--~ 210
20~----~~---1------~-----+------+-----~
'"
ro~
140
10~~~_+----~----~-----_r------~----_170
L - _ _ _ _- L_ _ _ _ _ _
2
~
____
4
~
______
~
6
_ _ _ _ _ _L __ _ _ _
10
8
~O
12
Strain, 0.001 in.lin.
WA.079 2048-T851 aluminum alloy plate, compressive stress-strain curves
70,-------,------,------,------,-------,------,490 RT
Test direction: longitudinal. RT, room temperature. Typical for plate thickness 76.2 mm (3 in.). Composition: AI-3.3Cu-1.5Mg-04.Mn. UNS A92048
60~----_+-----~----~--_=~~-----~----_1420
350
~ 40~----_+----.H~----~-----_r-----~----~280~
en
::¡;
~
500 'F (260 'C) 30
210
20~----~---~------~----__+------+_----_4140
10r-~~_+-----+_----__+-----~-----~----~70
L------~-----L--
2
4
__
~
______
~
6 8 Strain, 0.001 in.lin.
____- L____
10
~O
12
~
ro
Source: O.L. Deel, P.E. Ruff, and H. Mindlin, "Engineering Data on New Aerospace Structural Metals," Data Sheet F33615-72-C-1280, Technical ReportAFML-TR-73-1l4, Battelle Memorial Institute, June 1973. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3223, CINDASlPurdue University, 1995, p 3
350/Wrought Aluminum (WA)
WA.080 2090-T83 aluminum alloy sheet, tensile stress-strain curves
700
100
Tested at room temperature. Typical for sheet thickness 1.016-6.325 mm (0.040-0.249 in.). Ramberg-Osgood parameter, n(longitudinal, tension) = 14; n(45°, tension) = 18; n(long transverse, tension) = 12. UNS A92090
560
80
Source: MIL-HDBK-5H, 1 Dec 1998 420
60 '00 -'" uf
ro ::;;: [L
uf
"' ~
"' ~ (/) 280
40
20~--__4------4------+------+------r-----~140
L-----~-----L----~------~----~----~1~
Strain, 0.001 in./in.
14
Compressive tangent modulus, GPa 28 42 56
WA.081 2090-T83 aluminum alloy sheet, compressive stress-strain and compressive tangent modulus curves
72
Tested at room temperature. Typical for sheet thickness 1.016-6.325 mm (0.040-0.249 in.). Ramberg-Osgood parameter, n(longitudinal, compression) = 20; n(45°, compression) = 30; n(1ong transverse, compression) = 19. UNS A92090 420
60 '00 -'" uf
Source: MIL-HDBK-5H, 1 Dec 1998 ro ::;;: [L
uf
"'~
"' ~ (/)
é'ií 280
40
20~--~~-----4------~-----T------T----r~140
2
4 Strain, 0.001 in./in. 6 Compressive tangent modulus, 10 psi
Wrought Aluminum (WA)/351
70
60
50
/
~
rñ 40
.~
30
~
20
10
I
/
V
/
350 ro
a.. 280 ::!:
rñ
~
!
Q)
210 '¡¡¡ <::
~
140
70
2
TypicaI for plate thickness 101.6 mm (4 in.). Composition: Al-4.4Cu-l.5Mg-O.6Mn. UNS A92124
Long transverse- 420
I
v
~
tí .!!1
I
r
--==
LOngitu~inal
/
WA.082 2124-T851 aluminum alloy plate, tensile stress-strain curves
490
4
6
8
Strain, 0.001 in./in.
10
12
o
14
Source: R.M. Hart, "Aluminum Alloy 2124 Plate," Aluminum Company of America, Aleoa TechnicaI Center, l April 1982. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3221, CINDAS/Purdue University, 1995, p 16
352/Wrought Aluminum (WA)
80 70
60
,/
/ V
·00
"": 50 (IJ
~
'iñ
.~ 40
.....-
-
E 30
o ü
20
10
o
Long transverse
490
Typical for plate thickness 101.6 mm (4 in.). Composition: Al-4.4Cu-O.5Mg-O.6Mn. UNS A92124
420
R.M. Hart, "Aluminum Alloy 2124 Plate," Aluminum Company of America, Alcoa Technical Center, 1 Apri11982. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3221, CINDAS/ Purdue University, 1995, p 17
8:
350 ::¡;
rJÍ
~
280 210
140
70
O
2
~
.2: (IJ
~
g-
o
Ü
/ 1/
O
WA.083 2124-T851 aluminum alloy plate, compressive stress-strain curves
LonQitudina!....
I (
(IJ (IJ
[!! a.
560
4
6
8
Strain, 0.001 in./in.
10
12
14
Wrought Aluminum (WA)/353
Temperature,
-15 80
38
~ 70
Fiu
!:S"''"
'I y
~
"C
o
"""'<
60
~
.,
'>,
"C
c:
os
50
!:S"'" .l!l os E
5""
1000 h exposure. Test direction: longitudinal. Plate thickness: 50.8 mm (2 in.). Composition: AI-4.4Cu-1.5Mg0.6Mn. UNS A92124
\\ \\
Oi
173 c: .l!l
2~60
149
""C
tc:
40
30
R.R. Cervay, "Temperature Effect on the Mechanical Properties of Aluminum Alloy 2124-T851," University of Dayton Research Institute, AFML-TR-75-208, 1975. As published in Aerospace Structural Metals Handbook, Vo13, Code 3221, CINDAS/Purdue University, 1995, p 17
!:S"'" 280
210
RA
.
(
-O
e v
100
WA.084 2124-T851 aluminum alloy plate, effect of elevated temperatures on retained roomtemperature tensile properties
oC
93
200 Exposure temperature, °F
o 300
400
*
,§ 5
354/Wrought Aluminum (WA)
WA.085 2124-T851 aluminum alloy plate, tensile stress-strain curves
8o.------r-----.------,------.------~----~560
Tested at room temperature. Typical for plate thickness 38.125-127.0 mm (1.501-5.000 in.). Ramberg-Osgood parameter, n(longitudinal, tension) = 22; n(long transverse, tension) = 16; n(short transverse, tension) = 13. UNSA92124 Source: MIL-HDBK-5H, 1 Dec 1998
~
li ~
~ ::;¡;
40 I-------+------A------+-~--_+------+_----_I 280 ui ~
w
w
20~----~----_4------+-~--_+------~----~140
L-----~2------~----~------L-----~----~1~
Strain, 0.001 in.lin.
WA.086 2124-T851 aluminum alloy plate, compressive stress-strain and compressive tangent modulus curves
80,-----,------,------,------.------,-----,560
Tested at room temperature. Typical for plate thickness 38.125-127.0 mm (1.501-5.000 in.). Ramberg-Osgood parameter, n(longitudinal, compression) = 14; n(long transverse, compression) = 19; n(short transverse, compression) = 17. UNS A92124 ~
li
~
40 ~----+_----_A------+_~--_+------t___t_--_j 280 ~
~ ro
~ ro
20~----~----_4------+_~--_+------t__+--~140
Strain, 0.001 in.lin.
Source: MIL-HDBK-5H, 1 Dec 1998
Wrought Aluminum (WA)/355
Tested at room and elevated temperatures. 100 h exposure. Composition: AI-6.3Cu-0.3Mn-0. 18Zr-0. lOV0.06Ti. UNS A92219
280
40
.¡¡;
WA.087 2219-T6 aluminum alloy forged rod, tensile stress-strain curves
350
50
210
30
o.. :;¡;
..1<
ui
W.P. Achbach, RJ. Favor, and W.S. Hyler, "Material-Property-Design Criteria for Metals," WADC TR 55-150, Part VI, Oct 1955. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3205, CINDAS/Purdue University, 1995, p 9
ui
'"~
ro
140
20
'" ~
10~--~~--+---------~--------~---------170
L---------~------~--------~--------~O
2
8
Strain, 0.001 in./in.
WA.088 2219-T62 aluminum alloy sheet, tensile stress-strain curves
100,-------,-------,-------,,-------,-------,700
---
Tested at low temperatures. Sheet thickness: 2.540 mm (0.100 in.). Composition: AI-6.3Cu-0.3Mn-0. 18Zr-0. lOV0.06Ti. UNS A92219
-423 'F (-253 'C)
80~----~~~----~-------4-------~-------1560
_---1-......=-'-k-320 'F (-196 'C)
60
~
o.. :;¡;
ui
'" ~ en
40
Hr------+-------+_------~------~------~280
20~------+-------+_------~------~------~140
- - Longitudinal - - - Transverse °OL------~------~------~L-------L-----~O
0.04
0.08 0.12 Strain, in./in.
0.16
0.20
1
P.R. Schwartzberg et al., Cryogenic Materials Data Handbook, MILTDR-64-280, Aug 1964, and Progress Report No. 1, Feb 1965. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3205, CINDAS/Purdue University, 1995, p 9
356/Wrought Aluminum (WA)
120
840
100
700 :"..
~~
80
/-
--~ r--.-.... F
--
~ ~-
~
-423
.......
WA.089 2219-T81 aluminum alloy sheet, tensile stress-strain curves Tested at low temperatures. Sheet thickness: 2.540 mm (0.100 in.). Composition: Al-6.3Cu-0.3Mn-0. 18Zr-0. lOV0.06Ti. UNS A92219
T
(-253 OC)
-320°F (-196 OC)
560
I
ro
Il.
-110°F (-79 OC)
ER. Schwartzberg et al., Cryogenic Materials Data Handbook, MILTDR-64-280, Aug 1964, and Progress Report No. 1, Feb 1965. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3205, CINDAS/Purdue University, 1995, p 9
:2
420 ui
RT
"'~
éi5 280
40
140
20 - - Longitudinal
- - -1 Transverse 0.04
0.08
0.16
0.12
o
0.20
Strain, in./in.
100
80
WA.090 2219-T87 aluminum alloy sheet, tensile stress-strain curves
840
120
/
~ P
~
~
~-
~
~~ .:r=
---
--
1
-~~" -423
-.....
"'
- -:~'
Tested at low temperatures. Sheet thickness: 2.540 mm (0.100 in.). Composition: Al-6.3Cu-0.3Mn-0.18Zr-0.lOV0.06Ti. UNS A92219
560
ER. Schwartzberg et al., Cryogenic Materials Data Handbook, MILTDR-64-280, Aug 1964, and Progress Report No. 1, Feb 1965. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3205, CINDAS/Purdue University, 1995, p 9
(-253 OC)
-320°F (-196 OC)
I
ro
Il.
-110°F (-79 OC)
:2
420 ui
RT
V
700
"'
~ 280
40
140
20 - - Longitudinal - - - Transverse 1
0.04
0.08
0.12
Strain, in./in.
0.16
o
0.20
Wrought Aluminum (WA)/357
WA.091 2219-T62 aluminum alloy sheet and plate, tensile and compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
5oor-·----~1r4----_,28------,42------5,6------7T2----__.M350 L and LT, compression
Tested at room temperature. Test direction: L, longitudinal; LT, long transverse. Typical for sheet and plate thickness 3.175.:...50.80 mm (0.125-2.000 in.). RambergOsgood parameter, n(L and LT, tension) = 13; n(L and LT, compression) = 16. UNS A92219
40~-----P~--~~~~~~--~------+------i280
.¡¡;
210
30
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-174
'"
a.
::;;
..><:
rñ
rñ
!/)
g
!/)
~
rn
140
20
ro
10~-+---~----~------~----~------+--+---170
Strain, 0.001 in.lin. Compressive tangent modulus, 1
rf psi
70
60
50
.¡¡; 40 ..><:
I
/
V
~
-
--
Tested at room temperature. Test direction: longitudinal and long transverse. Typical for sheet and plate thickness 3.175-50.80 mm (0.125-2.00 in.). UNS A92219
420 ... ....
X
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-175
350
280
gf
8:
::;;
gf
~
ro
WA.092 2219-T62 aluminum alloy sheet and plate, tensile stress-strain curve (full range)
490
30
210
20
140
10
70
0.02
0.04
0.06 Strain, in.lin.
0.08
0.10
o
0.12
ro~
358/Wrought Aluminum (WA)
70
60
50
/
v
~
...... Long
:.---
""' ......... ,,~
~ransverse
WA.093 2219-T81 aluminum alloy sheet and 2219T851 aluminum alloy pi ate, tensile stress-strain curves (full range)
490
420
Tested at room temperature. Typical for sheet and plate thickness 1.016-63.50 mm (0.040-2.50 in.). UNS A92219
LOngitudinal\ X
350
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-179
g¡
280
40
~
:2
ui (J)
ui
~
é'i5 30
210
20
140
10
70
0.02
0.04
0.06
0.08
0.10
~
o
0.12
Strain, in./in.
WA.094 2219-T81 aluminum alloy sheet and 2219T851 aluminum alloy plate, tensile and compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
800~____,1r4____~28~____4,2______5T6______7~2____-.8\60
L and LT, tension
ro
~
g¡
gf 40 1----+---~---+---_+----_p...A__-___l 280 gf ~
ru
~
00
~--~--~---+----+---+--r-~140
~----~2L-----~4------~6----~~8------1LO--L-~1P
Strain, 0.001 in./in. Compressive tangent modulus, 1
d' psi
Tested at room temperature. Test direction: L, longitudinal; LT, long transverse. Typical for sheet and plate thickness 1.016-63.50 mm (0.040-2.500 in.). RambergOsgood parameter, n(L and LT, tension) = 20; n(L, compression) = 19; n(LT, compression) = 21. UNSA92219 Source: MIL-HDBK-5H, 1 Dec 1998, p 3-178
Wrought Aluminum (WA)/359
WA.095 2219-T852 aluminum alloy hand forging, tensile stress-strain curves
560
80
60
Longitudinal Long \ransverse" Short transverse "'"
r
V V
420
~
Source: MIL-HDBK-5H, 1 Dec 1998
/1.
:2 280 ui Ul !!!
üí
20
2
4
Tested at room temperature. Typical for forging thickness 101.6-152.4 mm (4.001-6.000 in.). Ramberg-Osgood parameter, n(longitudinal, tension) = 22; n(long transverse, tension) = 17; n(short transverse, tension) = 14. UNSA92219
140
6
8
10
Strain, 0.001 in./in.
14
Compressive tangent modulus, GPa 56 28 42
WA.096 2219-T852 aluminum alloy hand forging, compressive stress-strain and compressive tangent modulus curves
72
60
Tested at room temperature. Test direction: L, longitudinal; LT, long transverse; ST, short transverse. Typical for forging thickness 101.652-152.40 mm (4.001-6.000 in.). Ramberg-Osgood parameter, n(L, compression) = 20; n(LT, compression) = 19; n(ST, compression) = 17. UNS A92219
420 LTand ST
~ ~dLT
~
~L
/1.
:2
¡r
20
I V 2
~~
280 ui
~
140
4
6 8 Strain, 0.001 in./in. Compressive tangent modulus, 106 psi
10
Source: MIL-HDBK-5H, 1 Dec 1998
360/Wrought Aluminum (WA)
80
70
/
Short transverse
60
50
,...
¿) ~ ~
Long transverse
560
WA.097 2219-T852 aluminum alloy hand forging, tensile stress-strain curVes (full range)
490
Tested at room temperature. Typical forging thickness for 152.4-203.2 mm (6.001-8.000 in.). UNS A92219
420
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-186
Longitudinal
--
r
350 ro
CI..
:::¡;
280 vi
~
30
210
20
140
10
70
0.02
0.04
0.06
0.08
0.10
o
0.12
Strain, inJin.
WA.098 2219-T87 aluminum alloy sheet and plate, tensile and compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
800~____~14r-____,28~____4,2______5T6______7~0____-.8~60
Tested at room temperature. Test direction: L, longitudinal; LT, long transverse. Typical for sheet and plate thickness 3.175-25.40 mm (0.125-1.000 in.). RambergOsgood parameter, n(L and LT, tension) = 14; n(L and LT, compression) = 14. UNS A92219 Source: MIL-HDBK-5H, 1 Dec 1998, p 3-189 ro
~ gf 40
E
I-------+---~-Ht------+-~--__+----~~..___--_j 280
~ gf m ~
W
20~----~--~~------+-~---+------~-r--~140
Strain, 0.001 inJin. 6 Compressive tangent modulus, 10 psi
Wrought Aluminum (WA)/361
80 70 60
-
~
-
_
-
Long transverse
-- ---:. ~ Longitudin;;¡-
/'
560
WA.099 2219-T87 aluminum alloy sheet and plate, tensile stress-strain curves (full range)
490
Tested at room temperature. Typical for sheet and plate thickness 3.175-25.40 mm (0.125-1.000 in.). UNSA92219
420
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-190
50
350 ca
a.
::2:
280 VJ ui !!!
Cñ 30
210
20
140
10
70
0.04
0.02
0.06
0.08
0.10
o
0.12
Strain, inJin.
80 70 60 50
r
v-:;- ~
,---
560
WA.100 2219-T87 aluminum alloy plate, tensile stress-strain curves (full range)
490
Tested at room temperature. Typical for plate thickness 40.64-101.6 mm (1.600-4.000 in.). UNS A92219
420
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-192
Long transverse
"Short transverse
350
y
ca
a.
] gf 40
::2:
280 VJui
~
!!!
(f)
Cñ 30
210
20
140
10
70
0.02
0.04
0.06
Strain, inJin.
0.08
362/Wrought Aluminum (WA)
Temperature, oc
-18
38
149
204
260
316
371
427
100r---~~--T----'----'---~----'-----r---,
WA.101 2519-T87 aluminum alloy plate, effect of temperature on ultimate tensile strength
Typical strength at temperature after various exposures up to 10,000 h. UNS A92519 Source: MIL-HDBK-5H, 1 Dec 1998
0L-__-L____L -__ ____J -_ __ J_ _ _ _ _ _ _ _ O 100 200 300 400 500 600 700 ~
~
~
__
~
800
Temperature, °F
Temperature, oC ñ.1.8.~~3~8~__9~3~__1~4~9__~2~0~4__~2~6~0__~31r6__~37,1____ 427
100 r
WA.102 2519-T87 aluminum alloy plate, effect of temperature on tensile yield strength curves
Typical strength at temperature after various exposures. UNSA92519 Source: MIL-HDBK-5H, 1 Dec 1998
OL-__- L____L -__~____J -_ __ J_ _ _ _~_ _~~--~ O 200 300 400 500 600 700 800 Temperature, °F
Wrought Aluminum (WA)/363
WA.103 2618 aluminum alloy ciad sheet, tensile stress-strain curves at elevated temperatures
60 r------,------,-----,------,------r-----, 420
Test direction: transverse. Heat treatment: 530 oC (986°F), 1 h, water quenched, flattened, and aged, 200 oC (392°F), 2 h, 1 h soak. Composition: AI-25Cu1.5Mg-1.2Ni-1.0Fe-0.2Si-0.1Ti. UNS A92618
350
ca
~
g¡
Source: "Hiduminium Elevated Temperature Alloys," High Duty Alloys Ltd., 1956, As published in Aerostructural Metals Handbook, Vol 3, Code 3213, CINDASlPurdue University, 1995, p 6
gf 30 f-------I-----IJ~fh?--_+_--___+---+_--__l 210 gf
~
~
20f----~~L--~--_+_--___+---+_--__l140
10~~~-~--___+---+_---+---+_--~70
L------2L.---~4~----~6------~8------1~0~--~1f
Strain, 0.001 in./in.
WA.104 2618-T61 aluminum alloy hand-forged billets, tensile stress-strain curves
60 r------,------,-------,-------,-------, 420
40r-----+----+_~~~7F~---+---__l280
Tested at elevated temperatures. Typical for several handforged billets: 76.2 x 165.1 mm (3 x 6Yo in.), 101.6 x 203.2 mm (4 x 8 in.), and 203.2 x 279.4 mm (8 x 11 in.). Composition: AI-2.5Cu-l.5Mg-1.2Ni-l.0Fe-0.2Si-0.l Ti. UNSA92618
~ &. ~ gf 30 J-----+----.H++_----_+_------I-------/21 O ui
Source: J.A. Lurnm, "Mechanical Properties of 2618 Aluminum Alloy," Technical Report AFML-TR-66-238, North American Aviation, Inc., July 1966. As published in Aerostructural Metals Handbook, Vol 3, Code 3213, CINDASfPurdue University, 1995, p 6
50f------+_---_+_---~-~~~---__l350
_
m
~
~
(J)
20J----~~---+_---_+_---~---~140
10r-~Y_-+----+_---~---~---~70
2
4
6
Strain, 0.001 in./in.
8
364/Wrought Aluminum (WA)
WA.l05 2618-T61 aluminum alloy forging, tensile properties at various temperatures
Temperature, oC
-240 100
-129
-18
93
204
316
427 700
Typical. Composition: AI-2.5Cu-1.5Mg-1.2Ni-1.0FeO.2Si-O.ITi. UNS A92618
.", '-
~
Source: Aluminum Standards and Data, 1968-69, The Alummum Association, 1st ed., April1968. As published in Aerostructural Metal, Handbook, Vol 3, Code 3213, CINDASlPurdue University, 1995, p 9 ~
---...... F
ty
""
~
~l\ I~ ~
o 120
E E 80
§. .~ N
.S e 40 O
15O>
/
e
o
/ V
280
.!E .¡¡; e
2
'*
140 E
'"5
o
V
¡j]
~oo
-200
o
200 Temperature, °F
400
600
':!:!
800
Wrought Aluminum (WA)/365
Temperature.
oc
WA.106 2618-T61 aluminum alloy forged bar, effect of elevated temperatures and exposure time on tensile properties
-18 93 204 316 427 8o,---------,---------_,----------,----------,56o Exposure
Composition: Al-2.5Cu-1.5Mg-l.2Ni-l.0Fe-O.2Si-O.l Ti. UNSA92618
.30 min ... 100 h ~ 60~--------~~------~----------4_--------~420~
--"
~
~
~
~
~
~
~
~
E
~ ~ 40 ~--------_+_--------_41____",_____------4_--------~ 280 tí _ ~
~
~
e
e
2
2
~
~
E
5
E
20r---------+----------+---~~~.r--------_1140
Ok-------~L--------~--------~--------~O 60~---------_.--------_,----------,----------,420
OL---------~---------L---------L--------~O
120r---------~--------_.--------_r--------_,
~
t
E ffi~
80r----------+---------~----~~~4_--_+----~
~;
e.5
.~g e 5 40 ~--------_+_-----,~'__7'y------____~4_+------~ ~~ :JO>
~c
'" o 0::0;
°0L---------2~0-0--------4~OLO---------6LOO--------~800 Temperature. °F
5
Source: R.H. Voorhees and J.W. Freeman, Report on the ElevatedTemperature Properties of Aluminum and Magnesium Alloys, STP 291, ASTM, 1960. As published in Aerostructural Metals Handbook, Vol 3, Code 3213, CINDASlPurdue University, 1995, p 9
366/Wrought Aluminum (WA)
WA.107 2618-T61 aluminum alloy hand-forged billets, compressive stress-strain curves
60 r-------r-------,-------,-------,------, 420
RT I
50 1------+-----+---~~~~32i °F (163 OC)
Tested at elevated temperature. Typical for several handforged billets: 76.2 x 165.1 mm (3 x 612 in.), 101.6 x 203.2 mm (4 x 8 in.), and 203.2 x 279.4 mm (8 x 11 in.). Composition: AI-2.5Cu-l.5Mg-l.2Ni-l.OFe-0.2Si-0.l Ti. UNSA92618
350
400°F (204 OC)
~
:li
C/)~
~ :2 30 1-------11--f-H'-----1-------1--------1--------I210
ui
~
Source: J.A. Lumm, "Mechanical Properties of 2618 Aluminum Alloy," Technical Report AFML-TR-66-238, North American Aviation, Inc., July 1966. As published in Aerostructural Metals Handbook, Vol 3, Code 3213, CINDAS/Purdue University, 1995, p 9
~ 201-----~~----+_-----+_-----+_----~140
10I---.~-+_----+_----+_-----+_---~70
4
2
Strain,
8
6
0.001 in./in.
WA.108 2618-T61 aluminum alloy forged bar, tensile and compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
80°r-----,14~--~2~8'---------4r2----~56~----7~0~--~8\60
Tested at room temperature. Test direction: longitudinal. Typical for forged bar thickness 25.40 mm (1.000 in.). Ramberg-Osgood parameter, n(longitudinal, tension) = 13; n(longitudinal, compression) = 13. UNS A92618
Tension and compression 60~----+------+------1-----~~~_+----~420
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-205
~
~
:2
:li
40 I-----+-----A---+_---+"""'-o;;;;:---+---~ 280 ¡:f ~ w
C/)
~
201------fr----+----1-----~----+-+---I140
2
4
8 6 Strain, 0.001 in./in. Compressive tangent modulus,
106 psi
Wrought Aluminum (WA)/367
80
560
WA.109 2618-T61 aluminum alloy forged bar, tensile stress-strain curve (full range)
70
490
Tested at room temperature. Test direction: longitudinal. Typical for forged bar thickness 25.40 mm (1.000 in.). UNSA92618
---
J---
60
í
50
420
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-206 350
ti.
:2
280 ui
~
30
210
20
140
10
70
0.02
0.04
0.06 Strain. in.lin.
20 18 16
/
14
~ 12
¡ I
ui rn ~
u; 10 ~ .¡¡; c:
~
8 6
V
./
v---
1-"'"
~
J~
0.08
--
o
0.10
0.12
126 112 Nominal
~
\~ I I
I I
f
I
2
YS
~ ¿P
V 0.0
98 tU
84
a. :2 cñ
70
i
rn
Q)
56
I ~I
4
I I I I I 1
0.04
0.08
0.4
0.8
0.12 0.16 Strain. in.lin. 1.2 1.6 Strain. 0.001 in.lin.
WA.110 3003-0 aluminum alloy rod, tensile stressstrain curves
140
¡.-
42 28
lBc: ~
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essentially identical for both the true and nominal curves. YS, yield strength. Test specimen diam, 12.7 mm (0.5 in.). Gage length: 203.2 mm (8 in.). Nominal tensile strength, 105 MPa (15.2 ksi). True tensile strength, 130 MPa (18.8 ksi). Nominal yield strength (0.2% offset), 36 MPa (5.2 ksi). Elongation (in 50.8 mm, or 2 in.), 27.2%. Reduction of area, 71 %. True strain at maximum load, 21.5%. A log-log plot of the stress-strain curve would yield a slope of (n) of 0.24 in the area of uniform plastic deformation. UNS A93003 Source: Alcoa, A1uminum Research Laboratory, New Kensington, PA
14
o
0.20
0.24
0.28
2.0
2.4
2.8
368/Wrought Aluminum (WA)
WA.lll 3003-H12 aluminum alloy rod, tensile stress-strain curves
25,-------,-------,-------,--------,------,175
True
ro
'¡¡; -" ui
105 ~ ","
'"~
'"~
.!Q
.!Q
tí
tí
'¡¡; e
~
70
\
\ \ I I
35
'¡¡; e
~
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essential1y identical for both the true and nominal curves. YS, yield strength. Test specimen diam, 12.7 mm (0.5 in.). Gage length: 203.2 mm (8 in.). Nominal tensile strength, l38 MPa (20.0 ksi). True tensi1e strength, 142 MPa (20.6 ksi). Nominal yie1d strength (0.2% offset), 119 MPa (17.3 ksi). Elongation (in 50.8 mm, or 2 in.), 9.8%. Reduction of area, 76%. True strain at maximum load, 3.0%. A log-log plot of the stress-strain curve wou1d yield a slope of (n) of 0.06 in the area of uniform plastic deformation. UNS A93003 Source: Alcoa, Aluminum Research Laboratory, New Kensington, PA, July 1954
~------L-------L-----~------~------~O
0.04
0.02
0.06
0.08
0.10
Strain, in./in.
O
4
2
6
Strain. 0.001 in./in.
25,-------,-------,-------,-------,-------,175 True
.¡¡; -" ui
WA.l12 3003-H14 aluminum alloy rod, tensile stress-strain curves The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essential1y identical for both the true and nominal curves. YS, yie1d strength. Test specimen diam, 12.7 mm (0.5 in.). Gage length: 203.2 mm (8 in.). Nominal tensile strength, 159 MPa (23.0 ksi). True tensile strength, 161 MPa (23.4 ksi). Nominal yield strength (0.2% offset), 147 MPa (21.3 ksi). Elongation (in 50.8 mm, or 2 in.), 4.5%. Reduction of area, 54%. True strain at maúmum load, 1.6%. A log-log plot of the stress-strain curve would yie1d a slope of (n) of 0.05 in the area of uniform plastic deformation. UNS A93003
15
'"
~
tí
.!Q
.¡¡; e
~ 10
Source: Alcoa, Aluminum Research Laboratory, New Kensington, PA
0.01
0.02
0.03
o
0.04
0.05
4
5
Strain, in./in.
O
2
3
Strain. 0.001 in./in.
Wrought Aluminum (WA)/369
WA.113 3003-H18 aluminum alloy rod, tensile stress-strain curves
245
35 True_ 30
...
f
25
!
'¡¡; -'" uf 20 IJ)
/
.!!1
'~ 15
10
/
5
V ° ° °
,
~/ ~ 175 '\
\
ro
a.
\
140 ::2. \
:z
\ \
1ñ
~
al
105 'jj¡
Y
~
210
/'
~
~
.... ....
"
I I I
i
I
~ 70
I I I I I I .1. 0,01
0,02 0,03 Strain, inJin,
2
3
Source: Alcoa, Aluminum Research Laboratory, New Kensington, PA, July 1954
35
°
0,04
0,05
4
5
Strain, 0,001 inJin,
25
WA.114 3003-H24 aluminum alloy rod, tensile stress-strain curves
175
'¡¡; -'" 15 uf IJ)
True_
-1-::::::::::::
Nominal
~
/:0
r
20
1ñ .!!1 '¡¡;
"
\
\ \
35
I I I I
V
J. 0,02
0,04
2
4
0,06 Strain, inJin,
°
ro 105 ~
I I I I I 70 I I I I I
/
5
140
",
I
~
~ 10
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essentially identical for both the true and nominal curves. YS, yield strength. Test specimen diam, 12.7 mm (0.5 in.). Gage length: 203.2 mm (8 in.). Nominal tensile strength, 212 MPa (30.8 ksi). True tensile strength, 216 MPa (31.3 ksi). Nominal yield strength (0.2% offset), 195 MPa (28.3 ksi). Elongation (in 50.8 mm, or 2 in.), 3.5%. Reduction of area, 34%. True strain at maximum load, 2.0%. A log-log plot of the stress-strain curve would yield a slope of (n) of 0.06 in the area of uniform plastic deformation. UNS A93003
Strain, 0,001 inJin,
0,08
0,10
i .!!1 '¡¡;
" ~
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essentially identical for both the true and nominal curves. YS, yield strength. Test specimen diam, 12.7 mm (0.5 in.). Gage length: 203.2 mm (8 in.). Nominal tensile strength, 145 MPa (21.0 ksi). True tensile strength, 223 MPa (32.3 ksi). Nominal yield strength (0.2% offset), 133 MPa (19.3 ksi). Elongation (in 50.8 mm, or 2 in.), 10.8%. Reduction of area, 55%. True strain at maximum load, 5.8%. A log-log plot of the stress-strain curve would yield a slope of (n) of 0.06 in the area of uniform plastic deformation. UNS A93003 Source: Alcoa, Aluminum Research Laboratory, New Kensington, PA, July 1954
°
370/Wrought Aluminum (WA)
35
WA.115 3004-0 aluminum alloy rod, tensile stressstrain curves
245
30
~
/
25
~
Y
~
V-
~¡-
-
Nominal
210
\..
\
175 ro
a.
I
140~
V' j
I
10
o
I
~
CI)
105
~ c:
~
70
~~
$
5
rJ)
/
Source: Alcoa, Aluminum Research Laboratory, New Kensington, PA, July 1954
35
_A
O
0.02
0.04
0.06
2
3
0.08
0.10
0.12
0.14
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portíon is essentially ídentical for both the true and nominal curves. YS, yield strength. Test specimen diam, 12.7 mm (0.5 in.). Gage length: 203.2 mm (8 in.). Nominal tensile strength, 191 MPa (27.7 ksi). True tensile strength, 218 MPa (31.6 ksi). Nominal yield strength (0.2% offset), 67 MPa (9.7 ksi). Elongation (in 50.8 mm, or 2 in.), 15.6%. Reduction of area, 47%. True strain at maximum load, 13.1 %. A log-log plot of the stress-strain curve would yield a slope of (n) of 0.24 in the area of uniform plastic deformation. UNS A93004
O
0.16
Strain, in./in.
o
4
Strain, 0.001 in./in.
40
~
.......~ ,..-
35 ~
r
30
~ 25
~
....
\
20
c:
~ 15 10
I
5
oO
210
~
175 ~ ::;¡¡
gf 140 ~ rJ) .!!1 .¡¡;
105
70
35
0.02
0.03
2
3
0.04
0.05
0.06
5
6
Strain, in./in.
O
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essentially ídentical for both the true and nominal curves. YS, yield strength. Test specimen diam, 12.7 mm (0.5 in.). Gage length: 203.2 mm (8 in.). Nominal tensile strength, 255 MPa (37.0 ksi). True tensile strength, 270 MPa (39.2 ksi). Nominal yield strength (0.2% offset), 201 MPa (29.2 ksi). Elongation (in 50.8 mm, or 2 in.), 8.0%. Reduction of area, 54%. True strain at maximum load, 5.8%. A log-log plot of the stress-strain curve would yield a slope of (n) of 0.14 in the area of uniform plastic deformation. UNS A93004
YS
11
0.01
245
'f'O'"""
I
.!!1 .¡¡;
WA.116 3004-H34 aluminum alloy rod, tensile stress-strain curves
\
V
CI)
,
280
\
/
t5
~
--
Nomin1al
4
Strain, 0.001 in./in.
0.07
O
0.08
~
Source: Alcoa, Aluminum Research Laboratory, New Kensington, PA, July 1954
Wrought Aluminum (WA)/371
45
-~
40
cP'
35
~
1-::.:::'--- >-
30
/
.c;; -'"
.......... YS
V
"
~
üi ~ 20 I/l c:
10
I V
5
O O
I 70
I 35
Source: Aleoa, Aluminum Research Laboratory, New Kensington, PA, July 1954
~
245 210
'"
[L
::2:
I/l
I I
vr
15
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essentially identical for both the true and nominal curves. YS, yield strength. Test specimen diam, 12.7 mm (0.5 in.). Gage length: 203.2 mm (8 in.). Nominal tensile strength, 283 MPa (41.0 ksi). True tensile strength, 317 MPa (46.0 ksi). Nominal yield strength (0.2% offset), 247 MPa (35.8 ksi). Elongation (in 50.8 mm, or 2 in.), 6.9%. Reduction of area, 46%. True strain at maximum load, 4.9%. A log-log plot of the stress-strain curve would yield a slope of (n) of 0.10 in the area of uniform plastic deformation. UNS A93004
~
I
/
~
280
175 ui
1/
I/l
WA.117 3004-H38 aluminum alloy rod, tensile stress-strain curves
NOmiL,
.ü.
6
ui 25
--
315
I I
üi
140 ~
I/l
c:
~
105
I I I I
J.
0.01
0.02
0.03
0.04
o
0.05
0.06
0.07
5
6
7
Strain, in./in.
2
O
3
4
Strain, 0.001 in./in.
~
--=::
40
t
~~
I
~ 30 ui
~
..Q1
.c;; c:
~
WA.118 3004-H39 aluminum alloy rod, tensile stress-strain curves
350
50
20
I
10
o
b:::==>Ir4s
...
NoJinal
~
280
\
\ \ \ \
210
!/
I I I I I I I I I I
ui
~
üi .c;; 140 ~ ..Q1
70
V
I I I I .l
O
0.01
0.02
o
2
4
0.03
0.04
Strain, in./in.
6 8 Strain, 0.001 in.lin.
0.05
0.06
g¡'"
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essentially identical for both the true and nominal curves. YS, yield strength. Test specimen diam, 12.7 mm (0.5 in.). Gage length: 203.2 mm (8 in.). Nominal tensile strength, 307 MPa (44.5 ksi). True tensile strength, 314 MPa (45.6 ksi). Nominal yield strength (0.2% offset), 273 MPa (39.6 ksi). Elongation (in 50.8 mm, or 2 in.), 6.6%. Reduction of area, 40%. True strain at maximum load, 4.2%. A log-log plot of the stress-strain curve would yield a slope of (n) of 0.09 in the area of uniform plastic deformation. UNS A93004 Source: Aleoa, Aluminum Research Laboratory, New Kensington, PA, July 1954
o 0.07
372/Wrought Aluminum (WA)
35
245
30
/~ .,.....
25
¡J
I
10
I
I
5
o
l
O
-18 100
2
3
38
80
~
E
::J
i!! "#. 60
s:
-Ol
'" e c. E ,¡,'"
'" §'" ;;t40
93
-......
0.08 0.10 0.12 Strain, in.lin. 456 Strain, 0.001 in.lin.
7
8
316
'\~ ;\1\ 1\l\
g~
'" a.
0.16
~
"O
~
~ ~
0.14
Temperature, oC 204 260 149
o~
e
175
:
0.06
E
e
'\ \ I I
0.04
2
al ~
>-""-"
Y>-' ~
V
~
.3
V
f/
~::J
~e
~
210
Nominal
If
0.02
o
V
/ v
20
I I I I I I 70 I I I I 35 I I I .1. O 0.18 0.20
9
100
200
400 500 Temperature, °F
300
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essentially identical for both the true and nominal curves. YS, yield strength. Test specimen diam, 12.7 mm (0.5 in.). Gage length: 203.2 mm (8 in.). Nominal tensile strength, 198 MPa (28.7 ksi). True tensile strength, 230 MPa (33.3 ksi). Nominal yield strength (0.2% offset), 71.0 MPa (10.3 ksi). Elongation (in 50.8 mm, or 2 in.), 18.5%. Reduction of area, 70%. True strain at maximum load, 14.8%. A log-log plot of the stress-strain curve would yield a slope of (n) of 0.20 in the area of uniform plastic deformatíon. UNS A95052 Source: Alcoa, Aluminum Research Laboratory, New Kensington, PA, July 1952
10
371
427
WA.120 5052-0 aluminum alloy, all products, effect of elevated temperature on tensile properties
Strength at temperature after exposure up to 10,000 h. UNSA95052 Source: MIL-HDBK-5H, 1 Dec 1998, p 3-212
0
~v
....... F
e al
WA.119 5052-0 aluminum alloy rod, tensile stressstrain curves
600
tu
700
800
Wrought Aluminum (WA)/373
40
35
~
/
30
rñ
gj
20
.!!! '00 e
~ 15
5
o
I V O
Nominal
V
\
~
YS
WA.121 5052-H34 aluminum alloy rod, tensile stress-strain curves
245
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essentially identical for both the true and nominal curves. YS, yield strength. Test specimen diam, 12.7 mm (0.5 in.). Gage length: 203.2 mm (8 in.). Nominal tensile strength, 262 MPa (38.0 ksi). True tensile strength, 279 MPa (40.5 ksi). Nominal yield strength (0.2% offset), 211 MPa (30.6 ksi). Elongation (in 50.8 mm, or 2 in.), 8.6%. Reduction of area, 58%. True strain at maximum load, 5.8%. A log-log plot of the stress-strain curve would yield a slope of (n) of 0.14 in the area of uniform plastic deformation. UNS A95052
210 \ \
V I V
175
1 I I
rñ UJ
140 ~
:
.!!! '00
I
e
105 ~ I I I I I I
70
J.
0.01
0.02 2
38
0.03
0.04 0.05 0.06 Strain, in./in. 345 6 Strain, 0.001 in./in.
Temperature, oC 149 204 260
O
0.07
0.08
0.09
7
8
9
371
427
316
:, ~80r----+-~--+---~~~~--~1~0~,O~00~h~----+----4
~
*
1000 h 100 h 1/2-10 h
.2l
60r_--~----+_---+----~~_4----~----r_--~
E
~ ~
:::l
"'§
~40r---~----+----+-~--4---~~--~----r---~
E
.2l
E
~
ID
WA.122 5052-H34 aluminum alloy sheet and plate, effect of elevated temperature on ultimate tensile strength
Strength at temperature after exposure up to 10,000 h. UNSA95052
!:S"" :5
o
Source: Alcoa, Aluminum Research Laboratory, New Kensington, PA
I I
1oor----,----~~-,----_r----r_--~~--,_--~
.!!! .~
~
:2
35
o
-18
~ V--
280
... , ~\
/
-'"
10
V
~
'00 25
ti
~
~ ;,---
20r_--~----+_---+----+_--_4--~~~--r_--~
o>
.l9 e
~
al
a.
°0L----1~00----2~0-0---3~0-0---4~0-0---5-0LO----60LO----7LOO--~800 Temperature, °F
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-214
374/Wrought Aluminum (WA)
Temperature, oC
-18 100
38
93
149
~
'# ~
u.-
:; 80
204
~ ~
C, e
~
"O
ID
0;;, 60 ..9l 00 e .$ °
260
316
371
427
10,0001h 1000 h 1/2 -100 h
WA.123 5052-H34 aluminum alloy sheet and plate, effect of elevated temperature on tensile yield strength
Strength at temperature after exposure up to 10,000 ho UNSA95052 Source: MIL-HDBK-5H, 1 Dec 1998, p 3-214
,
~
:::¡
1\
§ ~
40
\
E .$ E o
2 '5 20 ID
'"""
~
e
~
ID
Il..
100
200
300
400
500
~
600
700
800
316
371
427
Temperature, °F
Temperature, oc
-18 100
38
93
149
204
260
~~~
~:::¡
':S" ,s
10 h 100~/ 1000 h ~ 10,000
g' 80
~
h/
..9l 00 e .$
Strength at temperature after exposure up to 10,000 h, as indicatedo UNS A95052
l~
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-215
°
~ 60 E :;
""
~
:::¡
ro
~ 40
E .$ E O
2
~ 20 Ol
.l'l e
~ID
Il..
100
200
300
400
500
Temperature, °F
WA.124 5052-H34 aluminum alloy sheet and plate, effect of elevated temperature on ultimate tensile strength
600
700
800
Wrought Aluminum (WA)/375
WA.125 5052-H34 aluminum alloy sheet and plate, effect of elevated temperature tensile yield strength
1001~8~_~3r8__~9~3~~~~~__~~___3_1r6____ 37r1__-.427
Strength at temperature after exposure up to 10,000 h, as indicated, UNS A95052
~
-";.., 1.1.:'"
~
80 I - - - - - I - - - - f - -
C, e
~
-O
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-215
1/2 hlL..,A'1,\-----I-\-\~_+----+_--__I 10 h 100 h 1000 h 10,000 h
a; .~ 601___--_+----+---_+-----~~~--+__I_----r_--~ .22 .~
.$ ~
~~401------+-----+----+----~--~~~~~--~---i E .$ E
ª
O 20~---+----+---~----~--~r_--_r----T_--~
.lE e
~
a.
100
200
300
400
500
600
700
800
Temperature, "F
WA.126 5052-H38 aluminum alloy rod, tensile stress-strain curves
350
50
~ 1-
40
~
r
I
L-::::::: ~ :---
Nlminal
~
~
280 \ \ \ \
I I I I I I I I I I
1/
J
10
o
al
210 ~
~
~
1ñ .22 '00
140 ~
70
I I I I
V
.l
O
0.01
0.02
0.03
o
2
4
6
0.04
0.05
Strain, inJin.
8
Strain, 0.001 inJin.
0.06
0.07
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve, The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essentially identical for both the true and nominal curves, YS, yield strength, Test specimen diam, 12,7 mm (0,5 in,), Gage length: 203.2 mm (8 in,), Nominal tensile strength, 301 MPa (43,6 ksi), True tensile strength, 317 MPa (46,0 ksi). Nominal yield strength (0,2% offset), 259 MPa (37.5 ksi), Elongation (in 50,8 mm, or 2 in,), 7,5%, Reduction of area, 49%, True strain at maximum load, 5.4%. A log-log plot of the stress-strain curve would yield a slope of (n) of 0,12 in the area of uniform plastic deformation. UNS A95052 Source: Alcoa, Aluminum Research Laboratory, New Kensington, PA, July 1954
O 0.08
376/Wrought Aluminum (WA)
Temperature, oC
-18 100
38
93
~
316
371
427
WA.127 5052-H38 aluminum alloy, all products, effect of temperature on ultimate tensile strength
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-217
N\~
1/2h 10,000h
1\
~
60
E
=§ ~
~
260
Strength at temperature after exposure up to 10,000 h. UNSA95052
V V
~
~
204
~r\
·00 e
-*l
149
40
\
E
.l!l
E
~
O
e 'O 20
'~
'"'" ¡: '" a. '"
.l9 e
100
200
300
400
500
F'=--
600
700
800
316
371
427
Temperature, °F
Temperature, oC
-18 100
38
93
-......
149
204
260
~1\
Strength at temperature after exposure up to 10,000 h. UNSA95052 Source: MIL-HDBK-5H, 1 Dec 1998, p 3-217
W
1/2 h 10,000 h
~
l\
100
200
300
WA.128 5052-H38 aluminum alloy, all products, effect of temperature on tensile yield strength
400
~
500
Temperature, °F
i'-
600
700
800
Wrought Aluminum (WA)/377
Temperature, oC
-18 100
38
93
149
204
260
316
371
427
"~
100~ ~ ~ ~~~
:E
Exposure up to 10,000 h. UNS A95052 Source: MIL-HDBK-5H. 1 Dec 1998, p 3-218
1000 h 100 ~ (;
g> 80
., ~
WA.129 5052-H38, aluminum alloy, all products, effect of exposure at elevated temperatures on room-temperature ultimate tensile strength
10~/
1/2 h
.$ ro E
~.
:; 60 .$
"¡¡; c::
.$ ~
.a
~c.
40
E .$
E
o
e
~
20
E c:: ~
CIl
a.
o o
100
200
300
400
500
600
700
800
316
371
427
Temperature, °F
Temperature, oc
-18 100
38
93
149
204
~~
10,000~ 1000~~
100:~ 10 h 1/2 h
260
t\' ,
r
\\
Exposure up to 10,000 h. UNS A95052
~
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-218
\
\ ~\
"~
100
200
300
400
500
Temperature, °F
WA.130 5052-H38 aluminum alloy, all products, effect of exposure at elevated temperatures on room-temperature tensile yield strength
600
700
800
378/Wrought Aluminum (WA)
25
o
14
Compressive tangent modulus, GPa 28 42 56
WA.131 5083-0 aluminum alloy sheet, tensile and compressive stress-strain and compressive tangent modulus curves
70
Tested at room temperature. Test direction: longitudinal and long transverse. Typical. Ramberg-Osgoodparameter, n(longitudinal and long transverse, tension) =50; n(longitudinal and long transverse, compression) = 50. UNS A95083
TensiJ and comptssion
20
r'--- .,--
140
---""1'\
I
15
105
I I
·00
"'vi" (fJ
~ 10
5
vi (fJ
~ (J) 70
35
8 10 6 Strain, 0.001 in./in. 6 Compressive tangent modulus, 10 psi
4
2
25
I 20
15 ·00
"'vi" (fJ
~
1ií 10
5
o..'"
:2
1/
o
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-224
14
Compressive tangent modulus, GPa 28 42 56
~,.l oompLoo ~ r:---1---r---
o
12
WA.132 5083-0 aluminum alloy plate, tensile and compressive stress-strain and compressive tangent . modulus curves
70
Tested at room temperature. Test direction: longitudinal and long transverse. Typical. Ramberg-Osgood parameter, n(longitudinal and long transverse, tension) = 21; n(longitudinal and long transverse, compression) = 21. UNSA95083
"d
I
140
~
I I
105
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-224
&.
:2 vi
(fJ
~ (J) 70
35
1/ 2
10 8 6 Strain, 0.001 in./in. 6 Compressive tangent modulus, 10 psi
4
o
12
Wrought Aluminum (WA)/379
350
50
40
/
30 'iii
V
----
- - - ...
ii5
20
Tested at room temperature. Test direction: longitudinal. Typical. UNS A95083
280 )(
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-225
210
ro
a.
/
""ui '"~
WA.133 5083-0 aluminum alloy plate, tensile stressstrain curve (full range)
::¡;
140
i
70
10
o
0.04
O
0.08
0.12
0.16
0.20
o
0.24
Strain, in./in.
WA.134 5086-0 aluminum alloy sheet, tensile and compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
25
o
14
28
42
56
70
Tested at room temperature. Test direction: longitudinal and long transverse. Typical. Ramberg-Osgood parameter, n(longitudinal and long transverse, tension) = 27; n(longitudinal and long transverse, compression) = 27. UNSA95086
140
20
I~~ression 15
""ui '" ~ 10
5
105
1
'iii
---"'r\
::¡; ",.
'"~
70
I
35
1/ 2
10
4
6 8 Strain, 0.001 in./in. Compressive tangent mOdulus,
106 psi
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-229 ro
a.
o
12
ii5
380/Wrought Aluminum (WA)
25
o
14
Compressive tangent modulus, GPa 28 42 56
_\ Tension and compression 20
"''" ~
1ií
10
105
2
~
"''" ~
~
~
70
~
1\
6 8 10 Strain, 0.001 in.lin. 6 Compressive tangent modulus, 10 psi
4
40
30
"'"
",-
'"
~
1ií 20
1ií
35
o
12
WA.136 5086-0 aluminum alloy 5086-0 sheet, tensile stress-strain curve (full range)
350
50
.¡¡;
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-229
!L
/
2
Tested at room temperature. Test direction: longitudinal and long transverse. Typical. Ramberg-Osgood parameter, n(longitudinal and long transverse, tension) = 5.0; n(longitudinal and long transverse, compression) = 5.0. UNSA95086
140
V~
~
5
"....-
/
\v I
15
WA.135 5086-0 aluminum alloy plate and extrusion, tensile and compressive stress-strain and compressive tangent modulus curves
70
/
/
/
/'
~
Tested at room temperature. Test direction: longitudinal. Typical. UNS A95086
-
280
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-230
'""
210
!L
2
"'
'" ~
140
70
10
0.04
0.08
0.12 Strain, in.lin.
0.16
0.20
o
0.24
en
Wrought Aluminum (WA)/381
WA.137 5086-Hl12 aluminum alloy plate, tensile and compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus. GPa
25°r-----,1r4-----,28--.----,42------5,6------7TO------,~175
Tested at room temperature. Test direction: L, longitudinal; LT, long transverse. Typical for plate thickness 12.70-25.40 mm (0.500-1.000 in.). Ramberg-Osgood parameter, n(L, tension) = 18; n(LT, tension) = 10; n(L, compression) = 9.3; n(LT, compression) = 10. UNSA95086
LT. tension and compression
105
a.
'üi -'"
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-234
:2
ui
ui
'"~
'"
~
ú:i
70
ú:i
~~---+-----~------~-----+------~~--~35
L -_ _ _ _
~
2
_ _ _ _-L__·__
4
~
______L -_ _ _ __ L L __ _
6 8 Strain. 0.001 in./in.
10
~O
12
6 Compressive tangent modulus. 10 psi
WA.138 5086-H32 aluminum alloy sheet, tensile
Compressive tangent modulus. GPa
50
o
'14
28
42
56
stress-strain curves
70
Tested at room temperature. Typical for sheet thickness 3.175 mm (0.125 in.). Ramberg-Osgood parameter, n(longitudinal, tension) = 28; n(long transverse, tension) = 10. UNSA95086
280
40
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-230 _ _ _ Longitudinal. tension
/ ' ¡.....--
30 'üi -'"
ui
'"~
ú:i
20
10
/ V
I
I
Long transverse. tension
210
'r
¡i ~
140 ú:i
70
2
4
a.
:2
6
8
Strain. 0.001 in./in. Compressive tangent modulus. 106 psi
10
382/Wrought Aluminum (WA)
WA.139 5086-H32 aluminum alloy sheet, compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
5oor-----~14------,28------4~2------5,6------7~0----~8~50
Tested at room temperature. Typical for sheet thickness 3.175 mm (0.125 in.). Ramberg-Osgood pararneter, n(longitudinal, compression) = 8.0; n(long transverse, compression) = 10. UNS A95086
40r-----~--~-4------+-----~------r_----~280
Long transverse, compression
Source: MIL"HDBK"5H, 1 Dec 1998, p 3-231
210 ro Q.
30 '00 -"
:2
''""
''"" ~ 140
~
1ií
20
10~-+--~-----4------+------+------+4----~70
L-----~----~------~----~------~----~O
2
50
40
30 '00 -"
8 10 6 Strain, 0.001 in.lin. Compressive tangent modulus, 106 psi
LO"'~
rI
V
12
4
--------
~
--;.~;!:::""••,
Tested at room temperature. Typical for sheet thickness 3.175 mm (0.125 in.). Based on one lot. UNS A95086 280
210
","
'" ~ 20
140
10
70
0.04
0.08
0.12 Strain, in.lin.
0.16
0.20
WA.140 5086-H32 aluminum alloy sheet, tensile stress-strain curves (full range)
350
o
0.24
Source: MIL"HDBK"5H, 1 Dec 1998, p 3-231
ro Q. :2
l
Wrought Aluminum (WA)/383
Longitudinal, tension
;;
30
""ui '"
~
20
10
Tested at room temperature. Typical. Ramberg-Osgood parameter, n(longitudinal, tension) = 24; n(long transverse, tension) = 9.3. UNS A95086
280
40
.¡¡¡
WA.141 5086-H34 aluminum alloy sheet, tensile stress-strain curves
350
50
/ V
v-:: ,-
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-231
/ < n g transverse, tensíon
210
V
~
::2
lZ
140
~
70
2
4
6 Strain,
10
8
o
12
0.001 inJin.
WA.142 5086-H34 aluminum alloy sheet, compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
5oor-·----~1~4----~28------~42------5~6------7TO----~8\50
I
I
Tested at room temperature. Typical. Ramberg-Osgood parameter, n(longitudinal, compression) = 8.6; n(long transverse, compression) = 12. UNS A95086
Long transverse, compression
40¡-~~-¡-----¡------~~~~~--t-----¡280
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-232
.¡¡¡
30 r------r~~~~~--~~~_+------+_----_1210
o..
""ui
::2
'"
~
20
r-----~----~r-----_r----_1----~~----_41401
10r--+---r----~------_r----_1------~r_--_470
~-----2~----~4------~6------~8------1~0-L--~1~
Strain, 0.001 in./in. Compressive tangent mOdulus,
106 psi
384/Wrought Aluminum (WA)
40
.¡¡;
WA.143 5086-H34 aluminum alloy sheet, tensile stress-strain curve (full range)
350
50
-7
~
l----
-- .....
¡--
Tested at room temperature. Test direction: longitudinal. Typical. UNS A95086
280
210
30
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-233
'"
O-
"'
:2:
~
!!!
20
140
10
70
0.02
0.04
0.06
0.08
iñ
o
0.10
0.12
70
84
Strain, in./in.
WA.144 5086-H36 aluminum alloy sheet, tensile and compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
O
14
28
42
56
5o.------,-----,~----,------T----~T-----~350
Tested at room temperature. Test direction: L, longitudinal; LT, long transverse. Typical. Ramberg-Osgood parameter, n(L, tension) = 27; n(LT, tension) = 13; n(L, compression) = 8.0; n(LT, compression) = 15. UNS A95086 Source: MIL-HDBK-5H, 1 Dec 1998, p 3-233 .¡¡;
210
30
'"
O-
:2:
"'
Ul
iñ
jg
!!!
140
20
10~-f--~----~------4------+------~~--~70
2
4
6
8
Strain, 0.001 in./in. 6 Compressive tangent modulus, 10 psi
10
Wrought Aluminum (WA)/385
WA.145 X5090-H36 aluminum alloy sheet, effect of temperature on tensile properties after 30 min at test temperature
Temperature, oc
38
-18
70
93
---.,¡ 60
50
149
"~
420
"-
~ ,,~
'00
-'"
cñ
'"~
U5 40
'\
30
\
350
~
280
210
20
140
40
280
o !e.
.S 20 C\I
e
O
~ el e
~
-
Ir-""
O
üJ
100
200 Temperature, °F
300
/
ro
c..
:2 cñ rJ)
"EE .~
Test direction: longitudinal. F;u, ultimate tensile strength; F;y, tensile yield strength. Composition: Al-7Mg-O.2CrO.005B-O.005Be
140
U5
Source: "Properties and Characteristics of Aluminum Alloy X5090, a High-Strength Work Hardening Sheet Material," Technical Information Report MRL-71-TIR-5, Metals Research Laboratory, Olin Corporation, 11 Oct 1971. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3304, CINDASlPurdue University, 1995, p 4
386/Wrought Aluminum (WA)
WA.146 X5090-H38 aluminum alloy sheet, stressstrain curves at various temperatures
7or------,------~----~------,_----~r_----~490
Test direction: longitudinal (top); long transverse (bottom). Composition: AI-7Mg-O.2Cr-O.005B-O.005Be
60r-----~------+_----_+~~~~----~~~--~420
50~----_+------+7L---_+~----~----~------~350
'¡jj
40
~----_+--__1--H'----_+------+__----~------~
280
~
w ~
00
!
(J)
~ ~
325 'F (163 'C)
30
210 (jj
20~--~LV'--~--+------+------+------~------~140
400 'F (204 'C) 10~~~~~~--+------+------+------~------~70
o~-----L----~------~-----L------L-----~O
70
490
60~----_+------+_----_+------+__----~------~420
75 'F (24 'C) 350
'¡jj
40 I-----+------?-+--_+------.::J...~--~------~ 280
~
~
(J)
~ ~
00 00
00 00
~
30
210 (jj 400 'F (204 'C)
101--h~~~---4------+------+------r-----~70
°0~-----2L------L4------~6------~8------~1-0----~120 Strain. 0,001 inJin,
Source: O.L. Deel and H. Mindlin, "Engineering Data on New Aerospace Structural Materials," Technical Report AFML-TR-71-249, Battelle Memorial Institute, Dec 1971. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3304, CINDASlPurdue University, 1995, p 3
Wrought Aluminum (WA)/387
Temperature,
oc
WA.147 X5090-H38 aluminum alloy sheet, effect of temperature on tensile properties after 20 min at test temperature
80~18_________3~8________-.93__________ 14~9________~20!60
F tu , ultimate tensile strength; F ty , tensile yield strength. Composition: Al-7Mg-O.2Cr-O.005B-O.005Be
70~------~~~~------4----------+----------1490
Source: 0.1. Deel and H. Mindlin, "Engineering Data on New Aerospace Structural Materials," Technical Report AFML-TR-71-249, Battelle Memorial Institute, Dec 1971. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3304, CINDAS/Purdue University, 1995, p 4
60~-----~'-+---------~~------~---------1420 L ___ _
F
-'...........
.... __ !!'_-
-- " ,
~ 50~--------~--------~~~~,--~~+----------1350~
"
¡i
,........
~
~~
,
::¡; rñ ~
'"
'~~
30~--------+---------~--------~~--~~~210
20~--------+---------~--------~----~~~140
• Longi\udinal ... Long transverse
10L----------
--------~--------~------~70
L1
80r----------r----------,----------~--------_.560
60
420
;f<
E E o
ro
!!?
a.
::¡; 280 rñ
.5 40 N
'"
-~
~
c:
~
-2
ro
'"c:
o ¡¡:¡
20
140
°0~-------~1~00~--------2~0~0---------30LO--------~408 Temperature, °F
388/Wrought Aluminum (WA)
WA.148 X5090-H38 aluminum alloy sheet, compressive stress-strain curves at various temperatures
8or------.------~----_,------~------r_----_,560
70~----~----~------4_----_+------+_----~490
Test direction: longitudinal (top); long transverse (bottom). Composition: AI-7Mg-O.2Cr-O.005B-O.005Be
60~----~----_+----_0------~~~1=~--~420
Source: O.L. Deel and H. Mindlin, "Engineering Data on New Aerospace Structural Materials," Technical ReportAFML-TR-71-249, Battelle Memorial Institute, Dec 1971. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3304, CINDASlPurdue University, 1995, p 4
50~-----+------+_--~~------~------~----~350
10~_A~~----_4------+_----_+------+_----~70
OL------L----~------~----~------~----~O
80,------,------,------,------,-------,-----,560
70~----_+------+------+------+_--~~~----~490
50~-----+------+-~L--+------+---~~F-----~350
~
gf 40 ~----_+----~+_--~4------+_----___11_----~ 280
~
210
201_--~~~~~------+-----_+------+_----~140
10~_A~~----_4------+_----_+------+_----~70
°0~-----L2------~4------~6------~8-------1LO----~1f Strain, 0.001 in./in.
~ !Ji
~
Wrought Aluminum (WA)/389
45
v
40
/
35 30
] ,;; 25
~
~
CIl
(
10 5
\.
ip
\
WA.149 5154-0 alurninum alloy rod, tensile stressstrain curves
280
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essentially identical for both the true and nominal curves. YS, yield strength. Nominal size: 19 mm (3/4 in.) diam. Test specimen diam, 12.7 mm (1/2 in.). Gage length: . 203.2 mm (8 in.). Nominal tensile strength, 260 MPa (37.7 ksi). True tensile strength, 307 MPa (44.5 ksi). Nominal yield strength (0.2% offset), 150 MPa (21.7 ksi). Elongation (in 50.8 mm, or 2 in.), 21.5%. Reduction of area, 66%. True strain at maximum load, 16.6%. A loglog plot of the stress-strain curve would yield a slope of (n) of 0.19 in the area of uniform plastic deformation. UNSA95154
210
&. ~
~~
175 ,;; CIl
~
1ií
YS
140
~
CIl
c: ~
105
J
I V
315
245
I
I
15
Nominal
\ \
20
c: ~
...
~
/V
/
T~ t..---
j
0.04
0.08
0.12
0.16
70
i
35
.i. 0.20
o
Source: Alcoa, Aluminum Research Laboratory, New Kensington, PA
Strain. in.lin.
o
2 Strain.
4
6
0.001 in.lin.
WA.150 5454-0 aluminum alloy sheet, plate, and extrusion, tensile and compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus. GPa
2oo.-----~1r4------2,8----~42~----,56~----7~0~--~M140
Tested at room temperature. Test direction: longitudinal and long transverse. Typical. Ramberg-Osgood parameter, n(longitudinal and long transverse, tension) = 16; n(longitudinal and long transverse, compression) =9.6. UNSA95454
+------+------+------1105
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-238 ro
.¡¡; -'"
,;; CIl
~
a.
~
10
70
,;; CIl
~
en
5~~--~----~------4-----_+------~~--~35
Strain. 0.001 in.lin. Compressive tangent modulus. 106 psi
390/Wrought Aluminum (WA)
WA.151 5454-H32 aluminum alloy rod, tensile stress-strain curves
350
50
40
~
/
y
..~ I
(
~
-o-...
'\
280
1\
\
-<)
\
I I I I
I
10
ro
210 ~
"'
'"l'! 'lií ..9! 'c;; 140 ~
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essentialIy identical for both the true and nominal curves. YS, yield strength. Nominal size: 19 mm (3/4 in.) diam. Test specimen diam, 12.7 mm (0.50 in.). Gage length: 203.2 mm (8 in.). UNS A95454 Source: Alcoa, Aluminum Research Laboratory, New Kensington, PA
I I I I
70
I I 1
0.02
0.04
0.06
0.08
o
0.10
0.12
10
12
Strain. in.lin.
o
2
468 Strain. 0.001 in.lin.
WA.152 5454-H32 aluminum alloy plate, tensile stress-strain curves
350
50
Tested at room temperature. Typical. Ramberg-Osgood parameter, n(longitudinal, tension) = 7.5; n(long transverse, tension) = 6.8. UNS A95454
280
40
Source: MIL-HDBK-5H. 1 Dec 1998, p 3-238
........- ~ ~
30 'c;;
Long transverse
210
"''"
l'!
en
20
/ 1/
:2
:i ~ 140
70
2
4
6 Strain. 0.001 in.lin.
8
ro
11.
;/
~
10
~ Longitud1inal
10
o
12
Wrought Aluminum (WA)/391
Tested at room temperature. Test direction: longitudinal. Typical. Ramberg-Osgood parameter, n(longitudinal, tension) = 10. UNS A95454
280
40
30 ~
~ 20
10
WA.153 5454-H34 aluminum alloy plate, tensile stress-strain curve
350
50
/
/
I
L
V
~
~
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-239
210
c..'"
:2
gf ~
140 1i5
70
2
4
6
8
10
o
12
Strain, 0.001 in.lin.
WA.154 5454-H34 aluminum alloy sheet, tensile and compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
50°r----1r4---,28-----,42-----5,6~----7TO----~8\50
Tested at room temperature. Test direction: L, longitudinal; LT, long transverse. Typical. Ramberg-Osgood parameter, n(L, tension) = 50; n(LT, tension) = 11; n(L, compression) = 8.1; n(LT, compression) = 9.8. UNSA95454
/-----·++T-'-:=?::=:~~+-----+--__+--_l280
210 '00
-'"
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-239
c..'"
:2
~
~
1i5 140
r--r--r--~-----~--~---+1~-_470
~---~2~----~4---~6------~8-----1~0~--~1~
Strain, 0.001 in.lin. Compressive tangent modulus, 106 psi
1i5
392/Wrought Aluminum (WA)
6or-------r-------~------._------~------~
WA.155 5454-H38 aluminum alloy rod, tensile stress-strain curves
420
350
\\ \ \ \ \ \
280 C\l
eL ~
rñ
'" '" .J!1 .¡¡;
210 ~ e
~
140
10~_.~--+-------~------4_------~--~--~70
0.02 O
2
0.06 0.04 Strain, in./in. 6 4 Strain, 0.001 in./in.
0.08
0.18
8
10
The upper row of strain values on the abscissa applíes to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essentially identical for both the true and nominal curves. YS, yield strength. Nominal size: 19 mm (3/4 in.) diam. Test specimen diam, 12.7 mm (0.50 in.). Gage length: 203.2 mm (8 in.). UNS A95454 Source: Alcoa, Aluminum Research Laboratory, New Kensington, PA
Wrought Aluminum (WA)/393
WA.156 5456-0 aluminum alloy, effect of low and elevated temperature on tensile properties
Temperature, oc
702r4-o-------------T18-------------2~0-5------------__,42~90
F ro' ultimate tensile strength; F ty ' tensile yield strength. Composition: Al-5.1Mg-O.8Mn-O.lOCr. UNS A95456 60~~----------+-------------~------------~420
Source: Alcoa Aluminum Handbook, Aluminum Company of American, 1962. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3303, CINDAS/Purdue University, 1995, p 6
50r---~--------T_-------------_r------------~350
ro
~ 40r-------------+_-------~----~------------~280 ~ ~
~
o
~
~
~
éií 30
210 éií
20~------------+---------~.-~r-----------~140
10r-------------T_------------~--~~~----~70
o '---.--------'--------'-----------' O 160.-------------,-------------,-------------__,
o ~80r-------------+--------------~~~---------4 e
o
iii
• ~OO
o
400 Temperature, °F
800
394/Wrought Aluminum (WA)
Temperature, 'C
1oor-----2T4-o----------1,29----------,1~8--------~9~00
WA.157 5456-H321 aluminum alloy sheet, effect of low and room temperature on tensile properties F tu' ultimate tensile strength; F ty, tensile yield
strength. Sheet thickness: 3l.7 mm (l/8 in.). Composition: Al-5.1Mg-O.8Mn-O.lOCr. UNS A95456 801----~~r-------~--------4_----
560
~ ~
~60~--_+--------~~----~~~~~ ~
(f)
401----t-----~-+--~~
__~~
280
• Longitudinal O Transverse
20L----L---------L--------~--------~140
t:t~ -400
-200
Temperature, 'F
o
I
200
Source: J.E. Campbell, "Review of Current Data on the Tensile Properties of Metals at Very Low Temperarures," DMIC Report 148, Batelle Memorial Instirute, 14 Feb 1961. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3303, CINDASlPurdue University, 1995, p 6 .
Wrought Aluminum (WA)/395
WA.158 5456-H311 aluminum alloy extrusion, compressive stress-strain curves
350
50 JOnQitudinal - - Transverse
280
40
f/
-'"
cñ
Ul
~
10
Source: Metallic Materials and Elements for Flight Vehicle Structures, MIL-HDBK-5, Aug 1962. As published in Aerospace Structural Metals Handbook, Vo13, Code 3303, CINDAS/Purdue University, 1995, p 6
----::-:
/
30 '¡ji
20
Tested at room temperature. Composition: Al-51.MgO.8Mn-O.lOCr. UNS A95456
210
",,"
ro
a..
::¡; cñ
! 140
/ 1/
CI)
70
8
4
o
12
Strain, 0.001 in.lin.
50
WA.159 5456-H311 aluminum alloy extrusion, tensile stress-strain curves
350 J,OnQitudinal - - Transverse
40
280
/'
30
//
-"
cñ
Ul
~
10
Source: Metal/ic Materials and Elements for Flight Vehicle Structures, MIL-HDBK-5, Aug 1962. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3303, CINDASlPurdue University, 1995, p 6
¡....--- -
1//
'¡ji
20
Tested at room temperature. Composition: Al-51.MgO.8Mn-O.l0Cr. UNS A95456
---
210
gf
~ 140
/
1/
&.
::¡;
70
4
8 Strain, 0.001 in.lin.
396/Wrought Aluminum (WA)
WA.160 5456-0 aluminum aJ/oy plate, tensile stressstrain curves
490
70
V-- True
60
/
50 ~ rñ
~'" ~
30
~
20
10
¡.o-<'"
\ \ I
~
)
(J)
.~
Nominal
~~
40
420
I!
.nO ~
YS
1 0.08
4
8
0.12
0.16
0.20
rñ
'"~
u¡
I
210
I I I I
140
I
70
I 1 0.04
.,
o280 :2
I
I
f
350
~
c
~
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion ofthe curves; this expanded portion is essentially identical for both the true and nominal curves. YS, yield strength. Nominal thickness: 19 mm (0.750 in.) diam. Test specimen diam, 12.7 mm (1/2 in.). Gage length: 50.8 mm (2 in.). Nominal tensile strength, 350 MPa (50.8 ksi). True tensile strength, 423 MPa (61.3 ksi). Nominal yield strength (0.2% offset), 163 MPa (23.6 ksi). Elongation (in 50.8 mm, or 2 in.), 22.0%. Reduction of area, 28%. True strain at maximum load, 18.7%. A log-log plot of the stress-strain curve would yield a slope of (n) of 0.22 in the area of uniform plastic deformation. UNS A95456 Source: Alcoa, Aluminum Research Laboratory, New Kensington, PA
o
0.24
Strain, in./in.
o
12
Strain, 0.001 in./in.
WA.161 5456-0 aluminum aJ/oy sheet and plate, tensile and compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
25
o
14 Tension1and
28
--
20
15 -'" rñ
'" ~
10
5
56
70
compr~ssion'---..
'---~ 1/
'¡ji
42
I
~
140
105
I I
Tested at room temperature. Test direction: longitudinal and long transverse. Typical. Ramberg-Osgood parameter, n(longitudinal and long transverse, tension) = 50; n(longitudinal and long transverse, compression) = 50. UNSA95456
., o-
:2
'"~
70
35
11 2
10 8 6 Strain, 0.001 in./in. 6 Compressive tangent modulus, 10 psi 4
o
12
(j)
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-244
Wrought Aluminum (WA)/397
--
WA.162 5456-0 aluminum alloy extrusion, tensile and compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
25
20
15
~
'"
~
10
5
o
14
""I
28
42
~
56
70
K v 1----
140
1----
I I
Tested at room temperature. Test direction: longitudinal and long transverse. Typical. Ramberg-Osgood parameter, n(longitudinal and long transverse, tension) = 13; n(longitudinal and long transverse, compression) = 13. UNSA95456
~
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-244 105
ro
o..
\
~
~'"
70
en
35
v
2
4
6
8
10
o
12
Strain, 0.001 in.lin. Compressive tangent modulus, 106 psi
WA.163 5456-Hl11 aluminum alloy extrusion, tensile and compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
50 0,-----,14,-----,28------,42------5,6------7,0------,8\50
Tested at room temperature. Test direction: L, longitudinal; LT, long transverse. Typical. Ramberg-Osgood parameter, n(L, tension) = 32; n(LT, tension) = 16; n(L, compression) = 9.5; n(LT, compression) = 16. UNSA95456
1-----+-:-::::-;::::.::::;:"-+--\.----+----+-----+-----128o
210
.¡¡;
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-245 ro
o..
-"
~
'"
~
'"
éií
140
~-T--_r----~~----~----~------~1------170
~·----~2~----~4~----~6~----~8------1~0~--~1~ Strain, 0.001 in.lin. Compressive tangent modulus, 106 psi
~
398/Wrought Aluminum (WA)
70
~
60
50
~ ,,; 40
§
.~
/
~
20
~ ~~
I
V
r--~inal
V
420 \
I I I I I
J)o
30
10
~
(
(f)
~
.l!1
WA.164 5456-H321 aluminum alloy plate, tensile stress-strain curves
490
350 C\l
a.. 280 ::¡;
ui
>-O
~
~
(l)
210
1I
~
c:
~
140
70
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essentially identical for both the true and nominal curves. YS, yield strength. Nominal thickness: 19.05 mm (0.750 in.) diam. Test specimen diam, 12.7 mm (112 in.). Gage length: 50.8 mm (2 in.). Nominal tensile strength, 400 MPa (58.0 ksi). True tensile strength, 452 MPa (65.6 ksi). Nominal yield strength (0.2% offset), 247 MPa (35.8 ksi). Elongation (in 50.8 mm, or 2 in.), 13.5%. Reduction of area, 17%. True strain at maximum load, 12.0%. A log-log plot of the stress-strain curve would yield a slope of (n) of 0.24 in the area of uniform plastic deformation. UNS A95456 Source: Alcoa, Aluminum Research Laboratory, New Kensington, PA, Aug 1956
J.
0.02
0.04
2
4
0.06
0.08
0.10
0.12
o
0.14
Strain, in.lin.
o
6
8
10
Strain, 0.001 in.lin.
WA.165 5456-H321 aluminum alloy plate, tensile and compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
5oor-----~1r4----_,28------,42------5T6------7TO----_,8\50
40f------...j
Tested at room temperature. Test direction: L, longitudinal; LT, long transverse. Typical for plate thickness 15.875-31.750 mm (0.625-1.250 in.). Ramberg-Osgood parameter, n(L, tension) = 42; n(LT, tension) = 16; n(L, compression) = 7.0; n(LT, compression) = 11. UNSA95456
~r+------+_----_+----~280
210
30
C\l
a..
'00 -'" ui
::¡; ui (f)
(f)
~
~
1ií
(J)
140
20
10f---+--~-----4------+------+------~----~70
L-----~2------~4------~6------~8------~----~1~
Strain, 0.001 in.lin. Compressive tangent modulus, 106 psi
Source: MIL·HDBK-5H, 1 Dec 1998, p 3-245
Wrought Aluminum (WA)/399
80
560
WA.166 6013-T4 aluminum alloy sheet, tensile true stress, true strain curve
70
490
Sheet thickness: 1.60 mm (0.063 in.). Composition: AI0.90Mg-0.80Si-0.85Cu-0.50Mn. UNS A96013
420
Source: J.w. Hardy, "Formability of Aluminum Alloy 6013 Sheet," Report MDC H5866, McDonnell Douglas Space Systems Co., Feb 1990. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3226, CINDASlPurdue University, 1995, p 8
60
50
V
~ ,¡;
/
~ 40 1ñ
~
-
~
350
'"
o.. ::E 280
/
Q)
2
J- 30
......
Q)
:::l
210 ¡!:
20
140
10
70
o
O
gf
~
0.05
0.10
0.15
o
0.20
0.25
1219
1524 16.0
True strain
WA.167 6013-T4 aluminum alloy sheet, loaddisplacement curve (tensile test)
Displacement, mm
o
3600
305
610
914
2400
10.7
f:!
'Ci
'o" --'
1200
o
O
Test direction: longitudinal. Specimen width: 12.7 mm (0.5 in.); thickness: 2.032 mm (0.080 in.). Gage length: 50.8 mm (2.0 in.). Ultimate tensile strength (Ftu): 336.4 MPa (48.8 ksi). Tensile yield strength (Fty): 215.8 MPa (31.3 ksi). Elongation: 21.8%. Electrical conductivity: 38.1 %IACS. Water quenched. Composition: AI-0.90Mg-0.80Si-O.85Cu-0.50Mn. UNSA96013
/'
....----
0.12
¡.--
0.24
\ 0.36
Displacement, in.
z
'"'Ci
'o"
--'
\
0.48
5.3
o
0.60
Source: J.T. Gutierrez, B.F. Larson, and J.F. Charles, "Fracture Mechanics Forming and Weld Properties for 6013 Sheet," Report MDC K0818, Douglas Aircraft Co., Dec 1989. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3226, ClNDAS/Purdue University, 1995, p 8
400/Wrought Aluminum (WA)
Displacement, mm 9.14 6.10
3.05
Test direction: long transverse. Specimen width: 12.7 mm (0.5 in.); thickness: 2.032 mm (0.080 in.). Gage length: 50.8 mm (2.0 in.). Ultimate tensile strength (FllJ 340.6 MPa (49.4 ksi). Tensile yield strength (Fty ): 197.9 MPa (28.7 ksi). Elongation: 22.6%. Electrical conductivity: 38.2%IACS. Water quenched. Composition: Al-0.90Mg-0.80Si-0.85Cu-0.50Mn. UNSA96013
10.7
2400
1200
WA.168 6013-T4 aluminum alloy sheet, loaddisplacement curve (tensile test)
1524 16.0
12.19
v--
/
~
\
z
""
.¿ o ...J
1\
\
0.24 0.36 Displacement, in.
0.12
0.48
'"
5.3
o
0.60
WA.169 6013-T6 aluminum alloy sheet, tensile stress-strain curves
560
80
Tested at room temperature. Typical for specimen thickness: 0.254-6.325 mm (0.010-0.249 in.). RambergOsgood parameter, n(longitudinal, tension) = 21; n(long transverse, tension) = 15. UNS A96013
420
60 Longitudina~
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-248
~e
1/
20
/
'"
o..
~
280
~
1/ 2
4
140
8 6 Strain, 0.001 in./in.
Source: J.T. Gutierrez, B.F. Larson, and J.F. Charles, "Fracture Mechanics Forrning and Weld Properties for 6013 Sheet," Report MDC K0818, Douglas Aircraft Co., Dec 1989. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3226, CINDAS/Purdue University, 1995, p 8
10
Wrought Aluminum (WA)/401
Compressive tangent modulus, GPa 56 28 42
14
60
/'
---
1/
20
V V 4
2
WA.170 6013-T6 aluminum alloy sheet, compressive stress-strain and compressive tangent modulus curves
84
560
Tested at room temperature. Typical for specimen thickness: 0.254-6.325 mm (0.010-0.249 in.). RambergOsgood parameter, n(longitudinal, compression) = 21; n(long transverse, compression) = 23. UNS A96013
420 transv~e
Longitudinal and long
"'--r---
70
____
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-249
Longitudinal
LOngtransve~
ca
a.
:2 280 ui
~
140
8
6
10
Strain, 0.001 in.lin. Compressive tangent modulus, 106 psi
60
WA.171 6013-T6 aluminum alloy sheet, tensile stress-strain curves
420 Longitudinal
~-
50
40
/
20
10
/
/
/'
~ong transverse
350
Composition: AI-0.90Mg-0.80Si-0.85Cu-0.50Mn. UNSA96013
280
Source: "A1coa A1uminum Alloy 6013," A1coa Green Letter No. 225, Dec 1987. As pub1ished in Aerospace Structural Metals Handbook, Vo13, Code 3226, CINDAS/Purdue University, 1995, p 8
&.
:2 ui
"' "'
210 ~
1/
(1)
~ ~ 140
70
2
4 6 Strain, 0.001 in.lin.
8
402/Wrought Aluminum (WA)
WA.l72 6013-T6 aluminum alloy sheet, loaddisplacement curve (tensile test)
Displacement, mm 3000
o
2.29
457
'\
2000
1000
50
._ 40
Xi gf
~
~ 30
'c;; VJ
l'!
a. E
10
/
1143 13.3
8.90
z
-"
1\
0.27 0.18 Displacement, in.
60
20
\
9.14
-otU .3
/
/ V
/
1\
0.36
o
WA.173 6013-T6 aluminum alloy sheet, compressive stress-strain curve
420
---
Test direction: longitudinal and long transverse. Composition: Al-0.90Mg-0.80Si-0.85Cu-0.50Mn. UNS A96013
350
280
& ::;¡;
~
210 .~ VJ VJ
l'!
c. E o 140 ü
4
6
Strain, 0.001 in.lin.
Source: J.T. Outierrez, B.E Larson, and J.E Charles, "Fracture Mechanics Forrning and Weld Properties for 6013 Sheet," Report MDC K0818, Doug1as Aircraft Co., Dec 1989. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3226, CINDASlPurdue University, 1995, p 8
0.45
70
2
Test direction: longitudinal. Specimen width: 12.7 mm (0.5 in.); thickness: 2.032 mm (0.080 in.). Gage length: 50.8 mm (2.0 in.). Ultimate tensile strength (Ftu ): 398.5 MPa (57.8 ksi). Tensile yield strength (Fty ): 368.1 MPa (53.4 ksi). Elongation: 11.0%. Electrical conductivity: 42.9%IACS. Water quenched. Composition: Al-0.90Mg-0.80Si-0.85Cu-0.50Mn. UNSA96013
4.45
\
0.09
8
686
8
Source: "Alcoa A1uminum Alloy 6013," Alcoa Oreen Letter No. 225, Dec 1987. As published in Aerospace Structural Metals Handbook, Vo13, Code 3226, CINDASlPurdue University, 1995, p 10
Wrought Aluminum (WA)/403
-
50
40
WA.174 6061-T62 aluminum alloy extrusion, tensile stress-strain curves (full range)
420
60
V
Longitudinal
r --
Specimen thickness: 3.2-41.3 mm (Ys-l% in.). Composition: AI-IMg-O.65Si-0.25Cu-O.20Cr. UNSA96061
350
Long transverse 280
'"
a.
:2
210 ui Ul !!:!
Source: 0.1. Brownhill, 0.1. Davies, and D.O. Sprow1s, "Mechanica1 Properties, Including Fracture Toughness and Fatigue and Resistance to Stress Corrosion Cracking of Stress Re1ieved and Stretched A1uminum Alloy Extrusions," AF Contract AF33(615)-3580, AFML TR68-34, Feb 1970. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3206, CINDASlPurdue University, 1995, p 6
éi5
20
140
10
70
0.02
0.04 0.06 Strain, in.lin.
420
50
350
40
/
~ Ul
~
o
0.10
60
I
ui
0.08
30
20
10
/
/
Test direction: L, longitudinal; LT, long transverse. Specimen thickness: 3.2-41.3 mm (Ys-l% in.). Composition: AI-IMg-O.65Si-O.25Cu-O.20Cr. UNSA96061
~~compression
V
i' L, tension
280 " LT, tension
'"
a.
:2 210 ui Ul !!:!
1/
éi5
140
70
2
WA.175 6061-T62 aluminum alloy extrusion, tensile and compressive stress-strain curves
4
6 8 Strain, 0.001 in.lin.
10
Source: O.J. Brownhill, 0.1. Davies, and D.O. Sprow1s, "Mechanica1 Properties, Including Fracture Toughness and Fatigue and Resistance to Stress Corrosion Cracking of Stress Relieved and Stretched A1uminum Alloy Extrusions," AF Contract AF33(615)-3580, AFML TR68-34, Feb 1970. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3206, CINDASlPurdue University, 1995, p 7
404/Wrought Alurninurn (WA)
60
420
50
350
WA.176 6061-T651 aluminum alloy extrusion, tensile stress-strain curves (full range)
Specimen thickness: ::;12,675 mm (::;0.499 in.), Composition: AI-IMg-O,65Si-0.25Cu-O,20Cr. UNSA96061
Longitudinal
40
~
Long transverse
r
280
a.'"
~
:¡;
g¡- 30
210
~
1i5
rñ
Source: 0.1, Brownhill, 0.1, Davies, and D,O, Sprowls, "Mechanical Properties, Including Fracture Toughness and Fatigue and Resistance 10 Stress Corrosion Cracking of Stress Relieved and Stretched Aluminum Alloy Extrusions," AF ContraetAF33(615)-3580, AFML TR68-34, Feb 1970, As published in Aerospace Structural Metals Handbook, Vol 3, Code 3206, CINDAS/Purdue University, 1995, p 7
~
1i5 20
140
10
70
0,02
0,04
0,06 Strain, inJin,
0,08
50
40
I
30 -'" rñ
'"~
1i5 20
WA.l77 6061-T651 aluminum alloy extrusion, tensile and compressive stress-strain curves
280
Test direction: L, longitudinal; LT, long transverse. Specimen thickness: ::;12,675 mm (::;0.499 in,), Composition: AI-IMg-O,65Si-0.25Cu-0.20Cr. UNSA96061
r i : 7 L T , tensio1n L, tension and compiession
210
rñ
'"
140
70
2
a. '"
:¡;
/
V
350 \. LT, comjression
,j
'00
10
---
o
0,10
6 4 Strain, 0,001 inJin,
8
~
Souree: O,J, Brownhill, 0.1, Davies, and D.O, Sprowls, "Mechanical Properties, Including Fracture Toughness and Fatigue and Resistanee to Stress Corrosion Cracking of Stress Relieved and Stretched Aluminum Alloy Extrusions," AF Contraet AF33(615)-3580, AFML TR68-34, Feb 1970, As published in Aerospace Structural Metals Handbook, Vol 3, Code 3206, CINDAS/Purdue University, 1995, p 7
Wrought Aluminum (WA)/405
60
420
50
350
r--
40 '00 -"
~
Longitudinal
WA.178 6061-T651 aluminum alloy extrusion, tensile stress-strain curves (full range)
Specimen thickness: ~76.2 mm (~3.0 in.). Composition: AI-IMg-O.65Si-O.25Cu-O.20Cr. UNS A96061
TransvLse
280
V
C\l
c..
::2:
30
210
20
140
10
70
o
O
0.02
0.04
0.08
0.06
Source: 0.1. Brownhill, 0.1. Davies, and D.O. Sprowls, "Mechanical Properties, Inc1uding Fracture Toughness and Fatigue and Resistance to Stress Corrosion Cracking of Stress Relieved and Stretched Aluminum Alloy Extrusions," AF Contract AF33(615)-3580, AFML TR68-34, Feb 1970. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3206, CINDAS/Purdue University, 1995, p 7
~
o
0.10
Strain, in./in.
50
~L" lp~.o"
WA.179 6061-T651 aluminum alloy extrusion, tensile and compressive stress-strain curves
350
"d
Fl: I
40
LT,
~M;OO
Test direction: L, longitudinal; LT, long transverse. Specimen thickness: ~76.2 mm (?:3.0 in.). Composition: AI-IMg-O.65Si-O.25Cu-O.20Cr. UNS A96061
280
LT, compression
30 '00 -"
~
(f)
20
10
/ V
210
V
140 éií
70
0.02
&.
::2: ~~
0.04
0.06
Strain, in./in.
0.08
o
0.10
Source: O.J. Brownhill, 0.1. Davies, and D.O. Sprowls, "Mechanical Properties, Including Fracture Toughness and Fatigue and Resistance to Stress Corrosion Cracking of Stress Relieved and Stretched Aluminum Alloy Extrusions," AF Contract AF33(615)-3580, AFML TR68-34, Feb 1970. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3206, CINDAS/Purdue University, 1995, p 8
406/Wrought Aluminum (WA)
WA.180 6061-T6 aluminum alloy, tensile stressstrain curves at room and elevated temperatures
350
50
Room temperature
40
Composition: AI-IMg-O.6Si-O.25Cu-O.20Cr. UNSA96061
280
212°F (100 OC) 300°F (149 OC) 400°F (204 OC) .¡¡;
210
30
ro
Il..
'"uf
:2 uf
I/l
I/l
~
~
500°F (260 OC)
Ci5
140
20
600°F (316 OC) 10
70
700 °F (371°C) O
00 Strain, 0.001 in./in.
en
"Typical Tensile Stress-Strain Curves for 6061-T6 at Room Temperature, 212, 300, 400, 500, 600, and 700 F," Physical Test No. 010758-G Data Sheets, 6 and 31 March 1958. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3206, CINDAS/ Purdue University, 1995, p 8
Wrought Aluminum (WA)/407
WA.181 6061-T6 aluminum alloy sheet, stress-strain curves at room and elevated temperatures
8or---------.---------,-----~~_r--~=_--_,560
--423 °F (-253 OC)
Tested at low temperature. Test direction: longitudinal (top); transverse (bottom). Sheet thickness: 2.54 mm (0.100 in.). Composition: AI-IMg-0.6Si-0.25Cu-0.20Cr. UNSA96061
I -320°F (-196 OC)
60 l--~~-~~~::::==+===::i._____--__1420
F.R. Schwartzberg et al., Cryogenic Matenals Data Handbook, ML-
~
:i~
&.
:2
40 I-V----------+---------+----------+---------l280 rñ ~
~
en
O~--------~--------~--------~---------"O
~
:i
~
~
:2
40 t-V----------+--'-------+----------+----------j 280 .;
ro~
(J)
°0~------~0~.0~8~----~0~.1~6------~0~.2~4------~0.3·9 Slrain, in./in.
TDR-64-280, Aug 1964, Suppl. 1, Feb 1965. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3206, CINDAS/Purdue University, 1995, p 9
408/Wrought Aluminum (WA)
Temperature,
oc
8o.r----~24~0~-------~1r29~--------T18~------~9\60
WA.182 6061-T651 aluminum alloy plate, effect of cryogenic temperatures on tensile properties C\l
o..
::lE ~
!:S"
• o
.s=
rn e
~
Longitu dina I
!:S"
Transverse
.s=
rn e
~ 60f-----I-"'=<--------f-------+--------j 420 ~ ~
.!!! "00
"c;,¡
e
e
!!
!!
15
~
E
E
3 40
280
60
420
I~
~
1--.
•
140
20 60
g El
:!e
o f¡j 40 Ol
e O Oi "C e
r /
~
RA
~
C\l
-
~ 2O ~ ~ C\l
~
C\l
'O e
E
O
t5:::!
~
O
-400
-200 Temperature, °F
o
200
3
Tested to -269 oC (-452 °F). Plate thickness: 31.75 mm (l ~ in.). Composition: AI-IMg-O.65Si-O.25Cu-O.20Cr. UNSA96061 Source: J.O. Kaufman, K.O. Bogardus, and E.T. Wanderer, Tensile Properties and Notch Toughness of Aluminum AIloys at -452F in Liquid He, Adv. Cryogenic Eng., Vol 13, 1968, P 294. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3206, CINDASI Purdue University, 1995, p 9
Wrought Aluminum (WA)/409
WA.183 6061-0 aluminum alloy, effect of exposure and test temperature on tensile properties
Temperature, oC
-240 40
o
-129
'"
-18
93
204
316
Exposure up to 10,000 h. Composition: AI-IMg-0.6Si0.25Cu-0.20Cr. UNS A96061
r-.....
~
'-
ir] ._--11----'-----+-.1-----+-1·__L 8
o
~
1.
~oo
80
El ~
§ 40 ~
el C
o
¡¡j
~oo
-- ---200
/
200 Temperature, °F
~oo
/
400
ro
[0 ir
./
8
o
o
Source: "Mechanical Properties at Various Temperatures of 6061-0," Data sheet, Alcoa Research Laboratories, I Feb 1956. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3206, CINDAS! Purdue University, 1995, p 9
600
800
410/Wrought Aluminum (WA)
WA.184 6061-T4 aluminum alloy sheet, effect of exposure and test temperature on tensile properties
Temperature, oC
-240 60 :,
!oS" ==Ol 40
-18
-129
~r-...
e
~
--
1ñ .!!! - - - 1/2h .~ 20 t-- _____ 100 h
.2l .2l ro
204
316
427 420
ro
a.
::¡; :J
!oS"
'-----
280 == Ol e
~",.....
.~
~
\\
.
.""
.~., "v', ."
_._-- 1000 h -.--.¡10,000h
E
"" S
93
'.:...~
O
1ñ .!!!
140 .~ .2l
~
'* E
O
"" S ro
280 ~
...............
--
¿. ~ "
.""
,.',\ ' ...........,',:.....;..... \
~
80r-----,------,------r-----,---~_T~r__.
i
·'1
.' .' I /
-
/
~ -'./ / ~ 40~-----+------4_------~----_+~r_~~_?L-~ o 1/,/ V ~ ----t------4------~----__~v~~ e
o
[jJ
~OO
-200
O
200 Temperature, °F
400
600
800
Composition: AI-IMg-O.6Si-O.25Cu-O.20Cr. UNSA96061 Source: "Mechanical Properties at Various Temperatures of 6061-T4 and 6062-T4," Data sheet, Aleoa Research Laboratories, 23 Feb 1956. As published in Aerospace Structural Metals Handbook, Vo13, Code 3206, CINDAS/Purdue University, 1995, p 10
Wrought Aluminum (WA)/411
Temperature, oc
-240
93
204
316
427
60~~--~~----~------~----~------~------.420
m
a.
:::¡; ~::>
::>
~
~
e
e
'§, 40 1----4-------+-----+--='....-=----+------+-------1 280 '§,
~
..'l2 .~ $
"* E 5
____
20
i..'l2
1/2h
140 .~
- - - - - 100 h
$
- .- .-
1000 h -.-_.- 10,000h
OL-____- L_____....L______J.-____.......J.______.....J...._.-:..-.---l O 60
--
420
t---
~ '.\, ,.
"~ .., ........ '"',,'.,............. ,\
""
~
o 80
. I
6' "
I
.' .'
-; 40 .."..~
~
C)
o
.'
·'1 . II / . I /
,....,V
l'/,,/
O
fii
I
~
e
/,;/
O
¡¡j
~OO
-200
o
200 Temperature, 'F
400
600
800
"* E 5
WA.185 6061-T6 aluminum alloy, effecl of exposure and test temperature on tensile properties
Composition: AI-IMg-O.6Si-O.25Cu-O.20Cr. UNSA96061 Source: "Mechanical Properties at Various Temperatures of 6061-T6 Products," Data table, Aleoa Research Laboratories, 6 Dec 1960. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3206, CINDASlPurdue University, 1995, p 10
4121Wrought Aluminum (WA)
RT
70
Temperature, oC r -__2,o_4________2,3_2_________ 26ro________-,28~90
WA.186 6061-T6 aluminum alloy sheet, effect of test temperature on stress to produce various amounts of small plastic strain in tension
Sheet thickness: 3.17 mm (l/8 in.). RT, room temperature. Composition: AI-IMg-0.6Si-0.25Cu-0.20Cr. UNSA96061
~-----.~~--------4_--~~--~--------~420
1~--------~--------~--------~~------~350
Plastic strain O 10-6 .¡¡; 40 ~--------+_--------_+--- L':. 5 X 10-6 -:. • 10X10-6
~
280
8:.
Source: R.E. Maringer and M.M. Cha, "Stability of Structural Materials for Space Craft Application," NASA CR 97844, N ational Aeronautics and Space Administration, Apri11968. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3206, CINDASlPurdue University, 1995, p 10
:2
O 2000 X 10-6
W30~~~~--~~~~~~----------+_--------_l210
cñ
~
20~~------~--------~~--~'_~J_---------4140
10~--------+_--------_+--------~~--------~70
r---~---------L---------L--------~O
400
450 Temperature, °F
500
550
WA.187 6061-T6 aluminum alloy ciad sheet, compressive stress-strain curves
50 r---------,----------r-----------,,--------.,---------, 350 200°F (93 OC)
Tested at 93,204, and 316 oC (200, 400, and 600°F) in long transverse direction. Composition: AI-IMg-0.6Si0.25Cu-0.20Cr. UNS A96061
h
40~------+_------~~~--~~~--_r------~280
400°F (204 OC)
.¡¡; -'"
30 ~------t_--Jf---t~~=;1~/~2'~an~d~2~h--_t------_¡210 10 h
(f)
~
ro
g¿
100-1000 20 ~------~~----+-------+-------_r------_l140
1/2 h exposure 70
10 10 h
2
4 6 Strain, 0.001 in./in.
8
O
10
~ W
Source: Metallic Materials and Elements for Aerospace Vehicle Structures, MIL-HDBK-5B, FSC 1500, Sept 1971. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3206, CINDASI Purdue University, 1995, p 10
Wrought Aluminum (WA)/413
WA.188 6061-T6 aluminum alloy sheet, compressive stress-strain curves
5or-------~------,_------,_------_r------_,350
Tested at 149 and 260 oc (300 and 500 °P) in long transverse direction. Composition: A1-1Mg-0.6Si0.25Cu-0.20Cr. UNS A96061
'-+----1280
40r--------r-------+----~
210
CIl
a..
~
Source: Metallic Materials and Elements for Aerospace Vehicle Structures, MIL-HDBK-5B, FSC 1500, Sept 1971. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3206, CINDAS/ Purdue University, 1995, p 11
::a;
rñ
rñ
'" ~
'"f!?
en 140
1i5
L-------2L-------41-:------~6------~8------~1f Strain,
0.001 in.lin.
"emperature, oC
60
- 240
-184
-
129
-73
WA.189 6061-T6 aluminum alloy sheet, effect of low temperature on shear strength
-18
Test direction: Longitudinal and transverse. Sheet thickness: 2.54 mm (0.100 in.). Composition: A1-1.0Mg-0.6Si0.25Cu-0.20Cr. UNS A96061 50
'00
.><
,S O>
e
~
40
\
I~"'-
en 30
20
,S el
''
ti;
ID
~
-400
-300
ER Schwartzberg et al., Cryogenic Materials Data Handbook, MILTDR-64-280, Aug 1964, and Suppl. No. 1, Feb 1965. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3206, CINDAS/ Purdue University, 1995, p 11
350
280 ~
1ií ti;
~ t--
-200 Temperature, 'F
-100
ID
~
-
o
en 210
140 100
414/Wrought Aluminum (WA)
25
WA.190 6061-0 aluminum alloy rod, tensile stressstrain curves
175
True 20
~
.¡¡; ~
IV
15
rñ
'"e! u; ~ .¡¡; e
~ 10
5
140
V
Nominal
~
~
C\l
..
\ I
v~k;
I
o
~
~ .¡¡;
70
35
I I I I I 0.08
0.12 Strain, in./in.
0.16
0.20
g¡
rñ
I I I I
V
0.04
105
e
~
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essentially identical for both the true and nominal curves. YS, yield strength. Test specimen diam, 12.7 mm (1/2 in.). Gage length: 203.2 mm (8 in.). Nominal tensile strength, 123 MPa (17.8 ksi). True tensile strength, 143 MPa (20.7 ksi). Nominal yield strength (0.2% offset), 43 MPa (6.2 ksi). Elongation (in 50.8 mm, or 2 in.), 23.4%. Reduction of area, 75%. True strain at maximum load, 18.2%. A log-log plot ofthe stress-strain curve would yield a slope of (n) of 0.22 in the area of uniform plastic deformation. UNS A96061 Source: Alcoa, Aluminum Research Laboratory, New Kensington, PA, July 1954
o
0.24
2 4 Strain, 0.001 in./in.
350
50
WA.191 6061-T4 aluminum alloy rod, tensile stressstrain curves
True
40
(
~
l/
..J . "-).-O'" ~
~ r--
Nominal 280
\ I
I
I I I
~
Ir
I
I
10
V
0.01
o
I I I
I I 1 0.02
0.03
2 4 6 Strain. 0.001 in./in.
0.04 0.05 Strain, in./in.
0.06
0.07
0.08
70
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essentially identical for both the true and nominal curves. YS, yield strength. Test specimen diam, 12.7 mm (1/2 in.). Gage length: 203.2 mm (8 in.). Nominal tensile strength, 285 MPa (41.4 ksi). True tensile strength, 307 MPa (44:5 ksi). Nominal yield strength (0.2% offset), 190 MPa (27.6 ksi). Elongation (in 50.8 mm, or 2 in.), 17.2%. Reduction of area, 54%. True strain at maximum load, 7.7%. A log-log plot ofthe stress-strain curve would yield a slope of (n) of O.11 in the area of uniform plastic deformation. UNS A96061 Source: Alcoa, Aluminum Research Laboratory, New Kensington, PA, July 1954
o
0.09
Wrought Aluminum (WA)/415
WA.192 6061-T6 aluminum alloy rod, lensile slressstrain curves
50.-----,------,-----,,-----,------,-----,350
280
\ \ t\l
210 ~
,Ji
~'"
~ .¡¡;
140 c: ~
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essentiaHy identical for both the true and nominal curves. YS, yield strength. Test specimen diam, 12.7 mm (112 in.). Gage length: 203.2 mm (8 in.). Nominal tensile strength, 307 MPa (44.5 ksi). True tensile strerigth, 334 MPa (48.5 ksi). Nominal yield strength (0.2% offset), 266 MPa (38.6 ksi). Elongation (in 50.8 mm, or 2 in.), 10.8%. Reduction of area, 49%. True strain at maximum load, 8.6%. A log-log plot of the stress-strain curve would yield a slope of (n) of 0.13 in the area of uniform plastic deformation. UNS A96061 Source: A1coa, Aluminum Research Laboratory, New Kensington, PA, July 1954
0.02 O
-18
2
0.04
0.06 Strain, in./in. 4 6 Strain. 0.001 in./in.
o
0.10
0.08
0.12
8
38
427
100~--~--~~--.r.,~r_---r--~~--~--~
WA.193 6061-T6 aluminum alloy, all products, effect of exposure al elevated tempera tu re on room lemperature lensile ultimate strength
Exposure up to 10,000 h, as indicated. AH products. UNSA96061 Source: MIL-HDBK-5H, 1 Dec 1998, p 3-264
Cl
~ ~
Il.
°OL----L·----L----L·--~L---~--~--
100
200
300 400 500 Temperature, °F
600
__~__~ 700
800
416/Wrought Aluminum (WA)
50
WA.194 6061-T6 aluminum alloy sheet, tensile stress-strain curves
350
LO",!tm_= 40
.¡;;
30
-'"
rñ
m ~
iií
20
/
10
V
/
~
I
Tested at room temperature. Typical for sheet thickness ~6.325 mm (~0.249 in.). Ramberg-Osgood parameter, n(longitudinal, tension) = 50; n(long transverse, tension) = 21. UNS A96061
280
Longitudinal
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-267 210
ro D.. ~
rñ
~
140 iií
70
2
4
6
8
o
10
Strain, 0.001 inJin.
20
.¡;;
/'
15
f-
rñ
m ~
10
5
~¡--_
2-0 h
j'' ' '""
/
140
105
rñ
m ~
100 h exposure 70
35
2
4
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-269 ro D.. ~
-
r
Tested at 260 oC (500 °P). Test direction: longitudinal. Typical for sheet thickness ~3.l75 mm (~0.125 in.). Ramberg-Osgood parameter, n(2-5 h exposure) = 13; n(lO h exposure) = 13); n(lOO h exposure) = 13. UNSA96061
10 h exposure
~
-'"
iií
WA.195 6061-T6 aluminum alloy sheet, tensile stress-strain curves
175
25
6
Strain, 0.001 inJin.
8
o
10
iií
Wrought Aluminum (WA)/417
WA.196 6061-T6 aluminum alloy sheet, compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa 500~----~1~4-----;28~_---~42~--__5~6~----7TO~__~~350
Tested at room temperature. Test direction: L, longitudinal; LT, long transverse. Typical for sheet thickness ::;6.325 mm (::;0.249 in.). Ramberg-Osgood parameter, n (L, compression) = 19; n(LT, compression) = 2l. UNSA96061
40~~~~----~---~~~-----4------+-----~280
210
30
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-269 ro
a.
~
::¡;
>Ji
>Ji
(/)
"'~
~
ro
20
140
ro
10~-+---~----~~----~-----4------~----~70
L------2L-----~4~----~6------~8------~10L---~1}
Strain, 0.001 in.lin. Compressive tangent modulus, 106 psi
50
40
o
14
'<.....
30 >Ji (/)
~
CI)
20
10
/
1/
70
WA.197 6061-T6 aluminum alloy sheet, tensile and compressive stress-strain and compressive tangent modulus curves
84 350
Tested at room temperature. Test direction: L, longitudinal. Typical. Ramberg-Osgood parameter, n(L, tension) = 50; n(L, compression) = 18. UNS A96061
L, compres,sion ''"''
/
~
Compressive tangent modulus, GPa 28 42 56
iOO~
I
280
----
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-270
~
"'\
210
>Ji
140
70
2
ro
a.
::¡;
4
6
8
Strain, 0.001 in.lin. Compressive tangent modulus, 106 psi
10
~
418/Wrought Aluminum (WA)
50
WA.198 6061-T6 aluminum alloy extrusion, tensile stress-strain curves
350 Longitudinal
~
40
/
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-271
1/
30 ~ <ñ
'"~
ro
20
10
V
210
ro a. ::¡; <ñ
~'"
140
/
V
Tested at room temperature. Typical for aH thicknesses. Ramberg-Osgood parameter, n(longitudinal, tension) = 34; n(long transverse, tension) = 29. UNS A96061
Long transverse- 280
CfJ
70
2
4
6
8
Strain, 0.001 in./in.
50°r-_ _ _1,4_ _-,28______4,2______5,6______7,O____-,8\50
WA.199 6061-T6 aluminum alloy extrusion, compressive stress-strain and compressive tangent modulus curves
l---=l::~;::~~::::=f=-. . . . h-----t-------J 280
Tested at room temperature. Typical for aH thicknesses. Ramberg-Osgood parameter, n(longitudinal, compression) = 38; n(long transverse, compression) = 28. UNSA96061
Compressive tangent modulus, GPa
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-271
210 ro a.
'00 .:.: <ñ
::¡; <ñ
'"~
'"~
ro
140
1----1---+------j----+-----+---~---i
70
L------2L-----~4------~6------~8------1~0----~1~
Strain, 0.001 in./in. Compressive tangent modulus, 106 psi
ro
Wrought Aluminum (WA)/419
40
.¡¡;
WA.200 6061-T6 aluminum alloy sheet, tensile stress-strain curve (full range)
350
50
",--
-
~
Tested at room temperature. Test direction: longitudinal. Typical. UNS A96061
t-,
"
\
280
Source: MIL-HDBK-5H, 1 Dec 1998. p 3-273
210
30
a.
-'"
:2
1/)
~
éií 20
140
10
70
0.02
0.04
0.06
0.10
0.08
~
o
0.12
Strain, in./in.
50
40
.¡¡;
WA.201 6061-T62 aluminum alloy extrusion, tensile stress-strain curves (full range)
350 Longitudinal
V
t-_ . .
l--:::~
t::--- 'Long transverse
1-,......
"',,"
\
30
Tested at room temperature. Typical for all thicknesses . UNSA96061
280
"
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-274
210
a.
-'"
:2
~
j
en 20
140
10
70
0.02
0.04
o.m,
0.08 Strain, in./in.
0.10
0.12
0.14
o
0.16
en
420/Wrought Aluminum (WA)
WA.202 606l-T651X, aluminum alloy extrusion, tensile and compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
5oor------1r4-----.28------4~2------5T6------7~0----~8\50
Tested at room temperature. Test direction: L, longitudinal; LT, long transverse. Typical for extrusion thickness :'5:12.67 mm (:'5:0.499 in.). Ramberg-Osgood parameter, n(L, tension) = 40; n(LT, tension) = 19; n(L, compression) = 15; n(LT, compression) = 14. UNS A96061 Source: MIL-HDBK-5H, 1 Dec 1998 .¡¡;
30
ro Il. ::¡;
-'"
g
üi
~
'"~
20 ~----~----_4------+_-----+------#_----~140
10~-4--~----~------4------+------~----~70
°OL-----~----~------~-----L------ll-----~O
2
4
6
8
Strain, 0.001 in./in. Compressive tangent modulus,
10
12
106 psi
WA.203 6061-T651X aluminum alloy extrusion, tensile and compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
50°r-----~1r4----~28~----~42~----5T6------7To-----.8\50
Tested at room temperature. Test direction: L, longitudinal; LT, long transverse. Typical for extrusion thickness 276.20 mm (23.000 in.). Ramberg-Osgood parameter, n(L, tension) = 45; n(LT, tension) = 24; n(L, compression) = 40; n(LT, compression) = 32. UNS A96061
h.;;:::::::~E:::::~t::~=t===~===i--1280
I
210 ro
.¡¡;
Il.
::¡;
'"
'~"
~
üi
140
~-4~~----~------4-----_+------~-----70
Strain, 0.001 in./in. Compressive tangent modulus,
106 psi
üi
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-272
Wrought Aluminum (WA)/421
WA.204 6061-T651X aluminum alloy extrusion, tensile stress-strain curves (full range)
350
50 LLgitUdi1,
40
.¡¡; -"
-1--
,.......-: ~
Long tra-;;;,;;;e -
V
........ ~-
~~
280
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-275
210
30
Tested at room temperature. Typical for extrusion thickness :5:12.675 mm (:5:0.499 in.). UNS A96061
c..
:2
gf
U)
~
~
20
140
10
70
0.02
0.04
0.06
0.08
0.10
0.12
iñ
o
0.14
0.16
Strain, in./in.
50
/" 40
WA.205 6061-T651X aluminum alloy extrusion, tensile stress-strain curves (full range)
350
I/'
V
LOO9r~t--
---
--~
--transverse
Lon~,
~
r--_
........
Tested at room temperature. Typical for extrusion thickness 76.20 mm (3.000 in.). UNS A96061
"'x
"x
30
280
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-276
210
~
c..
:2
U)
~
iñ 20
140
10
70
0.02
0.04
0.06
0.08
0.10
Strain, in./in.
0.12
0.14
0.16
o
0.18
1
422/Wrought Aluminum (WA)
16
./
14
,/
~
8
~ .¡¡; e
~
6
-----
/)V
.¡¡; 10
\
, ~
f
,
I
r
I
0.08
0.12
0.16 0.20 Strain, in.lin. 8 12 16 20 Strain, 0.001 in.lin.
-
~
~
.¡¡; 25
0.24
0.28
24
28
Q)
20
~
I
""""1"
~
O
Source: Alcoa, Aluminum Research Laboratory, New Kensington, PA
0.32
o
0.36
280
WA.207 6063-T6 aluminum alloy extruded rod, tensile stress-strain curves
,,
245
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portian of the curves; this expanded portian is essentially identical for both the true and nominal curves. YS, yield strength. Rod diam, 19 mm (3/4 in.). Specimen diam, 12.7 mm (1/2 in.). Gage length: 203.2 mm (8 in.). Nominal tensile strength, 243 MPa (35.3 ksi). True tensile strength, 252 MPa (36.5 ksi). Nominal yield strength (0.2% offset), 214 MPa (31.0 ksi). Elongation (in 50.8 mm, or 2 in.), 10.6%. Reduction of area, 44%. True strain at maximum load, 7.7%. A lag-lag plot ofthe stress-strain curve would yield a slope of (n) of 0.08 in the area of uniform plastic deformation. UNS A96063
210 I I I I I
175
& ::;;
140
~
rñ
I I I
I
I I I I
105 ~
70
35 I I 1 0.06 Strain, in.lin. 246 Strain, 0.001 in.lin.
0.02
0.04
0.08
0.10
'"
~ .¡¡; e
I I
~
O O
28
I
j
I
~
Nominal
....-~ :r,....
I
"'rñ"
5
42
I
35
~ 15
Cií
~ .¡¡; e
I 1
4
~ .¡¡; e
'"~
14
40
10
rñ
56
I I
V o
I I
YS
'"
[L
::;;
I
P
0.04
'"
70
\ \
4
ti
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portian of the curves; this expanded portian is essentially identical for both the true and nominal curves. YS, yield strength. Full specimen size. Test specimen diam, 19 mm (3/4 in.). Gage length: 203.2 mm (8 in.). Nominal tensile strength, 89.6 MPa (13.0 ksi). True tensile strength, 109 MPa (15.8 ksi). Nominal yield strength (0.2% offset), 34 MPa (4.9 ksi). Elongation (in 50.8 mm, or 2 in.), 34.5%. Reduction of area, 85%. True strain at maximum load, 19.0%. A lag-lag plot of the stress-strain curve would yield a slope of (n) of 0.20 in the area of uniform plastic deformation. UNS A96063
84
!
30
98
" ,,
.L
2
WA.206 6063-0 aluminum alloy extruded rod, tensile stress-strain curves
Nominal
~ vo-
12
"'rñ" '"
/
112
~
o
0.12
Source: Alcoa, Aluminum Research Laboratory, New Kensington, PA, March 1953
Wrought Aluminum (WA)/423
WA.208 7010-T7451 aluminum alloy plate, tensile stress-strain curves
8or-------~------,_------_r------_,------_,560
Tested at room temperature. Typica1 for sheet thickness 50.82-139.7 mm (2.001-5.50 in.). Ramberg-Osgood parameter, n(longitudina1, tension) = 13; n(long transverse, tension) = 8.8; n(short transverse, tension) = 8.7. UNSA97010
60~------+-------~-----~~~~---c~-----i420
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-285
g¡
g¡
gf 40 I-------+-------:A'-------+--------t-----------j 280
uf
~
~
20~----~~------~-------~------_t_------~140
~------~------~--------L-------L------~1~
Strain, 0.001 in.lin.
WA.209 7010-T7451 aluminum alloy plate, compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
80°r------1r4-----,2r8-----,42------,56------7TO------,8\60
Tested at room temperature. Typical for sheet thickness 50.82-139.7 mm (2.001-5.50 in.). Ramberg-Osgood parameter, n(longitudina1, compression) = 15; n(long transverse, compression) = 14; n(short transverse, compression) = 14. UNS A97010
60~----+_~~~~~~~~~----_+-----4420
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-285
~ gf 40 ~-----+_-----++------+------+------+-1---__l 280
_
~
~ ::¡; uf
m
V>
(f)
20r-----Tr----~r-----~----~------+-;_--~140
2
4
6
8
Strain, 0.001 in.lin. Compressive tangent modulus, 106 psi
10
424/Wrought Aluminum (WA)
WA.21 O 7010-T7451 aluminum alloy plate, tensile stress-strain curves
8or-------~------~------~------~-------560
Tested at room temperature. Typical for sheet thickness 12.7-38.1 mm (0.50-1.50 in.). Ramberg-Osgood parameter, n(longitudinal, tension) = 12; n(long transverse, tension) = 10. UNS A97010
60~------+_------+-------~~~--~~----~420
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-286
~
&
gf 40 1--------1----------,~------+_------_+_------_I 280
rñ
E w
~
~
W
2
4
6
8
Strain, 0.001 in./in.
WA.211 7010-T7451 aluminum alloy plate, compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
~____~14~____~28~____4~2~____5T6____~7~0____~8~60
Tested at room temperature. Typical for sheet thickness 12.7-38.1 mm (0.50-1.50 in.). Ramberg-Osgood parameter, n(longitudinal, compression) = 14; n(long transverse, compression) = 17. UNS A97010 Source: MIL-HDBK-5H, 1 Dec 1998, p 3-286
~
gf 40
I-----+--~'------+-----_+------+_'\t_--- 280
~
~
gf
~ w
w 201------~----_4------+_----_+------+_+_---
Strain, 0.001 in./in. 6 Compressive tangent modulus, 10 psi
140
Wrought Aluminum (WA)/425
WA.212 7010-T7651 aluminum alloy plate, tensile stress-strain curves
80r-------,-------,-------,--------r------, 560
Tested at room temperature. TypicaI for sheet thickness 50.82-139.7 mm (2.001-5.50 in.). Ramberg-Osgood parameter, n(longitudinaI, tension) = 9.2; n(long transverse, tension) = 9.7; n(short transverse, tension) = 8.2. UNSA97010
6o~------+-------4-------4_~~~~~----~420
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-287
~
gf 40 ~
~'"
I--------+-------~------+_------_+------___j 280
~
ro
CI)
20~------~------4-------4_------~------~140
2
4
6
8
Strain, 0.001 in.lin.
WA.213 7010-T7651 aluminum alloy plate, compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
1000-r-----~1r4----~2r8----~42r-----~56~----7~0~--~84700
Tested at room temperature. Typical for sheet thickness 50.82-139.7 mm (2.001-5.50 in.). Ramberg-Osgood parameter, n(longitudinal, compression) = 13; n(long transverse, compression) = 13; n(short transverse, compression) = 12. UNS A97010
80~-----~----~~-~~~~~~------~----~560
60
420
~
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-287
c.. '"
:2
en
en
~
ro
~
40
280
20~----~----~------~----_+------+_+_--~140
~----~2L-----~4------~6------~8------1~0-i--~1~
Strain, 0.001 in.lin. Compressive tangent modulus, 106 psi
ro
426/Wrought Aluminum (WA)
100
WA.214 7010-T7651 aluminum alloy plate, tensile stress-strain curves
700
80
Tested at room temperature. Typical for plate thickness 12.7-38.10 mm (0.500-1.500 in.). Ramberg-Osgood parameter, n(longitudinal, tension) = 14; n(long transverse, tension) = 9.9. UNS A97010
560
=~ong
Longitudinal
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-288
transverse
60
~ rñ
'"~
ro
40
20
/
/ 2
420
/
ro
[L
:2 rñ
'"
280
~
140
4
6
8
10
o
12
Strain, 0.001 in.lin.
WA.215 7010-T7651 aluminum alloy plate, compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
80°,-____,14______,28______4 2______5 6______7,O____-.8\60 T
T
Tested at room temperature. Typical for plate thickness 12.7-38.10 mm (0.500-1.500 in.). Ramberg-Osgood parameter, n(1ongitudina1, compression) = 12; n(long transverse, compression) = 20. UNS A97010 Source: MIL-HDBK-5H, 1 Dec 1998, p 3-288
~
~
~
~
gf 40 I-------I------+t------+------I-------t--IH----j 280 rñ
201------~----~------+_----_I_------r_+---_J140
Strain, 0.001 in.lin. 6 Compressive tangent modulus, 10 psi
Wrought Aluminum (WA)/427
WA.216 7049/7149-T73 aluminum alloy die forging, tensile stress-strain curves
700
100
80
Tested at room temperature. TypicaI for forging thickness :<:;101.60 mm (:<:;4.000 in.). Ramberg-Osgood parameter, n(longitudinaI, tension) = 54; n(short transverse, tension) = 29. UNS A97049, A97149
560 Lon~itudinal
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-295 .¡¡;
I.v-
60
-'"
rñ
~'"
en
40
20
100
V o
V
14
V
420
&.
::E
gf 280
~
140
4
2
Short transverse
6 8 Strain, 0.001 in.lin.
Compressive tangent modulus, GPa 28 42 56
10
WA.217 7049/7149-T73 aluminum alloy die forging, compressive stress-strain and compressive tangent modulus curves
70
80
Tested at room temperature. Typical for forging thickness :<:;101.60 mm (:5:4.000 in.). Ramberg-Osgood parameter, n(longitudinal, compression) =54; n(short transverse, compression) =29. UNS A97049, A97149
560 rf°ngitudinal
""""'-........; .¡¡;
60
-'"
rñ
~'"
en
40
20
V
/'
t---:::
V 2
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-295 L,.
/
"""
=
~- ¡-....,
~ Short transv':;; 1'\
420
gf ~
280 éií
140
4
6 8 10 Strain, 0.001 in.lin. 6 Compressive tangent modulus, 10 psi
ca
a.
::E
428/Wrought Aluminum (WA)
80
60
/
"'"
",-
'"~
é'ií
20
V V 2
14
~
rl Long transverse rl Short transverse
140
4
6 8 Strain, 0.001 in./in.
Compressive tangent modulus, GPa 28 42 56
o
12
10
WA.219 7049/7149-T73 aluminum alloy hand forging, compressive stress-strain and compressive tangent modulus curves
70
Tested at room temperature. Typical for forging thickness 50.08-127.0 mm (2.001-5.000 in.). Ramberg-Osgood parameter, n(longitudinal, compression) = 26; n(long transverse, compression) = 24; n(short transverse, compression) = 20. UNS A97049, A97149
560
1/
-
~
é'ií
40
v
Longitudinal and long transverse"" Shorttrans~
---.L.. -:::::z::
'00
"'vi" '"~
20
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-296
420
p
80
60
Tested at room temperature. Typical for forging thickness 50.083-127.0 mm (2.001-5.000 in.). Ramberg-Osgood parameter, n(longitudinal, tension) = 29; n(long transverse, tension) = 24; n(short transverse, tension) = 18. UNS A97049, A97149
560
11 Longitudinal
'00
40
WA.218 7049/7149-T73 aluminum alloy hand forging, tensile stress-strain curves
700
100
+;:::.-
::::::::~ V
v 2
420
vi
'"~
280
140
10 6 8 Strain, 0.001 in./in. 6 Compressive tangent modulus, 10 psi
4
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-296 en a.. :2:
o
12
é'ií
Wrought Aluminum (WA)/429
1ooo.------1,4-----.28------,42------5,6------7To------,8~00
WA.220 7049/7149-T73511 aluminum alloy extrusion, tensile and compressive stress-strain and compressive tangent modulus curves
Compression-+------+----Compressionlt--------1 560
Tested at room temperature. Test direction: longitudinal. Typical for extrusion thickness ::;127.0 mm (::;5.00 in.). Ramberg-Osgood parameter, n(longitudinal, tension) = 22; n(longitudinal, compression) = 20. UNS A97049, A97149
Compressive tangent modulus, GPa
80
420
.¡¡;
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-298 O)
a.
-'"
:2
ui m
ui m
~
~
ro
280
L------L----~------~--
4
2
6
__ ______ ~
8
ro
~~~~O
10
12
Strain, 0.001 in./in. Compressive tangent modulus, 106 psi
100
80
60
-'" mm ~
ro
y
40
20
Tested at room temperature. Typical for plate thickness 38.12-114.3 mm (1.501-4.500 in.). Ramberg-Osgood parameter, n(longitudinal, tension) = 13; n(long transverse, tension) = 12; n(short transverse, tension) = 10. UNSA97049
560 Longitudinal, Long transverse "-
.¡¡;
WA.221 7049-T7351 aluminum alloy plate, tensile stress-strain curves
700
y 2
y
-=:=:-
" ~-- ~ ~
420
"'" Short transverse
:2 ui
280
140
4
6 8 Strain, 0.001 in./in.
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-297 O)
a.
10
~
430/Wrought Aluminum (WA)
WA.222 7049-T7351 aluminum alloy plate, compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
1ooor-----~14------~28------4~2------5~6------7~0----~8~00
Tested at room temperature. Typical for plate thickness 38.125-114.30 mm (1.501-4.500 in.). Ramberg-Osgood parameter, n(longitudinal, compression) = 13; n(long transverse, compression) = 15; n(short transverse, compression) = 14. UNS A97049
80r-----~----~------+_----_+------r_----~560
420
.¡¡;
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-297 ro
a..
.><
:2
!Ji en
!Ji en
~
~
éií 280
éií
~----~----~------~----_+------+4----~140
~
____
~
_ _ _ __ L_ _ _ _
2
~
_ _ _ _ _ _L __ _ _ _
~L_
__
_JO 12
4 Strain, 0.001 in.lin. Compressive tangent modulus, 106 psi
80
r
70
~
60
50
RooJ temperature
35b °F (177 oC) 350 ro
a..
280 !Ji
~ 210
500°F (260 OC)
Ir
o
f
O
Tested at room and elevated temperatures. Test direction: longitudinal. Typical for forging thickness 127 mm (5 in.). Compositíon: AI-7.6Zn-2.5Mg-1.5Cu-0.15Cr. UNSA97049
:2
1/ //
10
490
420
I
20
WA.223 7049-T73 aluminum alloy forging, tensile stress-strain curves
250°F (121°C)
~
30
560
140
70
5
15 10 Strain, 0.001 in.lin.
20
Source: Private communication between O. Deel (Battelle Memorial Institute) and L.J. Barker (Kaiser Aluminum and Chemical Corp.), Dec 1969. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3217, CINDASlPurdue University, 1995, p 17
Wrought Aluminum (WA)/431
80
560
WA.224 7049-T73 aluminum alloy forging, tensile stress-strain curves
490
Tested at room and e1evated temperatures. Test direction: transverse. Typica1 for forging thickness 127 mm (5 in.). Composition: A1-7.6Zn-2.5Mg-1.5Cu-O.15Cr. UNSA97049
Room Itemperature
70
~r60
20
10
420
Ví
50
30
25d 'F (121 'C)
356 'F (177 'C) 350
IIr
as o.. :::E
280 gf
ti
I!!
1ñ 210
Ji
,
500 'F (260 'C)
Ir
140 70
5
10
15
Strain, 0.001 in.lin.
20
Source: O.L. Deel and H. Mindlin, "Engineering Data on New Aerospace Structural Materials," Technical Report AFML-TR-72-l96, Vol 11, Air Force Materials Laboratory, Wright-Patterson AFB, OH, Sept 1972. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3217, CINDAS/Purdue University, 1995, p 17
432/Wrought Aluminum (WA)
WA.225 7049-T73 aluminum alloy forging, effect of exposure and test temperature on tensile properties
Test temperature, oC 801r8~____-,38~____~9,3_______1,4_9_______2T04~_____2~6~60
Forging thickness: 127 mm (5 in.). Each point average of three tests. Composition: Al-7.6Zn-2.5Mg-1.5Cu-O.15Cr. UNSA97049
7or-------~~-----T------~--------+_------~490
Source: W.M. Pratt, "Material-Kaiser Aluminum Alloy X7049-T73, Effect of Elevated Temperature on Mechanical Properties," Report FGT5541, General Dynamics, Fort Worth Div., Dec 1969. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3217, CINDAS/ Purdue U niversity, 1995, P 18
40
Exposure time at test temperature --t--------+--\---~------__i
280
• 1/2 h ... 10 h • 100 h
30L-------~------~------~--------L-------~210
490
70
....... 60
'00
-'"
50
~
c, c: ~
¡¡; "C
a;
>= 40
30
~
420
l".\ I~ \•
ro
350 ~
210
140
20
~ 70r-------,--------r-------,--------~------,
:§:
E E
.S 60 f---------+-------f---------j--+----+--------j
'" .E c:
o
~
Cl
§
a;
50f---------+-------~--~~~~------t_------~
"C
c:
ro
~
~ 40f-------~~-------+------~~~¡---+--------j ro
c:
o ~
" 300L-------1~0~0------~20~0~----~3~O~O------~4~OO~-----5~OO ~ Test temperature, "F
Wrought Aluminum (WA)/433
80~----~------~----~-------.------.-------,560
WA.226 7049-T76 aluminum alloy extrusion, tensile stress-strain curves
70~-----~------+-----~~~--~------~------1490
Tested at room and elevated temperatures. Test direction: longitudinal. Composition: Al-7.6Zn-2.5Mg-1.5Cu-O.15Cr. UNSA97049
60~-----~-----+-----~--~~+---~~~~~
Source: O.L. Deel and H. Mindlin, "Engineering Data on New Aerospace Structural Materials," Technical Report AFML-TR-72-196, Vol JI, Air Force Materials Laboratory, Wright-Patterson AFB, OH, Sept 1972. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3217, CINDASlPurdue University, 1995, p 18
10~-h~~----~------4_----~------+-------1
8o.------,-----,------,------,------,------,56o
WA.227 7049-T76 aluminum alloy extrusion, tensile stress-strain curves
Room temperature
70~-----+-----~------4_----_4------+=~--~490
60~-----+------+-----~~----_+_
Tested at room and elevated temperatures. Test direction: transverse. Composition: Al-7.6Zn-2.5Mg-l.5Cu-O.15Cr. UNSA97049
420 350 ro
Il. ~ :2 gf 40~-----+------4ÑL-~~------~------~------1 280 gf ~ ~ U5 U5 30~----~--~~-------~----_4------+-----~ 210
20 ~---------MV---------j'--500 °F 260°C)--f-------+--------l 140 10~~~_+_----~'-------4-----~------+------1
°0~-----2L-----~4-------~6------~8------~----~
10
Strain, 0.001 in./in.
70
0 12
Source: O.L. Deel and H. Mindlin, "Engineering Data on New Aerospace Structural Materials," Technical Report AFML-TR-72-196, Vol JI, Air Force Materials Laboratory, Wright-Patterson AFB, OH, .Sept 1972. As published in Aerospace Structural M etals Handbook, Vol 3, Code 3217, CINDAS/Purdue University, 1995, p 18
434/Wrought Aluminum (WA)
Temperature,
oc
WA.228 7049-T73 aluminum alloy extrusion and bar, 7049-T76 bar, effect of temperature on tensile properties data
907r3------,18------3T8------9r3-----1,4-9-----2~04----__,26~30
80
\--=---,,~--~~--l---_+---+----l
560 ro
o.. :::e
~ ~
~
~
~70~~--~~~~-r-~~}-~~~----r--~490~
oe
~
e
~ ~
E:!
~
I~
~I
E ~ S
Test dírection: transverse. Compositíon: Al-7.6Znc2.5Mg1.5Cu-O.15Cr. UNS A97049 Source: R.E. Jones, "Mechanical Properties of7049-T73 and 7049-T76 Aluminum Alloy Extrusions at Severa! Temperatures;' AFML-TR-72-2, Air Force Materials Laboratory, Wright-Patterson AFB, OH, Feb 1972. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3217, CINDASlPurdue University, 1995, p 20
E
~
~
~
~
350~
\ii50 ~'"
~
~
~
~
~
~ 40\-----+---+---~---4---~~~--1280 ~
~
~
~
~
O. T73 3x11 Y4 in. (76.2x285.8 mm)
:;: 30
integrally stiffened extrusion
210 :;:
D. T73 3Y4x3% in. (82.6x88.9 mm) extruded bar
t:. Á T76 3Y4x3% in. (82.6x88.9 mm) extruded bar 20L-----~------~------~----~------~----~·140
-100
O
100
200 300 Temperature, °F
400
500
WA.229 7049-T73 aluminum alloy extrusion and bar, 7049-T76 bar, tensile property data
Temperature, oC
907r3~----,18------3~8------9r3----_,14r9-----2,0-4----_.26~30
80\--~~_+-----+------~----4-----_r------1560
--:;:¡
ro
o.. :::e -::::1
u..-
u..-
~ 70l----~~~~+~~~~---4------_r--~490 ~
rne
~
e
~
E:!
0 420 Sl
~
Sl 60 ro
ro
§
§
~
~
~
~
\ii~
~\ii
->.
->-r,
~ ~
~
E ~ 40l----+----+-----~---4-----~~-~280 ~
~
~
~
~
O. T73 3x11Y4 in. (76.2x285.8 mm)
:;: 30
integrally stiffened extrusion
210 :;:
D. T73 3Y4x3% in. (82.6x88.9 mm) extruded bar
t:. .... T76 3Y4x3% in. (82.6x88.9 mm) extruded bar 20L------L------~----~----~L-----~~--~140
-100
400
Temperature, °F
500
Test dírection: short transverse. Compositíon: Al-7.6Zn2.5Mg-1.5Cu-O.15Cr. UNS A97049 Source: R.E. Jones, "Mechanical Properties of 7049-T73 and 7049-T76 Aluminum Alloy Extrusions at Severa! Temperatures," AFML-TR-72-2, Air Force Materials Laboratory, Wright-Patterson AFB, OH, Feb 1972. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3217, CINDAS/Purdue University, 1995, p 20
Wrought Aluminum (WA)/435
80
70
;Y
60
V~
50
-
I 25, °F (121°C)
-'"
cñ 40
'"~
30
Source: Private cornmunication between O. Deel (Battelle Memorial Institute) and L.J. Barker (Kaiser Alurninum and Chernical Corp.), Dec 1969. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3217, CINDAS/Purdue University, 1995, p 20
210 500°F (260 OC)
h
l
Tested at room and elevated temperatures. Test direction: longitudinal. Typical for forging thickness 127 mm (5 in.). Composition: AI-7.6Zn-2.5Mg-1.5Cu-O.15Cr. UNSA97049
350
~
20
490 420
fI
ro
WA.230 7049-T73 aluminum alloy forging, compressive stress-strain curves
560
350°F (177 OC)
hV
·iñ
10
ROO~ temperature
140
I
70
15
5
20
Strain, 0.001 in.lin.
8o,-------,--------,.--------r-------,--------,56o
WA.231 7049-T73 aluminum alloy forging, compressive stress-strain curves
l
Room temperature
70 ~--+----J-~=i=:===:::j::==~490
?r--
Tested at room and elevated temperatures. Test direction: transverse. Typical for forging thickness 127 mm (5 in.). Composition: AI-7.6Zn-2.5Mg-l.5Cu-O.15Cr. UNSA97049
250 °F (121°C)
1 60r-------,.~~--_+·--------r_------~------_1420
~~~------+----~35~07¡oF~(~17~7~OC~)
50r-------~~~--_+--------r_------4_------_1350
h{'
~ 40r-----?/rR/¡--------+--------r-------4--------4280
~
~
30r---~f-~------_+--------r_------4--------i210
20
10
1/
500°F (260 OC) 140
L V
70
°0~------~5--------1~CI------~1~5-------2~0------~2;
Strain, 0.001 in.lin.
~ cñ
~
Source: Private cornmunication between O. Deel (Battelle Memorial Institute) and L.J. Barker (Kaiser Alurninum and Chemical Corp.), Dec 1969. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3217, CINDAS/Purdue University, 1995, p 20
436/Wrought Aluminum (WA)
WA.232 7049-T76 aluminum alloy extrusion, compressive stress-strain curves
8or-----,------,------,------,----~~----,560
60r_-----r------+---~~~----~----~------~
50r_-----r------+-~~-t~~--~----_4------~
Tested at room and elevated temperatures. Test direction: longitudinal. Composition: AI-7.6Zn-2.5Mg-l.5CuO.15Cr. UNS A97049
420
350 ro
o.. ~ ::¡; ~ 40~-----r---~17~-_+------4_----_4------~ 280 rñ
Source: O.L. Deel and H. Mindlin, "Engineering Data on New Aerospace Structural Materials," Technical ReportAFML-TR-72-196, Vol n, Air Force Materials Laboratory, Wright-Patterson AFB, OH, Sept 1972. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3217, CINDASlPurdue University, 1995, p 21
(f)
~
~ 30r-----+-.~~+_----4-----~------r_----~
210
500 'F (260 'C) 140 . .~~----_4------4_----_+------+_----~ 70
10~
2
4
6
8
10
0 12
Strain, 0.001 in.lin.
80 .------r------~----_,------,_------r_----~560
WA.233 7049-T76 aluminum alloy extrusion, compressive stress-strain curves
70 ~-----+------+_----_4--~~~------r_----~490
Tested at room and elevated temperatures. Test direction: transverse. Composition: AI-7.6Zn-2.5Mg-l.5Cu-O.15Cr. UNSA97049
60
~----~----_4-----f~~--_+------+_--~~420
50 1------+------+-~~_+----=..¡.......--==~----_l350 .¡¡;
""~
~
8: ::¡;
40
r_----r---~~~--_+------~----~------~280
30
~-----+--~~+_---_4------~------r_----~210
~
i 20 ¡----J~--~t=~~~~~t_----t_--__¡140 500 'F (260 'C) 10 ~~~4-----_4------+_-----+------r_----~70 O ~-----L------L4------~6------~8------~10------~1f 2 O Strain, 0.001 in.lin.
Source: O.L. Deel and H. Mindlin, "Engineering Data on New Aerospace Structural Materials," Technical Report AFML-TR-72-196, Vol n, Air Force Materials Laboratory, Wright-Patterson AFB, OH, Sept 1972. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3217, CINDAS/Purdue University, 1995, p 21
Wrought Aluminum (WA)/437
WA.234 7049-T73 aluminum alloy forging, effect of 10 h exposure and test temperature on compressive properties
Test temperature, oC
38
-18 70
93
--
... 60
204
149
1'--
420
"\
~
~
::¡;
T\
ui (J)
~ 50
ui
350 ~
\
"O
Qi ';;'
~
'00
~ 40
c.
E
Test direction: transverse, Forging thickness: 127 mm (5 in.). Each point average of three tests. Composition: Al-7.6Zn-2.5Mg-1.5Cu-O.15Cr. UNS A97049
1ií :g
Source: WM. Pratt, "Material-Kaiser Aluminum Alloy X7049-T73, Effect of Elevated Temperature on Mechanical Properties," Report FGT5541, General Dynamics, Fort Worth Div" Dec 1969, As published in Aerospace Structural Metals Handbook, Vol 3, Code 3217, CINDAS/ Purdue University, 1995, p 21
Q)
';;'
.~
280 :ll
~
~ o
8
210
30
100
200
300
140 500
400
Test temperature, °F
Test temperature, oC
38
-18 70
~
•
60
93
--
149
Forging thickness: 127 mm (5 in.). Composition: Al7.6Zn-2.5Mg-1.5Cu-0.15Cr. UNS A97049
'~ 420
1\\
~ ui (J)
~ 50 (J) :g Q)
';;'
.~
~ 40 c.
ca
a.
::¡;
ui
350 ~
1ií
:g .~
\
E o
• Longi\udinal
o
'" Transverse
30
100
WA.235 7049-T73 aluminum alloy forging, effect of temperature on compressive yield strength
204
200
300
Test temperature, 'F
400
\
,~ 280 :ll i!!
c.
E
o
o
\
210
140 500
Source: "Mechanical Property Data 7049 Aluminum-T73 Forgings," prepared by Batelle Memorial Institute, Columbus Laboratories, issued by Air Force Materials Laboratory, Wright-Patterson AFB, OH, Dec 1969, As published in Aerospace Structural Metals Handbook, Vol 3, Code 3217, CINDAS/Purdue University, 1995, p 21
438/Wrought Aluminum (WA)
WA.236 7050-T7451 aluminum alloy hand forging, tensile stress-strain curves
80r---~--'---,,---r---r--~---'---'r---,---,560
4% in. (114.3 mm)
Various thicknesses and test directions as indicated for 7050-T7451 (-T73651). Composition: Al-6.2Zn-2.25Mg2.3Cu-0.12Zr. UNS A97050
--......
Source: R.E. Davies, G.E. Nordmark, and J.D. Walsh, "Design Mechanical Properties, Fracture Toughness, Fatigue Properties, Exfoliation, and Stress-CoITosion Resistanee of 7050 Sheet, Plate, Hand Forgings, Die Forgings, and Extrusions," Report NOOOI9-72-C-0512 to Naval Air Systems Cornmand from Aleoa Laboratories, July 1975. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3222, CINDASlPurdue University, 1995, p 20
Strain, 0.001 in.lin.
WA.237 7050-174 aluminum alloy die forging, tensile stress-strain curves
80.---,----,----,----,----,----,----,----,---.560 4.25 in. (108 mm) diam
Various thicknesses and test directions for 7050-T74 (-T736). Composition: AI-6.2Zn-2.25Mg-2.3Cu-0.12Zr. UNSA97050
al
~
~
gf 40 I-----+---fj--.'---++-.'f----¡/.j-+---t----+----+-----I 280 gf
~
~
20~--~~--+-+~~--~~--+----~--~--_+--~140
- - - Longitudinal - . - . Short transverse
Strain, 0.001 in.lin.
Souree: R.E. Davies, G.E. Nordmark, and J.D. Walsh, "Design Mechanical Properties, Fracture Toughness, Fatigue Properties, Exfoliation, and Stress-CoITosion Resistance of 7050 Sheet, Plate, Hand Forgings, Die Forgings, and Extrusions," Report NOOOI9-72-C-0512 to Naval Air Systems Command from Aleoa Laboratories, July 1975. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3222, CINDASlPurdue University, 1995, p 20
Wrought Aluminum (WA)/439
WA.238 7050-T7451 aluminum alloy plate, tensile stress-strain curves
80~--~--~---r---r--~----r---~--,----.--~560
y"
in. (12.7 mm)
Various thicknesses and test directions for 7050-T7451 (-T73651). Composition: AI-6.2Zn-2.25Mg-2.3Cu0.12Zr. UNS A97050
4 in. (101.6 mm)
~
¡i 40 __-+_---I--.:--_t_-+---.~___t_+____rt__--+_--+_--_t_--_j 280 ~
é'i5
~ ui
~
é'i5
Source: R.E. Davies, G.E. Nordmark, and J.D. Walsh, "Design Mechanical Properties, Fracture Toughness, Fatigue Properties, Exfoliation, and Stress-Corrosion Resistance of 7050 Sheet, Plate, Hand Forgings, Die Forgings, and Extrusions," Report NOOO 19-72-C-0512 to Naval Air Systems Cornmand from Aleoa Laboratories, July 1975. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3222, CINDASlPurdue University, 1995, p 20
201---+-4-4-~-+-~---"-+~-T--I----+_-+_--_t_--_j140
- - Longitudinal - - - Long transverse - . - . Short transverse
Strain, 0.001 in./in.
WA.239 7050-T7351 aluminum alloy plate, tensile stress-strain curves
70r-------~-------~------_r------_r------_;490
PIate thickness: 50.8-152.4 mm (2-6 in.). Composition: AI-6.2Zn-2.25Mg-2.3Cu-0.12Zr. UNS A97050
601__-----4-------~-------~~~--+_-----_j420
50r-------+-------r__~~_P~~~-+------_1350
.¡¡; ~
-~
CJ)
40 1-------+--------:M---------f-------+---------I280
~
:2
~~
210 é'i5
30
201__-----.M--------~--------1__------+_-------j140
101-~~·--+_------t_-----+_-----~--------I70
°OL-------L--------L-------~------~------~O
2
-4 6 Strain, 0.001 in./in.
8
10
Source: D.J. Brownhill, R.E. Davies, G.E. Nordmark, and B.M. Ponchel, "Exploratory Development for Design Data on Structural Aluminum Alloys in Representative Aircraft Environments," AF contract 33615-74-C-5089, Aleoa Laboratories, AFML TR 77-102, July 1977. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3222, CINDASlPurdue University, 1995, p 21
440/Wrought Aluminum (WA)
80
560
WA.240 7050-T7651 aluminum alloy extrusion, tensile stress-strain curves
490
Various thicknesses. Test direction: L, longitudinal; LT, long transverse; ST, short transverse. Cross-sectional area: '5,277.4 cm2 ('5,43 in. 2). Composition: AI-6.2Zn2.25Mg-2.3Cu-O.12Zr. UNS A97050
~,L
.......: V- LT
70
60
I
50
30
20
10
/
1/
I 1/
:;; lE
--LT --ST
420
350
V
'"
a. :2 280 <ñ
'"~
Uí 210
140 - - ,;2.0 in. (';50.8 mm) ___ 2-5 in. (50.8-127 mm) 70
2
4
10
6 8 Strain, 0.001 in./in.
70
I
50
...
...
:i ~
Uí 30
/ 1/
350
280
/ V
&
:2
210
140 - - ,;2.0 in. (50.8 mm) ___ 2-5 in. (50.8-127 mm) 70
2
Various thicknesses. Test direction: L, longitudinal; LT, long transverse; ST, short transverse. Cross-sectional area: '5,277.4 cm2 ('5,43 in. 2). Composition: AI-6.2Zn2.25Mg-2.3Cu-0.12Zr. UNS A97050
420
ST
V/
40
10
/........... .... ....
f--L -LT _ LT
f/
-'"
20
WA.241 7050-T7351 aluminum alloy extrusion, tensile stress-strain curves
490
60
.¡¡;
Souree: J.T. Staley, J.E. Jaeoby, RE. Davies, G.E. Nordmark, J.D. Walsh, and F.R Rudolph, "Aluminum Alloy 7050 Extrusions," AF eontraet 33615-73-C-5015, Aleoa Laboratories, AFML-TR-76-129, Mareh 1977. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3222, CINDAS/Purdue University, 1995, p 21
4
6 8 Strain, 0.001 in./in.
10
o
12
X
Souree: J.T. Staley, J.E. Jaeoby, R.E. Davies, G.E. Nordmark, J.D. Walsh, and F.R Rudolph, "Aluminum Alloy 7050 Extrusions," AF eontraet 33615-73-C-5015, Aleoa Laboratories, AFML-TR-76-129, Mareh 1977. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3222, CINDAS/Purdue University, 1995, p 21
Wrought Aluminum (WA)/441
WA.242 7050-T76 aluminum alloy sheet, tensile stress-strain curves
700
100
Various thicknesses and test directions. Composition: Al6.2Zn-2.25Mg-2.3Cu-O.l2Zr. UNS A97050
0.090 in. (2.286 mm) 560
80
420
60 '00
ui
:2 ui 1/)
I
1/)
~
I
1ií
ro
a.
10.249 in. (6.325 mm)
-'"
I
280
40
Source: R.E. Davies, G.E. Nordmark, and J.D. Walsh, "Design Mechanical Properties, Fracture Toughness, Fatigue Properties, Exfoliation, and Stress-Corrosion Resistance df 7050 Sheet, Plate, Hand Forgings, Die Forgings, and Extrusions," Report NOOO 19-72-C-0512 to Naval Air Systems Command from Alcoa Laboratories, July 1975. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3222, CINDAS/Purdue University, 1995, p 21
~
20~--~-+--+-F--+------k-4--+----+----+----+---~140
- - Longitudinal - - - Long transverse
Strain, 0.001 in./in.
80 ,---,---,...---,----,---,----r---,-----,----,---- 560
WA.243 7050-T7452 aluminum alloy hand forgings, compressive stress-strain curves
Various thicknesses. Composition: Al-6.2Zn-2.25Mg2.3Cu-O.12Zr. UNS A97050
;7
60~--4----+--~~--+-~~~L+--~~/~/+---~----420
// / I
!
/!I
/
7% in. (190.5 mm)
~
:2
~ 40~--+---~,-~-+-.,~--4-~~--~----+---~---4280 ui
~
~
1ií
Strain, 0.001 in./in.
Source: R.E. Davies, G.E. Nordmark, and J.D. Walsh, "Design Mechanical Properties, Fracture Toughness, Fatigue Properties, Exfoliation, and Stress-Corrosion Resistance of 7050 Sheet, Plate, Hand Forgings, Die Forgings, and Extrusions," Report NOOOI9-72-C-0512 to Naval Air Systems Command from Alcoa Laboratories, July 1975. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3222, CINDAS/Purdue University, 1995, p 24
442/Wrought Aluminum (WA)
WA.244 7050-T74 aluminum alloy die forgings, compressive stress-strain curves
8or---.----,----~---r----~--~--~----~--~560
4.25 in. (108 mm) diam
Composition: Al-6.2Zn-2.25Mg-2.3Cu-0.12Zr. UNSA97050 Souree: R.E. Davies, G.E. Nordmark, and J.D. Walsh, "Design Meehanieal Properties, Fracture Toughness, Fatigue Properties, Exfoliation, and Stress-Corrosion Resistanee of 7050 Sheet, Plate, Hand Forgings, Die Forgings, and Extrusions," Report N00019-72-C-0512 to Naval Air Systems Command from Alcoa Laboratories, July 1975. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3222, CINDASlPurdue University, 1995, p 24
60~--_r--~--_r+_--_r~--~_.R_~~----+_--~420
.' 6.1 in. (155 mm) thick
Strain, 0.001 in./in.
70
I
WA.245 7050-T7351 aluminum alloy plate, compressive stress-strain curves
490
~transverse
~;;.
/
50
.¡¡;
350
280
/
""¡g ,g;
(/) 30
10
n S h q r t transverse Longitudinal
V
40
20
Plate thickness: 50.8-152.4 mm (2-6 in.). Composition: Al-6.2Zn-2.25Mg-2.3Cu-0.12Zr. UNS A97050
420
60
/ V
¡g 210
V
140
70
2
~
:;
6 4 Strain, 0.001 in./in.
8
o
10
~ i'ií
Souree: DJ. Brownhill, R.E. Davies, G.E. Nordmark, and B.M. Ponchel, "Exploratory Development for Design Data on Struetural Aluminum Alloys in Representative Aireraft Environments," AF eontraet 33615-74-C-5089, Alcoa Laboratories, AFML TR 77-102, July 1977. As published in Aerospace Structural Metals Handbook, Vo13, Code 3222, CINDASlPurdue University, 1995, p 24
Wrought Aluminum (WA)/443
WA.246 7050-T7451 aluminum alloy plate, compressive stress-strain curves
Various thicknesses. Composition: Al-6.2Zn-2.25Mg2.3Cu-0.12Zr. UNS A97050 60~--+---+---~~+-~~~~--~~~=--+---1420
~
~
~
~
gf 40 I----+_--/t-;,--~-I-__rl___:___t__l'__,¡_____.-+_-+_-__t_-_l 280 '"
Source: R.E. Davies, G.E. Nordmark, and J.D. Walsh, "Design Mechanical Properties, Fracture Toughness, Fatigue Properties, Exfoliation, and Stress-Corrosion Resistance of 7050 Sheet, Plate, Hand Forgings, Die Forgings, and Extrusions," Report NOOO 19-72-C0512 to Naval Air Systems Command from Alcoa Laboratories, July 1975. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3222, CINDAS/Purdue University, 1995, p 24
Strain, 0.001 in.lin.
o
WA.247 7050 aluminum alloy sheet, true stress as a function of strain rate
70
Tested at 482 oC (900°F). Grain size: 14!lm (0.55 mil). Total elongation shown in percent. Composition: Al6.2Zn-2.25Mg-2.3Cu-0.12Zr. UNS A97050
5.
Z
1. O
O. 1
0.0 5
!
I V
~ 120%
f..o-o 7.0
/-L
'"
o..
::¡;
'l!!" en
1ñ Q)
:::>
t= 0.7
0.0 1 10-6
0.07 10- 1 TrUl~
strain rate,
1 5-
Source: A.K. Ghosh and C.H. Hamilton, Deforrnation and Fracture in Al-Zn-Mg Alloys at Elevated Temperature, Strength of Metals and Alloys, Proc. Fifth Intemational Conference, Vol 2 (Aachen, Gerrnany), 27-31 Aug 1979. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3222, CINDASlPurdue University, 1995, p 32
444/Wrought Aluminum (WA)
90 r------r------r------r------,------,-----.630 80
WA.248 7050-T7451 aluminum alloy plate, compressive stress-strain curves at room and elevated temperatures
Room temperature
Tested at room and elevatedtemperatures. Test direction: (top) longitudinal; (bottom) long transverse. Plate thickness: 25.4 mm (1.0 in.). Composition: AI-6.2Zn-2.25Mg2.3Cu-0.12Zr. UNS A97050
70 60 .¡¡; -'"
50
ro
~-----r------~~~~~----~-----r----~350 ~
:i
'~"
~ 1i5 40 ~----~----~~~--~------~----~------1280 en 30 ~----~_7~L-~----~------~----~------1210 500 °F (260 oC) 20
O
O
____
~
L -_ _ _ _- L_ _ _ _ _ _L -_ _ _ _- L_ _ _ _ _ _L -_ _ _ _
~
10
90 ,------,------,------,------,------,-----.630 80
560
70
490
60
420 ro
~ 50 ~----_r------~~~~------~-----r------1350
~
.~
'"~
~ 1i5 40 ~----_r----~~-----r------~-----r------1280 en 30 ~----~~~--~----~------~----~------1210 500 °F (260 OC) 20
~~~~~i===i==+~~4_~~ 140
10
~-8~~------~----~------~----~------170
0 ~----~----~------L-----~----~----~O 0.8 1.0 1.2 0.4 0.6 0 0.2 Strain. %
Source: O.L. Deel, P.E. Ruff, and H. Mindlin, "Engineering Data on New Aerospace Structural Materials," AFML-TR-73-114, Battelle's Columbus Laboratories, June 1973. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3222, CINDAS/Purdue University, 1995, p 32
Wrought Aluminum (WA)/445
-18 80
38
93
Temperature, 149
oc 204
260
WA.249 7050-T7451 aluminum alloy plate, effect of temperature on compressive yield strength
316 560
Plate thickness: 25.4 mm (1.0 in.). Composition: Al6.2Zn-2.25Mg-2.3Cu-0.12Zr. UNS A97050 490
70
'"
.¡¡;
o..
420 :2
"".60
'"'"
''""
~
~
tí
:2 CIl 's;. 50
"C
350 ~
CIl
CIl
.2:
.2:
'"'"~ c.
§
Source: O.L. Deel, P.E. Ruff, and H. Mindlin, "Engineering Data on New Aerospace Structural Materials," AFML-TR-73-114, Battelle's Columbus Laboratories, June 1973. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3222, CINDASlPurdue University, 1995, p 32
'"~'c."
280 E
40
o
ü
Ü
• Longitudinal • Long transverse 30
20
210
0
100
200
300 400 Temperature, °F
80
~J~~
60
20
500
I V V 2
4
~ ~inal
606
40
WA.250 7050-T7351X aluminum alloy extrusion, tensile stress-strain curves
560
Tested at room temperature. Typical for extrusion thickness -::;'50.775 mm (-::;'1.999 in.). Cross-sectional area: -::;,206 cm2 (-::;'32 in. 2). Ramberg-Osgood parameter, n(longitudinal, tension) = 25; n(long transverse, tension) = 21. UNSA97050
420
Source: MIL·HDBK·5H, 1 Dec 1998, p 3-317
'"
o.. :2
280 '"
i
(f)
140
6
Strain, 0.001 in.lin.
8
10
446/Wrought Aluminum (WA)
WA.251 7050-T7351X aluminum alloy extrusion, tensile stress-strain curves
8or------r-----,------,------,------r-----~560
Tested at room temperature. Typical for extrusion thickness 50.80-127.0 mm (2.000-5.000 in.). Cross-sectional area: ~277 cm2 (~43 in. 2). Ramberg-Osgood parameter, n(longitudinal, tension) = 22; n(long transverse, tension) = 19, n(short transverse, tension) = 14. UNS A97050 Source: MIL-HDBK-5H, 1 Dec 1998, p 3-317
20~----~----~------4------+------+-----~140
4
2
10
8 6 Strain, 0.001 in./in.
WA.252 7050-T7351X aluminum alloy extrusion, compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
14
28
42
L/LO!' ,"""J, ~
Longitudinal ~
__ /
60
I
20
/
V 2
v
56
70
-.;;::
~
420
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-318
'"
CL
:2
280
~ 140
10 8 6 Strain, 0.001 in./in. 6 Compressive tangent modulus, 10 psi 4
Tested at room temperature. Typical for extrusion thickness ~50.775 mm (~1.999 in.). Cross-sectional area: ~206 cm2 (~32 in. 2). Ramberg-Osgood parameter, n(longitudinal, compression) = 39; n(long transverse, compression) = 38. UNS A97050
--
Wrought Aluminum (WA)/447
WA.253 7050-T7351X aluminum alIoy extrusion, compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
o
14
28
42
56
70
84
80~----~----~------~----~------.------,560
Tested at room temperature. Typical for extrusion thickness 50.80-127.0 mm (2.000-5.000 in.). Cross-sectional area: -:;,277 cm2 (-:;'43 in. 2). Ramberg-Osgood parameter, n(longitudinal, compression) = 29; n(long transverse, compression) = 33; n(short transverse, compression) = 23. UNS A97050 l1l
~
gf 40 1------1------+1------_+_----__+------+-__--_1 280 ~
~
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-318
~
en
201-----~----~1_----_+_----__+------+-_I_--_1140
2
4
6 8 10 Strain, 0.001 in./in. 6 Compressive tangent modulus, 10 psi
80
WA.254 7050-T74 aluminum alloy die forging, tensile stress-strain curves
560
Tested at room temperature. Typical for forging thickness -:;'76.20 mm (-:;'3.000 in.). Ramberg-Osgood parameter, n(longitudinal, tension) 27; n(short transverse, tension) = 24. UNS A97050
~ngitulina'
60
V
V V
-----
Short transverse
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-324 l1l
a..
::¡¡;
280
4
~
ro
20
2
=
420
140
6
Strain, 0.001 in./in.
8
10
448/Wrought Aluminum (WA)
WA.255 7050-T74 aluminum alloy die forging, compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
8oor-----~14------~28------4~2------5~6------7rO----~8\60
Tested at room temperature. Typical for forging thickness ::;76.20 mm (::;3.000 in.). Ramberg-Osgood parameter, n(longitudinal, compression) = 44; n(short transverse, compression) = 32. UNS A97050 Source: MIL-HDBK-5H, 1 Dec 1998, p 3-324
20~----~----~------4------+------+-1---~140
L-----~2~----~4------~6------~8------1~0~--~1~
Strain, 0.001 in./in. 6 Compressive tangent modulus, 10 psi
WA.256 7050-T7451 aluminum alloy stress-strain curves
80r-----~-----.------~-----,------r-----,560
pi ate, tensile
Tested at room temperature. Typical for plate thickness 12.70-101.60 mm (0.500-4.000 in.). Ramberg-Osgood parameter, n(longitudinal, tension) = 19; n(long transverse, tension) = 13; n(short transverse, tension) = 10. UNS A97050 ca
~ ~ ¡i 40 f--------j-------A------_I_----_+------t-----__j 280 rñ
.1:; ~ (/)
_ ~
iií
20f------~----_4------_I_----_+------t_----__j140
L-----~----~------~----~------1~0----~1~·
Strain, 0.001 in./in.
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-322
Wrought Aluminum (WA)/449
WA.257 7050-T7451 aluminum alloy plate, compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
o
14
28
42
56
70
84
8or-----~----_.------,_----_,------~----_,560
Tested at room temperature. Typical for plate thickness 12.70-101.60 mm (0.500-4.000 in.). Ramberg-Osgood parameter, n(longitudinal, compression) = 19; n(long transverse, compression) = 22; n(short transverse, compression) = 16. UNS A97050
60~----~~~~b---~~~~~~----+_----_1420
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-322
~'"
~
li
~
40 I--------+------/-!f--------j------t------+-+--------l 280
li
~
20~----~------f___----+----_t------+_1---_1140
2
6 8 10 Strain, 0.001 in.lin. Compressive tangent modulus, 106 psi
4
80
560
WA.258 7050-T74511 aluminum alloy extrusion, tensile stress-strain curves
Longitudinal
60
20
I :/ 2
I
V
420
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-325 ~ ::2
280 ui
j
140
4
Tested at room temperature. Typical for extrusion thickness ::;;44.450 mm (::;;1.750 in.). Ramberg-Osgood parameter, n(longitudinal, tension) = 19; n(long transverse, tension) = 26. UNS A97050
~I ~ transverse
6 Strain, 0.001 in.lin.
8
10
450/Wrought Aluminum (WA)
WA.259 7050-T74511 aluminum alloy extrusion, compressive and tangent modulus stress-strain curves
Compressive tangent modulus, GPa
8oor-----,1r4-----,28------4~2------5T6----~7TO----_.8\60
Tested at room temperature. Test direction: L, longitudinal; LT, long transverse. Typical for extrusion thickness ::;44.450 mm (::;1.750 in.). Ramberg-Osgood parameter, n(L, compression) = 19; n(LT, compression) = 23. UNS A97050 Source: MIL-HDBK-5H, 1 Dec 1998, p 3-325
~'"
~
gf 40 1-------+-----++------+------+------+--+-----1 280 gf
(/)~
~
ro 201------A------4------+------+------+--+-----1140
Strain, 0.001 in.lin. Compressive tangent modulus, 10 6 psi
WA.260 7050-T7452 aluminum alloy hand forging, tensile stress-strain curves
80.-----,,-----,------~-----,------,-----,560
Tested at room temperature. Typical for forging thickness ::;177.8 mm (::;7.000 in.). Ramberg-Osgood parameter, n(longitudinal, tension) = 14; n(long transverse, tension) = 14; n(short transverse, tension) = 9.3. UNS A97050
Longitudiqal Long transverse
Sh~rt transver~e 601-------+-----_4------+_~~~~----+-----~420
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-323
~'"
~
gf 40 I-------+-------A------+------+------t-------j 280 gf ~
~
ro
ro 201------~----_4------+_----_+------+_----~140
~-----2L-----~4,-----~6------~8------1~0----~1f· Strain, 0.001 in.lin.
Wrought Aluminum (WA)/451
WA.261 7050-T7452 aluminum alloy hand forging, compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
8oo.-----~14------,28------4~2------5~6------7TO----_.8\60
Tested at room temperature. Test direction: L, longitudinal; LT, long transverse; ST, short transverse. Typical for forging thickness ::;177.8 mm (::;7.000 in.). RambergOsgood parameter, n(L, compression) = 15; n(LT, compression) = 18; n(ST, compression) = 20. UNS A97050 Source: MIL-HDBK-5H, 1 Dec 1998, p 3-323
~
~
é'~i5
(J)
gf 40 1-------+------+t------+-------+------+-+-------1 280
-~
~----~----~------~----~------+_+---_1140
L------2L-----~4~----~6------~8------1~0~--~1;
Strain, 0.001 in.lin. Compressive tangent modulus, 106 psi
80
WA.262 7050-T7452 aluminum alloy die forging, tensile stress-strain curves
560
Tested at room temperature. Typical for forging thickness ::;152.4 mm (::;6.000 in.). Ramberg-Osgood parameter, n(longitudinal, tension) = 11; n(short transverse, tension) = 7.3. UNS A97050
~LOngituiina,
../'"
60
~
Short transverse
V
20
V V 2
4
420
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-326 ca
o..
::a;
280
~
é'i5
140
6
Strain, 0.001 in.lin.
8
10
452/Wrought Aluminum (WA)
WA.263 7050-T7452 aluminum alloy die forging, compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
14
28
42
56
70
84
.------r----~------._----_,------r_----~560
Tested at room temperature. Typical for forging thickness ::;152.4 mm (::;6.000 in.). Ramberg-Osgood parameter, n(longitudinal, compression) = 12; n(short transverse, compression) = 18. UNS A97050
60¡-----t------¡~~~~=_--r_----¡_----1420
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-326
~
&
:2
li
40 f-------f-------A------+_---_+------Hl---__j 280 ui ~ ~
w
w
20f------~----~------+_---_+------r1----__j140
L-----J-----~------~----~----~~----~1~
Strain, 0.001 in./in. Compressive tangent modulus, 106 psi
WA.264 7050-T7651 aluminum alloy pi ate, tensile stress-strain curves
80.-----,-----~------._----_r------r_----,560
Long transverse
Tested at room temperature. Typical for pI ate thickness ::;50.8 mm (::;2.000 in.). Ramberg-Osgood parameter, n(longitudinaI, tension) = 19; n(long transverse, tension) = 14. UNS A97050
60f-------f-----~----_,~---_+------r_----__j420
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-341 ro
~
li 40 f------f------If---+_--_+---r_--__j ~ W
~ 280
20f----~--~---+_--_+---r_--__j140
Strain, 0.001 in./in.
li
w ~
Wrought Aluminum (WA)/453
WA.265 7050-T7651 aluminum alloy plate, compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
o ~ G ~ ro M 80~----~-----;~----~----~~----T------1560
Tested at room temperature. Typical for plate thickness ~50.8 mm (~2.000 in.). Ramberg-Osgood parameter, n(longitudinal, compression) = 18; n(long transverse, compression) = 21. UNS A97050
60~-----~------~--~4---~~~--~~----~420
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-341
g¡
~
E
~ éií
gf 40 ~-----~------/-~---+------+----l--+------l 280
rn
rñ
20~--r~-----+-----l----+---~+--r--1140
ooL------2L_----~4------~6------~8------1~0--L-~lf
Strain, 0.001 in.lin. Compressive tangent modulus, 106 psi
80
VV
~
60
20
WA.266 7050-T7651X aluminum alloy extrusion, tensile stress-strain curves
560
v
Long transverse
4
420
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-339
&.
:2 280 rñ
V 2
Tested at room temperature. Typical for extrusion thickness ~50.775 mm (~1.999 in.). Cross-sectional area: ~206 cm2 (~32 in. 2). Ramberg-Osgood parameter, n(longitudinal, tension) = 25; n(long transverse, tension) = 20. UNSA97050
Longitudinal
----":: I
~
éií
140
6 8 Strain, 0.001 in.lin.
10
454/Wrought Aluminum (WA)
WA.267 7050-T7651X aluminum alloy extrusion, compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
14
28
42
56
70
84
r---,----,~--~---r----r---,560
Tested at room temperature. Typical for extrusion thickness 5,50.77 mm (5,1.999 in.). Cross-sectional area: 5,206 cm2 (:532 in. 2). Ramberg-Osgood parameter, n(longitudina!, compression) = 27; n(long transverse, compression) = 33. UNS A97050
1-----+----I---/-+----+---+-'~--1420
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-340
~
~'"
gf 401-----+----++---+----+---+--+---1 280
00
00
~
~
20~--~--_4---+_--_+---~1--~140
Strain, 0.001 in./in. 6 Compressive tangent modulus, 10 psi
WA.268 7050-T7651X aluminum alloy extrusion, tensile stress-strain curves
80~---r--_,---,_--_,---r_--,560
Tested at room temperature. Typical for extrusion thickness 50.80-127.0 mm (2.000-5.000 in.). Cross-sectional area: 5,277 cm2 (5,43 in. 2). Ramberg-Osgood parameter, n(longitudinal, tension) = 28; n(long transverse, tension) = 13; n(short transverse, tension) = 13. UNS A97050
60~---+---_4--_.~~~_+---~--~420
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-339
~'"
~
gf 4 0 1 - - - - - + - - - - F t - - - + - - - - + - - - + - - - - j 280 gf ~
~
00
00
20~--~--_4---+_--_+---r_--~140
Strain, 0,001 in./in,
Wrought Aluminum (WA)/455
WA.269 7050-T7651X aluminum alloy extrusion, compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa ~____~14~____~28~____4~2~____5T6______7TO____-.8\60
Tested at room temperature. Typical for extrusion thickness 50.80-127.0 mm (2.000-5.000 in.). Cross-sectional area: -:::;'277 cm2 (-:::;'43 in. 2). Ramberg-Osgood parameter, n(longitudinal, compression) = 22; n(long transverse, compression) = 27; n(short transverse, compression) = 22. UNS A97050
60~----~----~----~~----_+--~~~~---i420
"00
o..ro
"'"
:;¡;
~
j
gf 40 1-------f-----+1------+------+------+--I-----1 280
éñ
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-340
m
20~----~~----~------+_----_+------+_-r--~140
2
4
6 8 10 Strain, 0.001 in.lin. Compressive tangent modulus, 106 psi
100
~
90
~sverse
80 70
V
60
~
gf 50
V
~
m 40 30
V
20 10
/
/
630 560
Source: J. Gilbert Kaufman 420 ro
~/
a.
:;¡;
350
/
210 140 70
4
6 8 Strain, 0.001 in.lin.
Tested at room temperature. Typical for extrusion thickness 50.80-61.468 mm (0.500-2.420 in.). RambergOsgood parameter, n(longitudinal, tension) = 8.9; n(long transverse, tension) = 10. UNS A97055
490
/ 2
WA.270 7055~T77511 aluminum alloy extrusion, tensile stress-strain curves
700
10
~ éñ
456/Wrought Aluminum (WA)
560
WA.271 7075-T6 aluminum alloy, tensile stressstrain curves at room and elevated temperatures
70
490
Composition: Al-5.6Zn-2.5Mg-l.6Cu-0.3Cr. UNSA97075
60
420
50
350
Souree: "Typieal Tensile Stress Strain Curves for 7075 T6," Aleoa Researeh Laboratories, 20 Dec 1957, As published in Aerospace Structural Metals Handbook, Vol 3, Code 3207, CINDASlPurdue University, 1995, p 15
80 Room temperature
ro
a.
'¡¡j
"":i 40
::2:
280 U)
400°F (204 OC)
~
~
¡jj
(f)
210
30
20
140
500°F (260 OC)
70
10
O O
6 4 Strain, 0,001 inJin,
2
90
60 '¡¡j
""
50
U)
~
¡jj 40
30
20
í
V
300°F (149 OC) 350 °F (177 'C)
V
400°F (204 OC)
/'
r---~
1/ rr
450°F (232 OC)
Ir
500 °F
(2~0 OC)
560
WA.272 7075-T6 aluminum alloy sheet, complete stress-strain curves at room and elevated temperatures
490
Test direction: transverse. Composition: Al-5.6Zn2.5Mg-l.6Cu-0.3Cr. UNS A97075
630
R~om temper~ture
80
70
0 10
8
-t----
420 ro
350 ~
U)
280 ~ (f)
210
140
70
10
0,02
0,04
0,06 Strain, inJin,
0,08
0,10
o
0,12
G. Saehs, G. Espey, and G,B. Kasik, "Correlation of Information Available on the Fabrieation of Aluminum Alloys," See IV, Pt V, National Defense Researeh Cornmittee, 15 Sept 1944. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3207, CINDASI Purdue University, 1995, p 16
Wrought Aluminum (WA)/457
120
-----V~
100
80
--
V--
~
¡..--¡--
I
840
-423 °F (-253 OC)
I
-320°F (-196 OC)
06) :::-- I Room te~ture
700
-110 OF:9
560
40
280
20
140
0.04
0.08 Strain, in./in.
0.12
0.16
o
WA.273 7075-T6 aluminum alloy bar, complete stress-strain curves Tested at room and elevated temperatures. Bar diameter: 19 mm (0.75 in.). Composition: Al-5.6Zn-2.5Mg-1.6CuO.3Cr. UNS A97075 K.A. Warren and R.P. Reed, "Tensile and Impact Properties of Selected Materials from 20 to 300 K," Monograph 63, National Bureau of Standards, 1963. As published in Aerospace Structural M etals Handbook, Vol 3, Code 3207, CINDASlPurdue University, 1995, p 16
458/Wrought Aluminum (WA)
WA.274 7075-T6 aluminum alloy, isochronous stress-strain curves in tension
6or------r-----,------,------,------,-----~420
Short time __
---
Tested at: (top) 149 oC (300 °P); (bottom) 204 oC (400 °P). Composition: AI-5.6Zn-2.5Mg-l.6Cu-0.3Cr. UNSA97075
50~-----+------+------+------~~~~~----~350
280
40
ro
o.
~ cñ ti)
~
::a: 210 cñ ti)
30
~
en
iñ 20
140
10
70
O
O
280
40
30
... ... ,., ,.,
'00
-"
--210 ro
o.
::a:
1h
/
gf 20 ~
.- .-
-- --
Short time
140 cñ ti)
/
iñ
~
10 h
en
100 h
10
70
1000 h
00
2
4
6 8 Strain, 0.001 in./in.
10
O
12
Source: P.M. Howell and G.W. Stickley, "Isochronous Stress Strain Curves for Several Heat Treated Wrought Aluminum Alloys at 300 and 400F," Aleoa Research Laboratories, Mechanical Testing Div., 29 April 1958. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3207, CINDAS/Purdue University, 1995, p 20
Wrought Aluminum (WA)/459
WA.275 7075-T6 aluminum alloy ciad sheet, plate, effect of test direction on stress-strain curves
80~----~------,_------,_------_r------_,560
Test direction: L, longitudinal; T, transverse. Composition (7075): AI-5.5Zn-2.5Mg-I.6Cu-0.3Cr. CIad with low zinc, 7072, alloy. UNS A97075
60~----+_---+-----17~~-_+---_i420
Source: "Strength of Metal Aircraft Elements," ANC-5, Department of Defense, March 1955. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3208, CINDASlPurdue University, 1995, p 2
~
~
(/)~
ro
~ 40 f-------+----~'-----+---_+---___j 280 ~
~
140
20 .1 .1 .1
- - - Tension - - Compression
.1 .1 .1 .1
O O
4 6 Strain, 0.001 in.lin.
2
100
8
_ _1
T6, LOngitJdinal
r; --
- - - O, Transverse
80
100 'F(3JC) 200 'F (93 'C)
~
70 60
-.........
560
Sheet thickness: 1.626 mm (0.064 in.). Composition (7075): AI-5.5Zn-2.5Mg-1.6Cu-0.3Cr. CIad with low zinc, 7072, alloy. UNS A97075
490
420
350 ~
40 Room temperature
...
30 ",'"
.1
20
10
-
250 'F (12'1 'C)
~
~ 50 rñ
~
WA.276 7075-0 and 7075-T6 aluminum alloy ciad sheet, complete tensile stress-strain curves at room and elevated temperatures
630
90
i'
....
....
----
rñ en 280 (/) ~
-_.-- r---- ----~---210 300 'F (149 'C) -_.-- r---- ---- ---140
/
70
I I 0.02
0.04
0.06 Strain, in.lin.
0.08
0.10
O 0.12
Source: G. Sachs, G. Espey, and G.B. Kasik, "Corre1ation of Information Avai1ab1e on the Fabrication of A1uminum Alloys," Sec IV, Pt V, National Defense Research Committee, 15 Sept 1944. As pub1ished in Aerospace Structural Metals Handbook, Vol 3, Code 3208, CINDASlPurdue University, 1995. p 2
460/Wrought Aluminum (WA)
WA.277 7075-T6 aluminum alloy sheet, tensile stress-strain curves at room and elevated temperatures
7or------r-----,------,------,------.-----~490
Test direction: transverse. Sheet thickness: 1.626 mm (0.064 in.). Composition (7075): AI-5.5Zn-2.5Mg-1.6CuO.3Cr. CIad with Iow zinc, 7072, aIIoy. UNS A97075
.¡¡;
40 t------+--------1------+-+-----+------Ir-------j 280
~
~
~
~
00
E en 30
Source: D.D. Doerr, "Determination of Physical Properties of NonFerrous Structural Sheet Materials at Elevated Temperatures," AF TR 6517, Pt 1, Dec 1951. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3208, CINDASlPurdue University, 1995, p 3
~
210 ¡¡¡
20~~~_b~--_4--~~4_----_+--~~+_----~140
~----4_-----L-----J------L-----~----~0
Strain, 0.001 in.lin.
80.-----,------,------,------,------,-----~560
WA.278 7075-T6 aluminum alloy sheet, compressive stress-strain curves
70t-----~----~~----+------+------+-----4490
Tested at room and eIevated temperatures. Test direction: transverse. Sheet thickness: 1.626 mm (0.064 in.). Composition (7075): Al-5.5Zn-2.5Mg-1.6Cu-0.3Cr. CIad with low zinc, 7072, aIloy. UNS A97075
60t-----~~~~~~~+------+------+-----4420
50~----_rr.~~~----4_~L---+--~--+-----_1350
30t---~~-------1----~+-------+---
210
20~_+--~~-----1--~~+-------+--~L-+------
140
~----+_----~-----L-----L----~------O
Strain, 0.001 in.lin.
Source: D.D. Doerr, "Determination of Physical Properties of NonFerrous Structural Sheet Materials at Elevated Temperatures," AF TR 6517, Pt 1, Dec 1951. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3208, CINDASlPurdue University, 1995, p 3
Wrought Aluminum (WA)/461
Temperalure,
-18 80
.¡¡;
93
oc
204
316
60
WA.279 7075-T6 aluminum alloy ciad sheet, effect of exposure and test temperature on compressive yield strength
427 560
420
ro
o..
:;¡;
"'" ,s
,s
O>
e
O>
e
~
i
1ii ""C
""C
~ 40
280 :g¡ ;>,
.~In
(J)
> .¡¡;
In
In
~
~ c.
C.
E
E
O
O
ü
ü
20
140 .1/2 h 0100 h ... 1000 h V'3yralRT 1/2 h al ET
O O
200
400 Temperalure, °F
600
O
800
Sheet thickness: 1.626 mm (0.064 in.). RT, room temperature; ET, eIevated temperature. Composition (7075): AI5.5Zn-2.5Mg-1.6Cu-0.3Cr. CIad with Iow zinc, 7072, aHoyo UNS A97075 Source: D.D. Doerr, "Delermination of Physical Properties of NonFerrous Structural Sheet Materials at Elevated Temperatures," AF TR 6517, Pt 1, Dec 1951. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3208, CINDAS/Purdue University, 1995, p 3
462/Wrought Aluminum (WA)
WA.280 7075-T6 aluminum alloy ciad sheet, effect of exposure and test temperature on tensile properties
Temperature. oc 80r18________~93----------20,4---------3,1-6--------~42160
420
60
ro
o.. :2
"iñ
"'" :,
~::J
~
~
:5
~ c:
Cl
c:
~ 1ií 40
280
~
~
~
"iñ c:
"iñ c:
.$
.$
"*E :¡::¡ 140 :5
"*:¡::¡E :5 20
OL---------k---------k---------L-------~O
80.---------,----------,--------~--------__,560
20 .1/2 h O 100h ... 1000 h v3yratRT 1/2hatET
O O
200
400 Temperature. °F
600
808
Sheet thickness: 1.626 mm (0.064 in.). RT, room temperature; ET, elevated temperature. Note one sampIe was aged for 3 years. Composition (7075): AI-5.5Zn-2.5Mg1.6Cu-O.3Cr. CIad with Iow zinc, 7072, aHoyo UNS A97075 Source: D.D. Doerr, "Determination of Physical Properties of NonFerrous Structural Sheet Materials at Elevated Temperatures," AF TR 6517, Pt 1, Dec 1951. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3208, CINDASlPurdue University, 1995, p 3
Wrought Aluminum (WA)/463
40
35
---~--
~:
Nominal
"
>-
30
g¡
25
I
gf ~
tí 20 <:
¡ó':! 15
245
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essentially identical for both the true and nominal curves. YS, yield strength. Rod size: 19 mm (3/4 in.) diam. Test specimen diam, 12.7 mm (1/2 in.). Gage length: 203.2 mm (8 in.). Nominal tensile strength, 241 MPa (35.0 ksi). True tensile strength, 268 MPa (38.8 ksi). Nominal yield strength (0.2% offset), 108 MPa (15.7 ksi). Elongation (in 50.8 mm, or 2 in.), 11.9%. Reduction of area, 40%. True strain at maximum load, 10.4%. A loglog plot of the stress-strain curve would yield a slope of (n) of 0.09 in the area of uniform plastic deformation. UNSA97075
210
175
¡f
gf 140 ,¡g (J)
~
'00
..4- L,.-o
':fYJ"
10
WA.281 7075-0 aluminum alloy rolled and drawn rod, tensile stress-strain curves
::E
I r ¡
~
'00
5
V
~
280
<:
105 ¡ó':!
YS
I I I 70 I I I
t
35
Source: Aleoa, A1uminum Research Laboratory, New Kensington, PA, June 1953
I
:
o
0.02
0.04
0.06 Strain, in./in.
2
4
6
0.08
0.1~
0.10
Strain, 0.001 in./in.
90
r
80
70
_!,..----o-
I
/
60 '00
-'"
ui 50 (J)
j/
~
tí
~ 40 (J) <:
¡ó':! 30
20
10
V
O O
O
/
V
/'
Y'
/
/
I I I I I I I I I I I I I I I I I I I I I
I I 0.02 2
630
WA.282 7075-T6 aluminum alloy plate, tensile stress-strain curves
560
140
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essentially identical for both the true and nominal curves. YS, yield strength. Test direction: longitudinal. Nominal thickness: 15.9 mm (5/8 in.). Gage length: 203.2 mm (8 in.). Nominal tensile strength, 600 MPa (87.0 ksi). True tensile strength, 658 MPa (95.5 ksi). Nominal yield strength (0.2% offset), 531 MPa (77.0 ksi). Elongation (in 50.8 mm, or 2 in.), 10.0%. Reduction of area, 17%. True strain at maximum load, 9.5%. A log-log plot of the stress-strain curve would yield a slope of (n) of 0.10 in the area of uniform plastic deformation. UNS A97075
70
Source: Aleoa, A1uminum Research Laboratory, New Kensington, PA, April 1951
l'
0.04 0.06 Strain, in./in.
4
6
Strain, 0.001 in./in.
0.08
8
YS
490
420 al
o..
::E 350 ui (J)
~
tí 280 ~ <:
¡ó':! 210
o
0.10 10
464/Wrought Aluminum (WA)
100
90
r
80 70
--=::;;:::::::
gj 60 ui
~
ID 50 ~ .¡¡; c:
~
/
40
30
/
20 10
~
.....--
V
/
Nominal -
~
/
560
ro 420 ~ ui
en ~
ID ~
.¡¡;
280 ~
/
140
/
Y
WA.283 7075-T6 aluminum alloy plate, tensile stress-strain curves
700
-
True
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essentially identical for both the true and nominal curves. YS, yield strength. Test direction: transverse. Nominal thickness: 15.9 mm (5/8 in.). Gage length: 203.2 mm (8 in.). Nominal tensile strength, 600 MPa (87.0 ksi). True tensile strength, 658 MPa (95.5 ksi). Nominal yield strength (0.2% offset), 531 MPa (77.0 ksi). Elongation (in 50.8 mm, or 2 in.), 10.0%. Reduction of area, 17%. True strain at maximum load, 9.5%. A log-log pIot of the stress-strain curve would yield a slope of (n) of 0.10 in the area of uniform plastic deformation. UNS A97075 Source: Alcoa, Aluminum Research Laboratory, New Kensington, PA, April 1951
0.02
0.04
2
4
0.06
o
0.08
0.10
8
10
Strain, in.lin.
o
6
Strain. 0.001 in.lin.
WA.284 7075-T6 aluminum alloy ciad sheet, tensile and compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
1ooo,-----,14------,28------4T2------5T6------7,o-----,8~00
Tested at room temperature. Test direction: L, longitudinal; LT, long transverse. Typical for sheet thickness 4.775-6.325 mm (0.188-0.249 in.). Ramberg-Osgood parameter, n(L, tension) = 17; n(LT, tension) = 15 n(L, compression) = 13; n(LT, compression) = 12. UNSA97075 .¡¡;
420
60
-'" (/i
ro c.. :;;;
en
ui
iñ
~ en
en
~
280
40
20~----~-----4------+------+------~----~140
I I
I I
°0~----~2------J4------~6------~8------1~0----~1~ Strain, 0.001 in.lin. 6 Compressive tangent modulus, 10 psi
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-371
Wrought Aluminum (WA)/465
80 70
-
~
~ILOngitudinal
- --
-
560
WA.285 7075-T6 aluminum alloy ciad sheet, tensile stress-strain curves (full range)
490
Tested at room temperature. Typical. UNS A97075
- .....x
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-378
Long transverse
60
420
50
350
30
210
20
140
10
70
0.02
0.04
0.06
0.08
0.10
Strain, in./in.
WA.286 7075-T6 and 7075-T651 aluminum alloy rolled bar, rod, and shape, tensile and compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
1ooor------1r4------2,8--.---,42------,56------7,o------.8~00
Tested at room temperature. Test direction: longitudinal. Typical for specimen thickness ::::;76.20 mm (::::;3.000 in.). Ramberg-Osgood parameter, n(longitudinal, tension) = 50; n(longitudinal, compression) = 13. UNS A97075
80 f------f-------I------+-------+------+------ 560
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-376
420
.¡¡;
'"
Il.
-"
::¡¡
'"
'"
11)
~
11)
~
c;¡ 280
r-----~----~r-----~------+------+-;_--_1140
2
4
6 8 10 Strain, 0.001 in./in. Compressive tangent modulus, 106 psi
466/Wrought Aluminum (WA)
90 80
~
70
560
WA.287 7075-T6 and 7075-T651 aluminum alloy rolled or cold-finished bar, tensile stress-strain curve (full range)
490
Tested at room temperature. Test direction: longitudinal. Typical. UNS A97075
630
- --
- ......
~
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-379
420
60
ro
]l 50
350 ~
rñ
li
~
280 (fJ ~
é'i5 40
30
210
20
140
10
70
0.02
100
o
0.10
0.08 0.06 Strain, in./in.
0.04
0.12
70
14
o
0.14
WA.288 7075-T62 aluminum alloy plate, tensile and compressive stress-strain and compressive tangent modulus curves
84 700
Tested at room temperature. Test direction: L, longitudinal; LT, long transverse. Typical for plate thickness 6.350-50.80 mm (0.250-2.000 in.). Ramberg-Osgood parameter, n(L, tension) = 22; n(LT, tension) = 22 n(L, compression) = 25; n(LT, compression) = 22. UNSA97075
560
.¡¡;
420
60
ro o..
::a:
-'"
'"~
é'i5 280
40
~~~~~~~~~~+-~~-+~~~+-+-~~140
~
____
~
2
____
~
______
~
____
~
______L - L -__
8 6 Strain, 0.001 in./in. 6 Compressive tangent modulus, 10 psi
4
~O
12
'" ~
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-375
Wrought Aluminum (WA)/467
WA.289 7075-T62 aluminum alloy extrusion, tensile and compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
1ooor-----~1r4----_c28------,42------5,6------,_----_,8~00
Tested at room temperature. Test direction: L, longitudinal; LT, long transverse. Typical for extrusion thickness 6.350-38.075 mm (0.250-1.499 in.). Ramberg-Osgood parameter, n(L, tension) = 33; n(LT, tension) = 22 n(L, compression) = 27; n(LT, compression) = 23. UNSA97075 .¡¡;
420
60
(ti
a.
.><
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-377
::2:
uf
uf
Ul
Ul
~
~
Uí 280
40
Uí
20~----~----~------4_----_+------+_~--_4140
°0~----~2L-----~4------~6------~8------1~0~L-~1~
Strain, 0.001 in./in. Compressiv,e tangent modulus, 106 psi
100 90
80
WA.290 7075-T62 aluminum alloy extrusion, tensile stress-strain curves (full range)
700 LOngitu1dinal
r:. V
-
¡..---
.t"-
Long transverse
630
Tested at room temperature. Typical for extrusion thickness 6.35-38.07 mm (0.250-1.499 in.). UNS A97075
560
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-381
70
490
60
420
8!.
::2:
350 uf
~
40
280
30
210
20
140
10
70 0.02
0.04
0. 06
0.08
Strain, in./in.
0.10
0.12
o
0.14
ro
468/Wrought Aluminum (WA)
WA.291 7075-T651 aluminum alloy plate, tensile stress-strain curves
700
100
Longitudinal "-
80
LO~~Op
-:;:::::-¡::.---
Tested at room temperature. Typical for plate thickness 6.35-50.80 mm (0.250-2.000 in.). Ramberg-Osgood parameter, n(longitudinal, tension) = 32; n(long transverse, tension) = 17. UNS A97075
560
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-374 60 'iij
""!Ji en
~
(/)
40
20
V
/
420
/
!Ji en ~
ro 280
140
I 2
ro
a..
:2
4
6
8
10
o
12
Strain, 0.001 in./in.
WA.292 7075-T651 aluminum alloy plate, compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
1000~_ _,1~4___~28~____4,2______5T6______7,0____-.8~00
Tested at room temperature. Typical for plate thickness 6.35-50.80 mm (0.250-2.000 in.). Ramberg-Osgood parameter, n(longitudinal, compression) = 16; n(long transverse, compression) = 19. UNS A97075
1-----.o,.=-""=----;lL-----,,<----'f----~+-"<,.___::;;;o_"'F'-=...¡ 560
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-375 420
ro
a..
~
:2
!Ji en
!Ji en
~
~
ro
280
~----~----~------~-----+------+-+---~140
Strain, 0.001 in./in. 6 Compressive tangent modulus, 10 psi
ro
Wrought Aluminum (WA)/469
Jngitudinal , Long transverse,
80
·00
60
-'"
vi
'"~
Cií
40
20
WA.293 7075-T651X aluminum alloy extrusion, tensile stress-strain curves
700
100
v
v 2
v
v
-
~ ~
Tested at room temperature. Typical for extrusion thickness 12.7-19.0 mm (0.500-0.749 in.). Ramberg-Osgood parameter, n(longitudinal, tension) = 50; n(long transverse, tension) = 22. UNS A97075
560
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-376
420
!
280 m
140
4
6
8
10
Strain, 0.001 in./in.
WA.294 7075-T651X aluminum alloy extrusion, compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
100°r-----~1r4----~28~-----,42~----~56~----7To----~8~00
Tested at room temperature. Test direction: L, longitudinal; LT, long transverse. Typical for extrusion thickness 12.7-19.0 mm (0.500-0.749 in.). Ramberg-Osgood parameter, n(L, compression) = 26; n(LT, compression) = 27. UNSA97075
1-------1--="""-~~-d:,----.¿.~-__+_--_1 560
420
'00
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-377 al
vi
a. :2
Cií
'" ~
.>::
vi
'"~
280
r-----~----~----·--~----_+------+_~--_1140
~-----2~----~4~--·--~6------~8------1~0~~~1f
Strain, 0.001 in./in. Compressive tangent modulus, 106 psi
m
470/Wrought Aluminum (WA)
100 90 80
r-:-
V
---
700
WA.295 7075-T651X aluminum alloy extrusion, tensile stress-strain curves (full range)
630
Tested at room temperature. Typical for extrusion thickness 12.7-19.0 mm (0.500-0.749 in.). UNS A97075
LOngiTudinal
-+::~
Long transverse
560
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-380
70
490
60
420
'"
o...
::?: 350
'"~
40
280
30
210
20
140
10
70
0.02
0.04
0.06
0.08
0.10
0.12
éñ
o
0.14
Strain, in./in.
WA.296 7075-T73 aluminum alloy extrusion, tensile and compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
1ooor-----,14------,28------4,2------5T6----~7,0-----.8~00
Tested at room temperature. Test direction: L, longitudinal; LT, long transverse. Typical for extrusion thickness 6.35-38.07 mm (0.250-1.499 in.). Ramberg-Osgood parameter, n(L, tension) = 48; n(LT, tension) = 30 n(L, compression) = 27; n(LT, compression) = 26. UNSA97075
L, compression LT, compression
80~----~-----4------~~~~~~~~----~560
.¡¡; -'"
60
LT, compression
420
'"
o...
::?:
",-
'" ~
'"~
280
40
20~----~----~------+-----~------~4---~140
°0~----~2------~4------~6------L8------1LO~--~1~ Strain, 0.001 in./in. 6 Compressive tangent modulus, 10 psi
éñ
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-395
Wrought Aluminum (WA)/471
----V --
80
70
60
_ -+ --
560
WA.297 7075-T73 aluminum alloy extrusion, tensile stress-strain curves (fuI! range)
490
Tested at room temperature. Typical for extrusion thickness 6.35-38.07 mm (0.250-1.499 in.). UNS A97075
420
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-398
Longitudinal
-~:--""",
Long transverse
50
350
30
210
20
140
10
70
0.02
100
80
o
14
0.04
0.06 Strain, in./in.
0.08
0.10
Compressive tangent modulus, GPa 28 42 56
r-'00
:.!
ui Vl
~
ro
40
20
V
/ 2
~/
~-
WA.298 7075-T7351X aluminum alloy extrusion, tensile and compressive stress-strain and compressive tangent modulus curves
70
L and LT, compression " " LT, tension " " L t '. l'::,. L and LT, compres~¡ion ' enslon "-
60
0.1~
--
560
420
1'\
6 8 10 Strain, 0.001in./in. Compressive tangent modulus, 106 psi
~ ~
ui
280
140
4
Tested at room temperature. Test direction: L, longitudinal; LT, long transverse. Typical for extrusion thickness 12.7-19.0 mm (0.500-0.749 in.). Ramberg-Osgood parameter, n(L, tension) = 34; n(LT, tension) = 25 n(L, compression) = 28; n(LT, compression) = 28. UNSA97075
~
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-395
472/Wrought Aluminum (WA)
90
80
70
~
60
--::::: ~
,........
--=--
Long transverse
r-
WA.299 7075-T7351X aluminum alloy extrusion, tensile stress-strain curves (full range)
560
Tested at room temperature. Typical for extrusion thickness 12.7-19.02 mm (0.500-0.749 in.). UNS A97075
490
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-397
Longitudinal
-""""- .............. x
420
~ 50 ui
~
630
350
g¡'" ui
"'
40
280 (f) ~
30
210
20
140
10
70
o
O
0.02
0.04
0.06 0.08 Strain, in./in.
0.10
0.12
WA.300 7075-T7352 aluminum alloy hand forging, tensile stress-strain curves
700
100
Tested at room temperature. Typical for forging thickness 76.2-127.0 mm (3.001-5.000 in.). Ramberg-Osgood parameter, n(longitudinal, tension) = 15; n(long transverse, tension) = 17; n(short transverse, tension) = 12. UNSA97075
560
80
Longitudinal " ' " Long transverse" 60
-
~~~/
'00
"'ui" "'
~
40
20
o
0.14
/
cf.
:2
gf ~
280
/ 2
140
4
6 8 Strain, 0.001 in./in.
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-396
420
10
o
12
rn
Wrought Aluminum (WA)/473
100
o
Compressive tangent modulus, GPa 28 42 56
14
WA.301 7075-T7352 aluminum alloy hand forging, compressive stress-strain and compressive tangent modulus curves
70
560
80
"'-
60
ST
á
S:~
~~T
l~~ ~
-'"
~
ui m ~
~
-.::::::::
/"
éií
40
/
/ t
gj 60
280
~
>,,'"
-
True
¡..-Nominal ~
~ 40
30 20
!
I
ro-
O
560
I I
YS
I
490
I I I I
420 ~
I I
/
I I I
I I I I
r¡'
00
ca
gf 350 ~
m
..9l .¡¡; 280 ~ 210 140 70
I I
0.01 2
0.02
0.03
0.04 0.05 0.06 Strain, in.lin. 4 6 8 10 12 Strain, 0.001 in.lin.
WA.302 7079-T6 aluminum alloy extrusion, tensile stress-strain curves
630
V
t:
~
700
/
'00
10
..~
I V
~
..9l
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-396
6 8 10 Strain, 0.001 in.lin. Compressive tangent modulus, 106 psi
~
ui m ~ 1ií 50
ca
[L
:2 ui
4
2
90
70
~
420
140
100
80
-
l"
~ 'l!-L
'00
20
Tested at room temperature. Test direction: L, longitudinal; LT, long transverse; ST, short transverse. Typical for forging thickness 76.2-127.0 mm (3.001-5.000 in.). Ramberg-Osgood parameter, n(L, compression) = 15; n(LT, compression) = 13; n(ST, compression) = 15. UNSA97075
0.07
0.08
0.09
0.18
The upper row of strain values on the abscissa applies to both the complete true curve and the complete nominal curve. The lower row of strain values applies to the expanded portion of the curves; this expanded portion is essentially identical for both the true and nominal curves. YS, yield strength. Test direction: longitudinal (midway center to surface). Nominal size: 76 x 152 mm (3 x 6 in.) rectangle. Test specimen diam, 12.7 mm (0.5 in.). Gage length: 203.2 mm (8 in.). Nominal tensile strength, 594 MPa (86.2 ksi). True tensile strength, 636 MPa (92.2 ksi). Nominal yield strength (0.2% offset), 545 MPa (79.1 ksi). Elongation (in 50.8 mm, or 2 in.), 9.5%. Reduction of area, 18%. True strain at inaximum load, 6.8%. A log-log plot of the stress-strain curve would yield a slope of (n) of 0.09 in the area of uniform plastic deformation. This is no longer an active alloy but is inc1uded for reference purposes. UNS A97079 Source: Aleoa, AlulIÚnum Research Laboratory, New Kensington, PA
474/Wrought Aluminum (WA)
....-
Longitudinal
80
60 '00
"'rñ" '"~ U5
40
20
WA.303 7150-T6151 aluminum alloy plate, tensile stress-strain curves
700
100
V
V 2
V
/
.....
-
~g transverse
Tested at room temperature. Typical for plate thickness 19.050-25.40 mm (0.750-1.000 in.). Ramberg-Osgood parameter, n(longitudinal, tension) = 30; n(long transverse, tension) = 11. Composition: AI-6.4Zn-2.4Mg2.2Cu-0.12Zr. UNS A97150
560
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-408
420 (1. :2
g ~ 280
140
4
6 Strain,
10
8
o
12
0.001 in./in.
WA.304 7150-T6151 aluminum alloy plate, compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
1ooor------1~4-----,28------~42------576------7TO-----.8~00
Tested at room temperature. Typical for plate thickness 19.05-25.40 mm (0.750-1.000 in.). Ramberg-Osgood parameter, n(longitudinal, compression) = 15; n(long transverse, compression) =20. Composition: AI-6.4Zn2.4Mg-2.2Cu-0.12Zr. UNS A97150 420
60
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-408 ro
a. :2
'00
"'rñ" ,g;'"
rñ
'"~
rn
280
40
20~----A------4------+------+------~~--~140
2 Strain, 0.001 in./in. Compressive tangent modulus,
106 psi
U5
Wrought Aluminum (WA)/475
WA.305 7150-T61511 aluminum alloy extrusion, tensile stress-strain curves
1oor-----,------,------,-----~------,_----~700
Tested at room temperature. Typical for extrusion thick· ness 20.3-69.85 mm (0.800-2.750 in.). Ramberg-Osgood parameter, n(longitudinal, tension) = 9.5; n(long transverse, tension) = 9.5. Composition: AI-6.4Zn-2.4Mg2.2Cu-0.12Zr. UNS A97150
80~----4-----~------~----~~~~+_----_1560
420 ·00 -'" ui
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-409 ca
a. :2
ui
'" ~
'"~
en
280
~----~----~~----~----~------+_----_4
2
4
6 8 Strain, 0.001 in.lin.
ro
140
10
WA.306 7150-T61511 aluminum alloy extrusion, compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
100°r------1r4------2,8-----,42------~56------7~0-------8~00
Tested at room temperature. Typical for extrusion thickness 20.320-69.850 mm (0.800-2.750 in.). RambergOsgood parameter, n(longitudinal, compression) = 16; n(long transverse, compression) =27. Composition: AI6.4Zn-2.4Mg-2.2Cu-O.l2Zr. UNS A97150 ·00
60
420
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-409 ca
a. :2
-'"
ui
ui
'"
~
'"
280
40
20~--~~----~------~----~------+_~~-4140
2
4
6 8 10 Strain, 0.001 in.lin. Compressive tangent modulus, 106 psi
~
476/Wrought Aluminum (WA)
Longitudinal "-
80
60 '00
"'cñ" "' ~
1ií
40
20
WA.307 7150-T7751 aluminum alloy plate, tensile stress-strain curves
700
100
[7
/
2
/
/
><:
----
Tested at room temperature. Typical for plate thickness 8.636-47.625 mm (0.340-1.875 in.). Ramberg-Osgood parameter, n(longitudinal, tension) = 12; n(long transverse, tension) = 11. Composition: Al-6.4Zn-2.4Mg2.2Cu-0.12Zr. UNS A97150
560
Long transverse
Source: MIL-HDBK-5H. 1 Dec 1998, p 3-410
420 C1l
o-
:¡; cñ
"'~
280 1ií
140
4
6
8
10
o
12
Strain, 0.001 in./in.
WA.308 7150-T7751 aluminum alloy plate, compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
100°r-----,14------,28~----4,2~----5T6----~7TO-----,8~00
Tested at room temperature. Typical for plate thickness 8.636-47.625 mm (0.340-1.875 in.). Ramberg-Osgood parameter, n(longitudinal, compression) = 17; n(long transverse, compression) = 22. Composition: Al-6.4Zn2.4Mg-2.2Cu-0.12Zr. UNS A97150 420
60
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-410 C1l
o-
~
:¡; cñ <1)
cñ
"'~
~
1ií
280
40
20~----A_----~------+_-----+------~1_--~140
2
4
6
8
Strain, 0.001 in./in. 6 Compressive tangent modulus, 10 psi
10
1ií
Wrought Aluminum (WA)/477
WA.309 7150-T77511 aluminum alloy extrusion, tensile stress-strain curves
700
100
LOngitudin~ 80
60
~
'"
!!:!
éií
40
20
V
V 2
/
V
VCn
~
Tested at room temperature. Typical for extrusion thickness 17.78-29.108 mm (0.700-1.145 in.). RambergOsgood parameter, n(longitudinal, tension) = 8.8; n(long transverse, tension) = 8.2. UNS A97150
560
g transverse
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-411 420
al
o..
:2
gf !!:!
280
éií
140
4
6
8
10
Strain, 0.001 in./in.
WA.310 7175-T73511 aluminum alloy extrusion, tensile stress-strain curves
700
100
80
Tested at room temperature. Typical for extrusion thickness 25.40-50.80 mm (1.000-2.000 in.). Cross-sectional area: 206-419 cm2 (32-65 in. 2). Ramberg-Osgood parameter, n(longitudinal, tension) = 41; n(long transverse, tension) = 58. Composition: Al-5.6Zn-2.5Mg-1.6Cu-0.23Cr. UNSA97175
560 Lon! itudinal
,...-::::
¿;-
60 '0;
-'"
~'"
C/l
40
20
V
V 2
Long transverse- 420
V
'" !!:!
280
140
4
~
:2
6 Strain, 0.001 in./in.
8
10
éií
Source: MIL-HDBK-5H, 1 Dec 1998, p 3--420
478/Wrought Aluminum (WA)
o
100
14
Compressive tangent modulus, GPa 28 42 56
'-- t--60 'iii
'"uf 00
~
20
ca
Tested at room temperature. Test direction: longitudinal and long transverse. Typical for extrusion thickness 25.40-50.80 mm (1.000-2.000 in.). Cross-sectional area: 206-419 cm2 (32-65 in. 2). Ramberg-Osgood parameter, n(longitudinal and long transverse, compression) = 13. Composition: AI-5.6Zn-2.5Mg-l.6Cu-0.23Cr. UNSA97175
::¡;
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-420
560
80
40
WA.311 7175-T73511 aluminum alloy extrusion, compressive stress-strain and compressive tangent modulus curves
70
V V 2
v
~
¡..-
_....
--.......1\
420
a.
00-
280
~
140
8 10 6 Strain, 0.001 in.lin. Compressive tangent modulus, 106 psi
4
o
12
WA.312 7175-T74 aluminum alloy die forging, tensile stress-strain curves
700
100
Tested at room temperature. Typical for forging thickness -::;'76.20 mm (-::;'3.000 in.). Ramberg-Osgood parameter, n(longitudinal, tension) = 50; n(transverse, tension) = 25. Composition: AI-5.6Zn-2.5Mg-l.6Cu-0.23Cr. UNSA97175
560
80 Longitudinal
60 'iii
'"uf 00
~
40
20
V
V 2
V
~
fo--Transverse ca
a.
::¡;
gf ~
280 (¡)
140
4
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-425
420
6 Strain, 0.001 in.lin.
8
10
o
12
Wrought Aluminum (WA)/479
100
80
.¡¡;
o
14
Compressive tangent modulus, GPa 28 42 56
~Lo",;LMI~ / Transverse "-
-~ ~ t---L-
I,,¿
1----
-"
'"
~
40
vi
V
2
- --
>
r--
I
60
20
V
V
WA.313 7175-T74 aluminum alloy die forging, compressive stress-strain and compressive tangent modulus curves
70
Tested at room temperature. Typical for forging thickness :5:76.20 mm (:5:3.000 in.). Ramberg-Osgood parameter, n(longitudinal, compression) = 50; n(transverse, compression) = 25. Composition: Al-5.6Zn-2.5Mg-1.6Cu-0.23Cr. UNSA97175
560
i"'I
1\
420
Source: MIL-HDBK-5H, 1 Dec 1998, p 3--425
&.
::!;
280
~
140
6
4
8
10
Strain, 0.001 in.lin. 6 Compressive tangent modulus, 10 psi
WA.314 7175-T74 aluminum alloy hand forging, tensile stress-strain curves
700
100
Tested at room temperature. Typical for forging thickness :5:101.60 mm (:5:4.000 in.). Ramberg-Osgood parameter, n(longitudinal, tension) = 34; n(long transverse, tension) = 26; n(short transverse, tension) = 13. Composition: Al5.6Zn-2.5Mg-1.6Cu-0.23Cr. UNS A97175
560
80 Lopgitudinal " Long tfansverse " Short transverse "-
80
.¡¡;
60
-"
'"~
ro
40
20
V
V 2
V
~
280
140
4
6 8 Slrain, 0.001 in.lin.
Source: MIL-HDBK-5H, 1 Dec 1998, p 3--426
420
/"
10
~
480/Wrought Aluminum (WA)
WA.315 7175-T74 aluminum alloy hand forging, compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus. GPa
100
o
14
28
42
56
80
·00
60
~
./LT
L
/
(J)
~
1ií 40
20
L~
V
-
-
)L
~
420
ro
o..
~
/
2
Tested at room temperature. Test direction: L, longitudinal; LT, long transverse, ST, short transverse. Typical for forging thickness :::::101.60 mm (:::::4.000 in.). RambergOsgood parameter, n(L, compression) = 27; n(LT, compression) = 17; n(ST, compression) = 19. Composition: AI-5.6Zn-2.5Mg-1.6Cu-0.23Cr. UNS A97175
560
LT~
:::--
"'!Ji"
70
Source: MIL-HDBK-5H, 1 Dec 1998. p 3-426
:2 !Ji (J) ~
280
1ií
140
6 8 10 Strain. 0.001 inJin. 6 Compressive tangent modulus. 10 psi
4
WA.316 7175-T7452 aluminum alloy hand forging, tensile stress-strain curves
8o.------r----~------,_----_,------r_----,560
Tested at room temperature. Typical for forging thickness 101.625-127.0 mm (4.001-5.000 in.). Ramberg-Osgood parameter, n(longitudinal, tension) = 12; n(long transverse, tension) = 13; n(short transverse, tension) = 10. Composition: AI-5.6Zn-2.5Mg-l.6Cu-0.23Cr. UNS A97175 ro
~
~
gf 40 l------+-------A------+------+------i---------1 280 !Ji ~ ~ 1ií 1ií
20~----~----~------+_----_+------T_----~140
~-----L----~------~----~------1~0----~1l
Strain. 0.001 inJin.
Source: MIL-HDBK-5H. 1 Dec 1998, p 3-427
Wrought Aluminum (WA)/481
WA.317 7175-T7452 aluminum alloy hand forging, compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
8oor------1r4-----,2~8--.--_,42------,56------7,0----__,M560
Tested at room temperature. Typical for forging thickness 101.625-127.0 mm (4.001-5.000 in.). Ramberg-Osgood parameter, n(longitudinal, compression) = 13; n(long transverse, compression) = 15; n(short transverse, compression) = 17. Composition: Al-5.6Zn-2.5Mg1.6Cu-0.23Cr. UNS A97175
60r-----~~~~------~~~~------+_----~420
~
8:.
gf 40 r------+-------A------~---__+------~r_--~ 280
~
:2 uj
~
Ci5
20r----7r---~------~---__+-----+_r_--~140
L-----~2------~4-------~6------~8------1~0-L--~1~
Strain, 0.001 inJin. Compressive tangent modulus, 106 psi
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-427
482/Wrought Aluminum (WA)
WA.318 7175-T74 aluminum alloy die (top) and hand forging (bottom), tensile and compressive stress-strain curves
8or-------,--------,-------,----~--,_------,560
70~------4--------+------~--~~~~~~--~490
60~------~------_+------~~----~~------~420
50~------~------_+--~--~--------+_------~350
ro
~
li
40 I-------+-------&------~--------+--------~ 280
~
w
~
li ~
w 30~------~--DL--_+------~--------+_------~210
20~------~------~--------~------~------~140
L-------J-------~--------~------~------~O 80~------~------~--------r_------,_------~560
~
li
ro
40 ~------4-------_H_--------I_------+_------~ 280
~ w
30~------~--~--_+--------~------~------~210
20~----~~------_+------~--------+_------~140
101_-.~--~------+__------+-------_r------~70
2
4 Strain. 0.001 in.lin.
~
li
~ w
Tested at room temperature. Test direction: L, longitudinal; T, transverse; ST, short transverse. Typical for die forging thickness :::::76.20 mm (:::::3.000 in.) top, and hand forging thickness :::::101.60 mm (4.000 in.) bottom. Composition: AI-5.6Zn-2.5Mg-l.6Cu-0.23Cr-low Ti,Mn,Si. UNS A97175 Source: C.E Babilon, R.H. Wygonik, G.E. Nordmark, and B.W. Lifka, "Mechanical Properties, Fracture Toughness, Fatigue, Environmental Fatigue Crack Growth Rates, and Corrosion Characteristics of High Toughness Aluminurn AlIoy Forgings, Sheet and Plate," AFML-TR-7383, Air Force Materials Laboratory, Apri11973. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3219, CINDAS/ Purdue University, 1995, p !O
Wrought Aluminum (WA)/483
80
-
/ ' 75°F (24°C)
70
60
/;
50
~~ ~V'
30
20
10
o
/
J
W ~
/~
250°F (121°C)
~
350°F (177 OC)
560
WA.319 7175-T74 aluminum alloy forging, tensile stress-strain curves
490
Tested at various temperatures, Test direction: longitudinal (top) and transverse (bottom). Composition: Al5.6Zn-2.5Mg- L6Cu-O,23Cr-low Ti,Mn,Si. UNSA97175
420
/
-
350 al
[L
::¡; 280
'" ~
210
500°F (260 OC)
140
70
o
8o,-----,------,------,------,------,------,56o
70r------r----~------~--~~~
60r------r----~------~
__~~
490
420
50~-----r----~---~~i------±~~--+-----~350
~
:i
8:. ::¡;
40 1---------t--------jH'-,~--+_----_+------+_----_I 280
'"
~ w
ro~ 30r------r--~bY------~-----+------+------1210
500°F (260 OC)
101-----T.~-r----~------+-----_+------+_----_I70
°0L-----~0,-2-----0~A------0~.6------0~.8------1~.0----~1.J Slrain, %
Source: AMS 4038A, 1966. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3219, CINDASlPurdue University, 1995, p 12
484/Wrought Aluminum (WA)
WA.320 7175-T74 aluminum alloy forging, effect of temperature on tensile properties
Temperature. 'C
-18 90
80
93
38
...... ~ A...
~ 'J F - ....
ty
149
204
260
560
:;
'""",.,
490 !:S"'
~
'§,
"[!!
420 Oí
'~
"tJ
ID .;;'
350
~,\
-k- -
Transverse
20
280
210 140
/
- ~ . --r-
~,;
",
"'RA
~
r ---100
200
--_..J....
.¿.- -
e
300 Temperature. 'F
400
500
"*E
§
100
L
'§,
" ~
70
10
ff
¡¡¡
~
'\ '\
_ _ _ Longitudinal
"tJ
~"
,
-
&.
600
Composition: Al-5.6Zn-2.5Mg-l.6Cu-O.23Cr-low Ti,Mn,Si. UNS A97175 Source: AMS 4038A, 1966. As published in Aerospace Structural Metals Handbook, Vo13, Code 3219, CINDASlPurdue University, 1995, p 14
Wrought Aluminum (WA)/485
8or------r-----,------,-----~----~~----,560
WA.321 7175-T74 aluminum alloy forging, compressive stress strain curves
70~-----~----_4------~~--_+--~~+_----_1490
Tested at various temperatures. Test direction: longitudinal (top) and transverse (bottom). Composition: AI5.6Zn-2.5Mg-1.6Cu-O.23Cr-Iow Ti,Mn,Si. UNS A97175
60~-----~----_4----E-~----_+------~._--_1420
Source: AMS 4038A. 1966. As published in Aerospace Structural Metals Handbook, Vo13, Code 3219, CINDAS/Purdue University, 1995, p 14
50~-----~------~~~~~~--_1------~----~350
~
~ ::¡; ~ 40 ~-----l_----_/__J'-/-----~----__+------+_----___i 280 .;
~
~
30~-----l-~~~------4-------+------+_----___i210
500°F (260 OC)
20~--_A~_=_4~:~~====:¡----~----~140 10~,M~~----_1------4-----__+------+_----___i70
OL------~------~----~----~------~----~O
80r------r------r------r-----,------,------,560 70~-----~------~----~~~~------,-~~~490
60~-----~------r_--_,~----_1------4_----~420
50~----~------r_~~--~~~_1----~4_~--~350
~
~ ::¡; ~ 40 ~-----~----__+f_____7<----_I_----_1------4_----~ 280 .; ~
ti)
~
ro 30~----_r-.~L-r_----~----_4------+_----~210
500°F (260 OC)
10~_h~~----_4-------+_----_+------+_----_170
°0~-----L----~-------~----~------L------10
0.2
0.4
0.6
Strain. %
0.8
1.0
1.2
486/Wrought Aluminum (WA)
110
-
100 90
l
80
P-""'"
~
~ f-"'
700
Nominal .r..
y
630
"""
f
YS
I
\
f f
V
~
gf 60 ~
f
/
tí
~ 50 40
~
30
J
I
20
I
f f I
V
e
10
-
True
I
._ 70
~
WA.322 7178-T6 aluminum alloy extruded bar, tensile stress-strain curves
770
f
/ V
f f I
490 ro a.
:2;
420 gf ~
tí
350 ...!!1 ¡¡; e
280 ~
Source: Alcoa, Aluminum Research Laboratory, New Kensington, PA
210
f f f f f
~
0.01
560
YS, yield strength. Nominal size: 15.9 x 76.2 mm (5/8 x 3 in.). Test specimen diam, 12.7 mm (0.5 in.). Gage length: 203.2 mm (8 in.). Nominal tensile strength, 655 MPa (95.0 ksi). True tensile strength, 703 MPa (102 ksi). Nominal yield strength (0.2% offset), 600 MPa (87.0 ksi). Elongation (in 50.8 mm, or 2 in.), 7.6%. Reduction of area, 14%. True strain at maximum load, 7.0%. A log-log plot of the stress-strain curve would yield a slope of (n) of 0.08 in the area of uniform plastic deformation. Composition: AI-6.8Zn-2.7Mg-2.0Cu-0.3Cr. UNSA97178
0.02
0.04
0.03
0.05
0.06
10
12
0.07
140 70
o.oH
Strain, in./in.
o
6
4
2
8
Strain, 0.001 in./in.
80 LongLdinal
70
A k-----
560
WA.323 7249-T7452 aluminum alloy hand forging, tensile stress-strain curves
490
Tested at room temperature. Ramberg-Osgood parameter, n(longitudinal, tension) = 26.0; n(long transverse, tension) = 24.0; n(short transverse, tension) = 14.0. Tensile yield strength: longitudinal = 461.6 MPa (67.0 ksi); long transverse = 454.7 MPa (66.0 ksi); short transverse = 420.3 MPa (61.0 ksi). Composition: AI-4.7Zn-2.2Mg1.6Cu-0.15Cr. UNS A97249
P"
60
/
50 ~
gf
~
40
/
iií
30
20
10
/ V
~
Long tran¡verse
420
Short transverse
350
V
ro
a.
:2;
280 ui U)
~
iií 210
1/
140
70
2
4
6 Strain, 0.001 in./in.
8
10
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-432
Wrought Aluminum (WA)/487
WA.324 7249-17452 aluminum alloy hand forging, compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
o 80
14
28
42
56
70
84 560
70
490
60
420
50
350
.¡¡;
"'gf" ~
ro
Tested at room temperature. Ramberg-Osgood parameter, n(longitudinal, compression) = 20.0; n(long transverse, compression) = 20.0; n(short transverse, compression) = 23.0. Tensile yield strength: longitudinal = 420.3 MPa (61.0 ksi); long transverse = 475.4 MPa (69.0 ksi); short transverse = 496.1 MPa (72.0 ksi). Composition: AI4.7Zn-2.2Mg-1.6Cu-0.15Cr. UNS A97249
:2
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-432
Il.
40
280 ui 1/) ~
Ci5
Ci5
30
210
20
140
10
70
0 12
2 Strain, 0.001 in.lin. Compressive tangent modulus, 106 psi
80
60
WA.325 7249-17452 aluminum alloy hand forging, tensile stress-strain curves (full range)
560
f
--
-- r=--:::::.... t:::~ Short tr~nsverse ~
LOng1transverL
~""P.,
Longitudinal'
t'x
Tested at room temperature. Typical for forging thickness: in longitudinal and long transverse directions, 38.10-152.40 mm (1.500-6.000 in.); in short transverse direction, 76.20-152.40 mm (3.000-6.000 in.). Composition: AI-4.7Zn-2.2Mg-l.6Cu-0.15Cr. UNSA97249
420
tE.
:2
280 ui 1/) ~
Ci5
20
140
0.02
0.04
0.06
0.08 Strain, in.lin.
0.10
0.12
0.14
o
0.16
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-433
488/Wrought Aluminum (WA)
80
60
V
u.
20
WA.326 7475-T7351 aluminum alloy plate, tensile stress-strain curves
560
'7 v
r-
".---
420
lJ~,
V / V /
Plate thickness: 38.1 mm (1.5 in.). Composition: AI5 .6Zn-2.2Mg-1.5Cu-O.21 Cr-Iow Si,Fe,Mn, Ti. UNS A97475
o..'"
:2
Source: R.R. Cervay, "Static & Dynamic Fracture Properties for AluminumAlloy 7475-T651 and T7351," AFML-TR-75-20, Air Force Materials Laboratory, April 1975. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3220, CINDASlPurdue University, 1995, p 12
280 I/l ui ~
ro
140
o
Strain, 0.001 in./in.
WA.327 7475-T651 aluminum alloy plate, tensile stress-strain curves
8o,-----r-----,-----~----,_----,_----_r----,560
P1ate thickness: 38.1 mm (1.5 in.). Composition: AI5.6Zn-2.2Mg-1.5Cu-O.21Cr-Iow Si,Fe,Mn,Ti. UNSA97475
60~----~----+---~~----1_----~----_r----~420
~
gf 40
f-------~------,I_----+_----+_----+----_+----_i
~'"
280 gf
~
~
ro
ro
20~--~~--_4----~L---_+----_+----_+----~140
~----~--~L---~----~----~-----L----~O
Strain, 0.001 in./in.
Source: R.R. Cervay, "Static & Dynamic Fracture Properties for Aluminum Alloy 7475-T651 and T735 1," AFML-TR-75-20, Air Force Materials Laboratory, April 1975. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3220, CINDASlPurdue University, 1995, p 12
Wrought Aluminum (WA)/489
-- /
70
1/
60
/
Longitudina!
50
~ 40
li ~
Cií 30
20
10
~ong
V /
/
/
/ V 1/
WA.328 7475-T61 aluminum alloy ciad sheet, tensile stress-strain curves
490
..... 420
Composition: Al-5.6Zn-2.2Mg-l.5Cu-O.21Cr-low Si,Fe,Mn,Ti. UNS A97475
350
Source: J.A. Dickson, "Aleoa 467 Process X7475 Alloy," Aleoa Green Letter G.L. 216 5-70, Aluminum Co. of America, May 1970. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3220, CINDAS/Purdue University, 1995, p 12
transverse
280
/ V
& :2 rii
~
210 Cií
140
70
o
Strain, 0.001 in./in.
70
60
V Longitudina¡l'
50
.¡¡; -"
j
30
20
10
--
1/
40
rii
UJ
WA.329 7475-T761 aluminum alloy ciad sheet, tensile stress-strain curves
490
j
/
/
1--
/ I~ong
/ ij l'
V 1/
¡..--
V
420
Composition: Al-5.6Zn-2.2Mg-l.5Cu-O.21 Cr-low Si,Fe,Mn,Ti. UNS A97475
350
Source: J.A. Dickson, "Aleoa 467 Process X7475 Alloy," Aleoa Green Letter G.L. 216 5-70, Aluminum Co. of America, May 1970. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3220, CINDAS/Purdue University, 1995, p 12
transverse
280
2101 140
70
o Str.ain, 0.001 in./in.
&
:2
490/Wrought Aluminum (WA)
70
60
V
./
.¡¡; .><
1/
40
~ (J)
30
20
10
/
420
Composition: AI-5.6Zn-2.2Mg-l.5Cu-0.21 Cr-low Si,Fe,Mn,Ti. UNS A97475
350
Source: l.A. Dickson, "Alcoa 467 Process X7475 Alloy," Alcoa Green Letter GL 2165-70, A1uminum Co. of America, May 1970. As pub1ished in Aerospace Structural Metals Handbook, Vol 3, Code 3220, CINDASlPurdue University, 1995, p 16
280
/
~
:2 rñ Ul
v v
210
ro~
140
/
70
V
1/
WA.330 7475-T761 aluminum alloy ciad sheet, compressive stress-strain curves
490
Ihong transverse
/
rñ
/'
/
LOngitudin1
50
v
¡....--
o Strain, 0.001 inJin.
80
LOngit~
70
560
WA.331 7475-T651 aluminum alloy plate, tensile stress-strain curves
490
Tested at room temperature. Typical for plate thickness 6.350-38.10 mm (0.250-1.500 in.). Ramberg-Osgood parameter, n(longitudinal, tension) = 50; n(long transverse, tension) = 15. Composition: AI-5.6Zn-2.2Mg1.5Cu-0.21Cr-Iow Si,Fe,Mn,Ti. UNS A97475
r n g transverse
60
/
50
/
30 20 10
420
/
V
350
V
:2
280
rñ
~
ro 210
IV
140
70
2
Source: MIL-HDBK-5H, 1 Dec 1998, p 3--441
a.
4
6 8 Strain, 0.001 in./in.
10
Wrought Aluminum (WA)/491
14
Compressive tangent modulus, GPa 28 42 56
70
WA.332 7475-T651 aluminum alloy plate, compressive stress-strain and compressive tangent modulus curves
84
560
70
490
60
420
50
350
Tested at room temperature. Typical for plate thickness 6.350-38.10 mm (0.250-1.500 in.). Ramberg-Osgood parameter, n(longitudinal, compression) = 15; n(long transverse, compression) = 18. Composition: Al-5.6Zn2.2Mg-1.5Cu-0.21Cr-low Si,Fe,Mn,Ti. UNS A97475 Source: MIL-HDBK-5H, 1 Dec 1998, p 3-441
a.'"
.¡;;
::;¡; 280 ui rJ)
-'"
gf 40
~
~ 30
210
20
140
10
70
2
4
6 8 10 Strain, 0.001 in.lin. Compressive tangent modulus, 106 psi
0 12
80
560
WA.333 7475-T7351 aluminum alloy plate, tensile stress-strain curves
70
490
Tested at room temperature. Typical for plate thickness 12.70-101.60 mm (0.500-4.000 in.). Ramberg-Osgood parameter, n(longitudinal, tension) = 15; n(long transverse, tension) = 13; n(short transverse, tension) = 13. Composition: Al-5 .6Zn-2.2Mg-l.5Cu-0.21 Cr-low Si,Fe,Mn,Ti. UNS A97475
Longitudinal and long transverse l
60
y ~sverse
50
V
30
20
10
/
/
/
420
350
&.
::;¡; 280 ui
/
~
210
140
70
2
4
6 8 Strain, 0.001 in.lin.
10
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-448
492/Wrought Aluminum (WA)
80
o
14
Compressive tangent modulus, GPa 28 42 56
70
70
490
60
420
50
350
~
Tested at room temperature. Typical for plate thickness 12.70-101.60 mm (0.500-4.000 in.). Ramberg-Osgood parameter, n(longitudinal, compression) = 20; n(long transverse, compression) = 20; n(short transverse, compression) = 19. Composition: AI-5.6Zn-2.2Mg-1.5Cu0.21Cr-Iow Si,Fe,Mn,Ti. UNS A97475 ro
o..
~
li
WA.334 7475-T7351 aluminum alloy plate, compressive stress-strain and compressive tangent modulus curves
84 560
Source: MIL-HDBK-5H, 1 Dec 1998, p 3--448
::;; 280 ui U)
40
~
(j)
(j) 30
210
20
140
10
70
2
10 6 8 Strain, 0.001 in.lin. 6 Compressive tangent modulus, 10 psi 4
0 12
80
560
WA.335 7475-T7651 aluminum alloy plate, tensile stress-strain curves
70
490
Tested at room temperature. Typical for plate thickness 6.350-38.10 mm (0.250-1.500 in.). Ramberg-Osgood parameter, n(longitudinal, tension) = 33; n(long transverse, tension) = 19. Composition: AI-5.6Zn-2.2Mg1.5Cu-0.21Cr-Iow Si,Fe,Mn,Ti. UNS A97475
Transve~¡"'--
Long transverse
60
/
50
/
30
20
10
420
/ V
350
V
ro
o..
::;; 280
~
210
V
140
70
2
li (j)
4
8 6 Strain, 0.001 in.lin.
10
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-458
Wrought Aluminum (WA)/493
WA.3367475-T7651 aluminum alloy plate, compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
14
70
.::::::::
28
56
/ LoL transver1 " ~LOngitudinal
-......:::: f:::::::::-..,
60
/
50
~
¡---:::::::
/
20
/
84 560
70
Tested at room temperature. Typical for plate thickness 6.350-38.10 mm (0.250-1.500 in.). Ramberg-Osgood parameter, n(longitudinal and long transverse, compression) = 20. Composition: Al-5.6Zn-2.2Mg-1.5Cu-0.21Crlow Si,Fe,Mn,Ti. UNS A97475
490
~
~~
"
V
30
10
42
/
420
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-458
350 ro Il. ::¡;
280
uf
'"~
éi.í
210
140
/
70
2
6 8 10 Strain, 0.001 in./in. Compressive tangent modulus, 106 psi 4
90
630
WA.337 7475-T61 aluminum alloy sheet, tensile stress-strain curves (full range)
560
Tested at room temperature. Typical for sheet thickness 1.016-6.325 mm (0.040-0.249 in.). Composition: AI5.6Zn-2.2Mg-l.5Cu-0.21Cr-low Si,Fe,Mn,Ti. UNSA97475
Long tJnsverse
80 70
r7t-
Lon itudinal
r--~
~ 490
60
420
50
350 ~
éi.í 40
~ 280 ~
g¡
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-442 ro
~ ~
en
30
210
20
140
10
70
0.02
0.04
0.06
0.08
Strain, in./in.
0.10
0.12
o
0.14
494/Wrought Aluminum (WA)
80
60
"'rñ"
~
ro
40
/
/ 2
/
~
Tested at room temperature. Typical for sheet thickness 1.016-6.325 mm (0.040-0.249 in.). Ramberg-Osgood parameter, n(longitudinal, tension) =33; n(long transverse, tension) = 16. Composition: AI-5.6Zn-2.2Mg1.5Cu-0.21Cr-Iow Si,Fe,Mn,Ti. UNS A97475
560
Longitudinal
·00
20
WA.338 7475-T61 aluminum alloy sheet, tensile stress-strain curves (expanded portion)
700
100
k:::::-
Long transverse
420
Source: MIL-HDBK-5H, 1 Dec 1998, p 3--439 ro
Cl.
:a; rñ
280
~
140
4
6
8
10
o
12
Strain, 0.001 in./in.
WA.339 7475-T61 aluminum alloy sheet, compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
100°r-----,14~----,28~----4,2------5T6------7TO----_,8~00
Tested at room temperature. Test direction: L, longitudinal; LT, long transverse. Typical for sheet thickness 1.016-6.325 mm (0.040-0.249 in.). Ramberg-Osgood parameter, n(longitudinal, compression) = 15; n(long transverse, compression) = 19. Composition: Al-5.6Zn2.2Mg-1.5Cu-0.21Cr-Iow Si,Fe,Mn,Ti. UNS A97475
1------j----+---+----!----+-----156o
420 ·00
ro
Cl.
"'rñ"
:a;
~
~
rñ
ro
280
~----~----~------+_-----+------~r---~140
~-----L-----J~----~----~------~~--~1~
Strain, 0.001 in./in. 6 Compressive tangent modulus, 10 psi
en
Source: MIL-HDBK-5H, 1 Dec 1998, p 3--439
Wrought Aluminum (WA)/495
80
",,,,,,,L, ~
1
~ ~~ Long transverse
60
V
1/ 1/
20
WA.340 7475-T61 aluminum alloy ciad sheet, tensile stress-strain curves
560
Tested at room temperature. Typical for sheet thickness 1.6-4.75 mm (0.063-0.187 in.). Ramberg-Osgood parameter, n(longitudinal, tension) = 26; n(long transverse, tension) = 14. Composition: Al-5.6Zn-2.2Mg-1.5Cu-0.21Crlow Si,Fe,Mn,Ti. UNS A97475
420
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-440
'" :2 a.
280 .; en ~
Ci5
140
1/ 1 1
vI
1
2
14
4
10
Compressive tangent modulus, GPa 56 28 42 Long tranLerse " "
~r--.
70
6 8 Strain, 0.001 in.lin.
/ 1/ Longitudinal,
---= ~
¡..-
R ~~ / r--:: ~
60
Ir
50
~
gf 40
g
30
20 1
10
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-440
350
'\
'"
a.
:2 280 .; en ~
Ci5 210
1/ /
140
r-l I 70
1
I I
1 1
...l
2
Tested at room temperature. Typical for sheet thickness 1.600-4.750 mm (0.063-0.187 in.). Ramberg-Osgood parameter, n(longitudinal, compression) = 15; n(long transverse, compression) = 16. Composition: Al-5.6Zn2.2Mg-1.5Cu-0.21Cr-low Si,Fe,Mn,Ti. UNS A97475
490
420
/
C/J
WA.341 7475-T61 aluminum alloy ciad sheet, compressive stress-strain and compressive tangent modulus curves
70
4
6 8 10 Strain, 0.001 in.lin. 6 Compressive tangent modulus, 10 psi
496/Wrought Aluminum (WA)
80
70
-:::::.L~ transverse L
rLT
Lon itudinal
~
"'" ~
I
'~
560
WA.342 7475-T761 aluminum alloy sheet, tensile stress-strain curves (full range)
490
Tested at room temperature. Typical for sheet thickness 1.016-6.325 mm (0.040-0.249 in.). Composition: Al5.6Zn-2.2Mg-l.5Cu-0.21Cr-low Si,Fe,Mn,Ti. UNSA97475
60
420
50
350
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-459
&.
:::;:
280
rñ (J)
~ 30
210
20
140
10
70
0.02
0.04
0.06
0.08
0.10
0.12
o
0.14
Strain, in.lin.
WA.343 7475-T761 aluminum alloy sheet, tensile stress-strain curves
8o.-----,------r-----,------r-----,-----~560
Tested at room temperature. Typical for sheet thickness 1.016-6.325 mm (0.040-0.249 in.). Ramberg-Osgood parameter, n(longitudinal, tension) = 26; n(long transverse, tension) = 16. Composition: AI-5.6Zn-2.2Mg1.5Cu-0.21Cr-Iow Si,Fe,Mn,Ti. UNS A97475
60~----+-----~----~~----~----4------1420
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-454
~'"
~
:i e
40 1-----4------+-------+------+-------+--------1 280
ro
:i ~
ro 201-----~----_+----___j------+_----_r----_1140
~----~2------L4----~6~----~8----~1~0----~1f Strain, 0.001 in.lin.
Wrought Aluminum (WA)/497
WA.344 7475-T761 aluminum alloy sheet, compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa ~____~14~__~2T8____~42~____5T6______7,0____-,8\60
Tested at room temperature. Typical for sheet thickness 1.016-6.325 mm (0.040-0.249 in.). Ramberg-Osgood parameter, n(longitudinal, compression) = 15; n(long transverse, compression) = 19. Composition: AI-5.6Zn2.2Mg-1.5Cu-0.21Cr-low Si,Fe,Mn,Ti. UNS A97475
60~-----~----~~~~~~--+------r----~420
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-454
~
~'"
gf 40 1------+------fr-------j------+------+-+------1 280
rñ
~
~
20~----~-----+---__t------+_-----+-;_--~140
Strain, 0.001 in.lin. Compressive tangent modulus, 106 psi
80 Long
70
60
~
tr~nsverse
-
l,..--
...
" '\
560
WA.345 7475-T761 aluminum alloy dad sheet, tensile stress-strain curve (full range)
490
Tested at room temperature. Typical for sheet thickness 1.016-6.325 mm (0.040-0.249 in.). Based on two 10ts. Composition: AI-5.6Zn-2.2Mg-l.5Cu-0.21Cr-low Si,Fe,Mn,Ti. UNS A97475
\
420
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-460
50
350
&.
::;
280
30
210
20
140
10
70
0.02
0.04
0.06
0.08
Strain, in.lin.
0.10
0.12
o
0.14
rñ
~
498/Wrought Aluminum (WA)
80
WA.3467475-T761 aluminum alloy ciad sheet, tensile stress-strain curves
560
Tested at room temperature. Typical for sheet thickness 1.016-1.575 mm (0.040-0.062 in.). Ramberg-Osgood parameter, n(longitudinal, tension) = 9.0; n(long transverse, tension) = 9.1. Composition: AI-5.6Zn-2.2Mg1.5Cu-0.21Cr-Iow Si,Fe,Mn,Ti. UNS A97475
LOngit~~ ~
60
/
20
/
/
Long transverse
7
420
ro
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-455
[L
::2:
280 I/l cñ
V
~
(¡j
140
/ /
/
4
2
6
10
8
Strain, 0.001 in./in.
14
Compressive tangent modulus, GPa 28 42 56
WA.3477475-T761 aluminum alloy ciad sheet, compressive stress-strain and compressive tangent modulus curves
84 560
70
Tested at room temperature. Typical for sheet thickness 1.016-1.575 mm (0.040-0.062 in.). Ramberg-Osgood parameter, n(longitudinal, compression) = 12; n(long transverse, compression) = 16. Composition: Al-5.6Zn2.2Mg-1.5Cu-0.21Cr-Iow Si,Fe,Mn,Ti. UNS A97475
490
70
~ong transvE!rs~
:::: ......
60
Longitudinal
"'-.
~
r-=;t<= / ~
420
..........
50
V
30
/
20
/
ro
[L
::2:
280 I/l cñ
\
~
(¡j
210
140
// 10
"-
....
/
70 I I
/
/
I
2
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-456
350
..............
10 6 8 Strain, 0.001 in./in. 6 Compressive tangent modulus, 10 psi
4
Wrought Aluminum (WA)/499
80 70
LOngitud~~ ~
60
/
50
i
I
30 20
// 10
/
/
Long transverse
V
560
WA.3487475-1761 aluminum alloy dad sheet, tensile stress-strain curves
490
Tested at room temperature. Typical for sheet thickness 1.600-4.750 mm (0.063-0.187 in.). Ramberg-Osgood parameter, n(longitudinal, tension) = 9.0; n(long transverse, tension) = 9.1. Composition: AI-5.6Zn-2.2Mgl.5Cu-0.21Cr-Iow Si,Fe,Mn,Ti. UNS A97475
420
350
V
Souree: MIL-HDBK-5H, 1 Dee 1998, p 3-455
210
140
70
/ /
/
2
4
6 8 Strain, 0.001 in.lin.
10
WA.349 7475-1761 aluminum alloy dad sheet, compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
8oor-----~1.~4----~2~8----~42~----~56~----7~0~--~8\60
Tested at room temperature. Typical for sheet thickness 1.600-4.750 mm (0.063-0.187 in.). Ramberg-Osgood parameter, n(longitudinal, compression) = 12; n(long transverse, compression) = 16. Composition: Al-5.6Zn2.2Mg-1.5Cu-0.21Cr-low Si,Fe,Mn,Ti. UNS A97475
60~----~~~79~~--4_~~~~----+_----_1420
Souree: MIL-HDBK-5H, 1 Dee 1998, p 3-457
~ 8: :2 gf 40 ~---+---____jf-----4_----__+---_\++_----_l 280
w
20
140
... ,
/
I
/
I
/
I
/
O O
2
4
6 8 Strain, 0.001 in.lin.
Compressive tangent modulus, 106 psi
10
0 12
500/Wrought Aluminum (WA)
80
WA.350 7475-T761 aluminum alloy ciad sheet, tensile stress-strain curves
560
Long i t U % i::= ¿ Long transverse
60
/
20 1
I
/'
Tested at room temperature. Typical for sheet thickness 4.775-6.325 mm (0.188-0.249 in.). Ramberg-Osgood parameter, n(longitudinal, tension) = 9.0; n(long transverse, tension) = 9.1. Composition: Al-5.6Zn-2.2Mg1.5Cu-0.21Cr-low Si,Fe,Mn,Ti. UNS A97475
420
m ::2:
Source: MIL-HDBK-5H, 1 Dec 1998, p 3-456
c..
280
V
uf
~
140
1 1 1
~I 2
4
6
8
10
Strain, 0.001 in./in.
Compressive tangent modulus, GPa
8oor-----,14------,28------4T2------5T6------7ro-----.8~60
WA.351 7475-T761 aluminum alloy ciad sheet, compressive stress-strain and compressive tangent modulus curves
Tested at room temperature. Typical for sheet thickness 4.775-6.325 mm (0.188-0.249 in.). Ramberg-Osgood parameter, n(longitudinal, compression) = 12; n(long transverse, compression) = 16. Composition: Al-5.6Zn2.2Mg-1.5Cu-0.21Cr-Iow Si,Fe,Mn,Ti. UNS A97475 Source: MIL-HDBK-5H, 1 Dec 1998, p 3-457
140
20 \ \
1
I I I
1 1 1 O O
2
4
6 8 Strain, 0.001 in./in.
Compressive tangent modulus, 106 psi
10
0 12
Wrought Aluminum (WA)/501
80
60 ~ rñ
'" ~
40
20
WA.352 8090-T8 aluminum alloy plate, monotonic and stabilized cyclic stress-strain curves
700
100
r
~
560
Solution heat treated with cold water quench followed by 3% stretch and artificial aging at 198 oC (389 °P) for 16 h. Test direction: Longitudinal. Composition: AI2.5Li-1.3Cu-1.0Mg. UNS A98090
420
Source: K.T. Venkateswara Rao and R.O. Ritchie, Fatigue of Aluminum Lithium Alloys, Int. Mater. Rev., 1992. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3225, CINDASlPurdue University, 1995, p 26
~
! /1
al
a. ::¡; rñ
280 O Monotonic • Cyclic R =-1
140
0.01
0.02 Total strain, %
0.03
o
0.04
'" ~
Aluminum Laminates (LA)/503
Aluminum Laminates (LA) 60
420
LA.001 2024-T3 aluminum alloy, aramid-fiberreinforced sheet laminate (AMS 4254), 2/1 lay-up, typical tensile stress-strain curves
350
Thickness, 0.81 mm (0.032 in.). Ultimate tensile strength: longitudinal, 621 MPa (90 ksi); long transverse, 331 MPa (48 ksi). Tensile yield strength: longitudinal, 331 MPa (48 ksi); long transverse, 228 MPa (33 ksi). RambergOsgood parameter, n(long transverse, tension) = 12
/' j"',"diMI 50
lí
40
280
//
Long transverse
Source: MIL-HDBK-5H, Dec 1998, p 7-34
W v
20
10
1.--
)
140
70
1/
2
4
6
8
10
Strain, 0.001 in./in.
60
/
I
50
I I
40
/V
10
...........
2
Thickness, 1.35 mm (0.053 in.). Ultimate tensile strength: longitudinal, 662 MPa (96 ksi); long transverse, 303 MPa (44 ksi). Tensile yield strength: longitudinal, 338 MPa (49 ksi); long transverse, 207 MPa (30 ksi). RambergOsgood parameter, n(long transverse, tension) = 9.9
!--- Long transverse
a.'"
:2
210 (/)
/;
V
350
280
// V
20
LA.002 2024-T3 aluminum alloy, aramid-fiberreinforced sheet laminate (AMS 4254),3/2 lay-up, typical tensile stress-strain curves
LOngitudinll
/
i
420
70
4
6 8 Strain, 0.001 in.lin.
10
Source: MIL-HDBK-5H, Dec 1998, p 7-34
504/Aluminum Laminates (LA)
60
50
/
40
/V
2
4
6 8 Strain, 0.001 in.lin.
/
V
10
420
LA.004 2024-T3 aluminum alloy, aramid-fiberreinforced sheet laminate (AMS 4254),5/4 lay-up, typical tensile stress-strain curves
350
Thickness, 2.39 mm (0.094 in.). Ultimate tensile strength: longitudinal, 696 MPa (101 ksi); long transverse, 290 MPa (42 ksi). Tensile yield strength: longitudinal, 338 MPa (49 ksi); long transverse, 207 MPa (30 ksi). Ramberg-Osgood parameter, n(long transverse, tension) = 12
Longitudinl
/
280
//
'"
[L
:;¡;
___ Long transverse
210 cñ
~
1// V
(f)
140
/;
2
Source: MIL-HDBK-5H, Dec 1998, p 7-35
'" ~
70
40
I
'"
[L
:;¡; 210 cñ
140
50
10
Thickness, 1.88 mm (0.074 in.). Ultimate tensile strength: longitudinal, 696 MPa (101 ksi); long transverse, 296 MPa (43 ksi). Tensile yield strength: longitudinal, 338 MPa (49 ksi); long transverse, 207 MPa (30 ksi). Ramberg-Osgood parameter, n(long transverse, tension) = 11
...... ( - - Long transverse
60
20
350
280
/;
V
LA.003 2024-T3 aluminum alloy, aramid-fiberreinforced sheet laminate (AMS 4254), 4/3 lay-up, typical tensile stress-strain curves
LOngitudinll
/
1// V
20
10
V
420
70
4
6 Strain, 0.001 in.lin.
8
10
Source: MIL-HDBK-5H, Dec 1998, p 7-35
Aluminum laminates (lA)/505
LA.005 2024-T3 aluminum alloy, aramid-fiberreinforced sheet laminate (AMS 4254),2/1 lay-up, typical compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
o
14
28
42
56
70
84
5or-----~-----,------.------.------~----_,350
Thickness, 0.81 mm (0.032 in.). Compressive yield strength: longitudinal, 241 MPa (35 ksi); long transverse, 228 MPa (33 ksi). Ramberg-Osgood parameters: n(longitudinal, compression) = 13; n(long transverse, compression) = 12 210 ro o..
'00
""ui '"~
Source: MIL-HDBK-5H, Dec 1998, p 7-36
::?! ui IJ)
é'i5
140
~
~~~~-----~~----4_----_4----~+_----_470
L------21-.----~4~----~6------~8----~~10----~1f
Strain, 0.001 in.lin. Compressive tangent modulus, 106 psi
LA.006 2024-T3 aluminum alloy, aramid-fiberreinforced sheet laminate (AMS 4254), 3/2 lay-up, typical compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
14 SO°r------r -----,2-8--.---,42------,S6------7,0------,8\SO
Thickness, 1.35 mm (0.053 in.). Compressive yield strength: longitudinal, 241 MPa (35 ksi); long transverse, 207 MPa (30 ksi). Ramberg-Osgood parameters: n(longitudinal, compression) = 13; n(long transverse, compression) = 13
r-~~-r~--~~~---4_~~~------+_-----1280
210 ro o..
'00
""ui
::?! ui
'" ~
'"
~
140
~~~-~----~------4_----~----4-+_-----470
~----~2~_----~4~----~6-----L~8----~1~0----~1f Strain, 0.001 in.lin. Compressive tangent modulus, 10 6 psi
é'i5
Source: MIL-HDBK-5H, Dec 1998, p 7-36
506/Aluminum Laminates (LA)
lA.007 2024-T3 aluminum alloy, aramid-fiberreinforced sheet laminate (AMS 4254), 4/3 lay-up, typical compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
50°r------1,4-----,28------~42~----5T6~--~7TO----~8\50
__--'<:--+_----+----+---+-----1-----1
Thickness, 1.88 mm (0.074 in.). Compressive yield strength: longitudinal, 234 MPa (34 ksi); long transverse, 207 MPa (30 ksi). Ramberg-Osgood parameters: n(longitudinal, compression) = 12; n(long transverse, compression) = 12
280
210
~
ro a. :;¡;
Source: MIL-HDBK-5H, Dec 1998, p 7-37
'"~
ii5
140
~'" (f)
1---,~~----__+------+_---+-+--__+1__+_----~70
L-----~----~------~--~~--~~~----~O
2
6 8 10 Strain, 0.001 in./in. 6 Compressive tangent modulus, 10 psi
4
12
lA.008 2024-T3 aluminum alloy, aramid-fiberreinforced sheet laminate (AMS 4254), 5/4 lay-up, typical compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
50°,------1,4-----,28------,42------5,6------7TO-----,8\50
Thickness, 2.39 mm (0.094 in.). Compressive yield strength: longitudinal, 228 MPa (33 ksi); long transverse, 207 MPa (30 ksi). Ramberg-Osgood parameters: n(longitudinal, compression) = 12; n(long transverse, compression) = 12
401--------1-----~------+-----_+------~----~280
.¡¡;
210 ro a.
30
:;¡;
"'
'"
ii5
140
20
101--~~--1-----~------+---1---+---+--~----~70
L------2L-----~4------~6---L--~--~-1~0----~1~
Strain, 0.001 in./in. Compressive tangent modulus, 106 psi
~
Source: MIL-HDBK-5H, Dec 1998, p 7-37
Aluminum laminates (lA)/507
100
lL~,;"",
80
60 'iii
'"uf U)
~
40
LA.009 2024-T3 aluminum alloy, aramid-fiberreinforced sheet laminate (AMS 4254), 2/1 lay-up, typical tensile stress-strain curves (full range)
700
Thickness, 0.81 mm (0.032 in.). Ultimate tensile strength: longitudinal, 621 MPa (90 ksi); long transverse, 331 MPa (48 ksi). Tensile yield strength: longitudinal, 331 MPa (48 ksi); long transverse, 228 MPa (33 ksi)
560
I
I
420
~~
~
Source: MIL-HDBK-5H, Dec 1998, change notice 1, Oct 2001, P 7-38
&. ;:¡; uf
Long transverse 280
V
20
~
140
30
60
90 120 Strain, 0.001 in./in.
150
120
l'
100
o
180
840
LA.010 2024-T3 aluminum alloy, aramid-fiberreinforced sheet laminate (AMS 4254),3/2 lay-up, typical tensile stress-strain curves (full range)
700
Thickness, 1.35 mm (0.053 in.). Ultimate tensile strength: longitudinal, 662 MPa (96 ksi); long transverse, 303 MPa (44 ksi). Tensile yield strength: longitudinal, 338 MPa (49 ksi); long transverse, 207 MPa (30 ksi)
/ L"",n",;O" 80
560
/
Source: MIL-HDBK-5H, Dec 1998, change notice 1, Oct 2001, P 7-38
&. ;:¡; 420
1 40
Long transverse 280
I(
20
140
30
60
90 120 Strain, 0.001 in./in.
150
188
uf
~
508/Aluminum Laminates (LA)
120
r
100
840
LA.Oll 2024-T3 aluminum alloy, aramid-fiberreinforced sheet laminate (AMS 4254), 4/3 lay-up, typical tensile stress-strain curves (full range)
700
Thickness, 1.88 mm (0.074 in.). Ultimate tensile strength: longitudinal, 696 MPa (101 ksi); long transverse, 296 MPa (43 ksi). Tensile yield strength: longitudinal, 338 MPa (49 ksi); long transverse, 207 MPa (30 ksi)
/""9''''';"'' 80
560
I
40
Source: MIL-HDBK-5H, Dec 1998, change notice 1, Oct 2001, P 7-39
'" ::¡; a.
420 cñ
I
~
Long transverse 280
I~
20
140
30
60
90
120
150
o
180
Strain, 0.001 in.lin.
120
r
100
840
LA.012 2024-T3 aluminum alloy, aramid-fiberreinforced sheet laminate (AMS 4254), 5/4 lay-up, typical tensile stress-strain curves (full range)
700
Thickness, 2.39 mm (0.094 in.). Ultimate tensile strength: longitudinal, 696 MPa (101 ksi); long transverse, 290 MPa (42 ksi). Tensile yield strength: longitudinal, 338 MPa (49 ksi); long transverse, 207 MPa (30 ksi)
/ L009;""'" 560
80
Source: MIL-HDBK-5H, Dec 1998, change notice 1, Oct 2001, P 7-39
I
40
I
Long transverse
Ir
280
140
20
30
60
90 Strain, 0.001 in.lin.
120
150
Aluminum laminates (lA)/509
100
700
80
560
60
420
'00
LA.OH 7475-T761 aluminum alloy, aramid-fiberreinforced sheet laminate (AMS 4302),2/1 lay-up, typical tensile stress-strain curves
!ti
o..
"'rñ"
:2 rñ
'"~
Thickness, 0.81 mm (0.032 in.). Ultimate tensile strength: longitudinal, 710 MPa (103 ksi); long transverse, 386 MPa (56 ksi). Tensile yield strength: longitudinal, 524 MPa (76 ksi); long transverse, 331 MPa (48 ksi). Ramberg-Osgood parameters: n(longitudinal, tension) = 6.4; n(long transverse, tension) = 6.1 Source: MIL-HDBK-5H, Dec 1998, p 7-42
'"~
iñ
280
40
iñ
~----~~---+-----~------+-----~----~140
~----~2·------L4-----~6------~8----~1~0----~1~
Strain, 0.001 in.lin.
100
700
80
560
60
420
'00
LA.014 7475-T761 aluminum alloy, aramid-fiberreinforced sheet laminate (AMS 4302), 3/2 lay-up, typical tensile stress-strain curves
!ti
o..
"'rñ" '"~
:2 rñ
'"~
iñ
40
280
2
4
6
Strain, 0.001 in.lin.
8
10
iñ
Thickness, 1.35 mm (0.053 in.). Ultimate tensile strength: longitudinal, 765 MPa (111 ksi); long transverse, 352 MPa (51 ksi). Tensile yield strength: longitudinal, 565 MPa (82 ksi); long transverse, 296 MPa (43 ksi). Ramberg-Osgood parameters: n(longitudinal, tension) = 5.2; n(long transverse, tension) = 5.8 Source: MIL-HDBK-5H, Dec 1998, p 7-42
510/ Aluminum Laminates (LA)
LA.015 7475-T761 aluminum alloy, aramid-fiberreinforced sheet laminates (AMS 4302), 4/3 and 5/4 lay-ups, typical tensile stress-strain curves
,-----,------,-----,------r-----,------,700
~----+-----~-----+------~_7L-4_----~560
420 "¡¡;
ro
o..
"'rñ"
:2 rñ IJ)
IJ)
~
~
Ci5
280
Ci5
Data for 4/3 lay-up: Thickness, 1.88 mm (0.074 in.). Ultimate tensile strength: longitudinal, 786 MPa (114 ksi); long transverse, 345 MPa (50 ksi). Tensile yield strength: longitudinal, 565 MPa (82 ksi); long transverse, 290 MPa (42 ksi). Ramberg-Osgood parameters: n(longitudinal, tension) = 5.5; n(long transverse, tension) = 7.5. Data for 5/4lay-up: Thickness, 2.39 mm (0.094 in.). Ultimate tensile strength: longitudinal, 800 MPa (116 ksi); long transverse, 331 MPa (48 ksi). Tensile yield strength: longitudinal, 579 MPa (84 ksi); long transverse, 276 MPa (40 ksi). Ramberg-Osgood parameters: n(longitudinal, tension) = 5.7; n(long transverse, tension) = 6.4 Source: MIL-HDBK-5H, Dec 1998, p 7-43
4
6
8
10
Strain, 0.001 in./in.
LA.0167475-T761 aluminum alloy, aramid-fiberreinforced sheet laminate (AMS 4302),2/1 lay-up, typical compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa
80 0, -____,14______2,8____-,42______5,6____-,70____--,8\60
60~~
Thickness, 0.81 mm (0.032 in.). Compressive yield strength: longitudinal, 317 MPa (46 ksi); long transverse, 352 MPa (51 ksi). Ramberg-Osgood parameters: n(longitudinal, compression) =6.7; n(long transverse, compression) = 13
__+_----~----_+------r_----4-----~420
ro
~
~
gf 40 ~----+-----~~-+___F~---".--~----4_----~ 280 gf
E
~
C/)
Ci5
20~----~~--~----_+----~r_--~4-----~140
Strain, 0.001 in./in. 6 Compressive tangent modulus, 10 psi
Source: MIL-HDBK-5H, Dec 1998, p 7-43
Aluminum laminates (lA)/511
80~----~----~~----,------,------,------,560
LA.017 7475-T761 aluminum alloy, aramid-fiberreinforced sheet laminate (AMS 4302), 3/2 lay-up, typical compressive stress-strain and compressive tangent modulus curves
60~----~-----~------4-----~------+-----~420
Thickness, 1.35 mm (0.053 in.). Compressive yield strength: longitudinal, 317 MPa (46 ksi); long transverse, 331 MPa (48 ksi). Ramberg-Osgood parameters: n(longitudinal, compression) = 6.2; n(long transverse, compression) = 14
Compressive tangent modulus, GPa
o
14
28
42
56
70
84
g¡'"
~
Source: MIL-HDBK-5H, Dec 1998, p 7-44
gf 40 1---------1-------+------;p~__t_=""'=L-__+------+_----___j 280 gf
~
~
20~----~~~-1------1_--_+_+----+_+_----~140
~----~2------~4------~6----L-~8-----LL-----~1f
Strain, 0.001 in.lin. 6 Compressive tangent modulus, 10 psi
Compressive tangent modulus, GPa
80 0.------1,4-----,28------,42------5,6------7,0------,8\60
601--------~----__+------~----__+------+-----___1420
LA.018 7475-T761 aluminum alloy, aramid-fiberreinforced sheet laminates (AMS 4302), 4/3 and 5/4 lay-ups, typical compressive stress-strain and compressive tangent modulus curves Data for 4/3 lay-up: Thickness, 1.88 mm (0.074 in.). Compressive yield strength: longitudinal, 303 MPa (44 ksi); long transverse, 324 MPa (47 ksi). RambergOsgood parameters: n(longitudinal, compression) = 5.3; n(long transverse, compression) = 15. Data for 5/4 layup: Thickness, 2.39 mm (0.094 in.). Compressive yield strength: longitudinal, 303 MPa (44 ksi); long transverse, 310 MPa (45 ksi). Ramberg-Osgood parameters: n(longitudinal, compression) = 5.8; n(long transverse, compression) = 14 Source: MIL-HDBK-5H, Dec 1998, p 7-44
201-------~_7~__+------~--+___+----~+-----___1140
Strain, 0.001 in.lin. Compressive tangent modulus, 106 psi
512/Aluminum Laminates (LA)
120
840
LA.019 7475-T761 alurilinum alloy, aramid-fiberreinforced sheet laminate (AMS 4302), 2/1 lay-up, typical tensile stress-strain curves (full range)
700
Thickness, 0.81 mm (0.032 in.). Ultimate tensile strength: longitudinal, 710 MPa (103 ksi); long transverse, 386 MPa (56 ksi). Tensile yield strength: longitudinal, 524 MPa (76 ksi); long transverse, 331 MPa (48 ksi)
/7100
/'",I"'IM'
80
40
20
560
(
ro
//
¡..---
20 30 Strain, 0.001 in.lin.
10
1ií
40
h,t"',,,,
100
/
V
840
LA.020 7475-T761 aluminum alloy, aramid-fiberreinforced sheet laminate (AMS 4302), 3/2 lay-up, typical tensile stress-strain curves (full range)
700
Thickness, l.35 mm (0.053 in.). Ultimate tensile strength: longitudinal, 765 MPa (111 ksi); long transverse, 352 MPa (51 ksi). Tensile yield strength: longitudinal, 565 MPa (82 ksi); long transverse, 296 MPa (43 ksi)
560
/
ro
o.. :2
//
~
Long transverse
420 ui en E:!
1ií
280
f
V
420 ui en E:!
280
120
20
-- -~
140
V
40
-
Long transverse
f
80
Source: MIL-HDBK-5H, Dec 1998, p 7--45
o.. :2
140
10
30 20 Strain, 0.001 in.lin.
40
Source: MIL-HDBK-5H, Dec 1998, p 7--46
Aluminum laminates (lA)/513
LA.021 7475-T761 aluminum alloy, aramid-fiberreinforced sheet laminate (AMS 4302),4/3 lay-up, typical tensile stress-strain curves (full range)
980
140
l><
120
840
Thickness, 1.88 mm (0.074 in.). Ultimate tensile strength: longitudinal, 786 MPa (114 ksi); long transverse, 345 MPa (50 ksi). Tensile yield strength: longitudinal, 565 MPa (82 ksi); long transverse, 290 MPa (42 ksi)
rngitudinal 100
/ //
.;
E
(/) 60
40
20
I
I
~ 80
f V
700
Source: MIL-HDBK-5H, Dec 1998, p 7-47 560 ~
::;;: .;
'"~
420 éi5 -~
Long transverse
~
280
140
o
30 20 Strain, 0.001 in./in.
10
O
40
120
100
/ /
80
40
20
A"'dIMI
LA.022 7475-T761 aluminum alloy, aramid-fiberreinforced sheet laminate (AMS 4302),5/4 lay-up, typical tensile stress-strain curves (full range)
700
Thickness, 2.39 mm (0.094 in.). Ultimate tensile strength: longitudinal, 800 MPa (116 ksi); long transverse, 331 MPa (48 ksi). Tensile yield strength: longitudinal, 579 MPa (84 ksi); long transverse, 276 MPa (40 ksi)
560
I
Source: MIL-HDBK-5H, Dec 1998, p 7-48
~ ::;;:
;,~ ..--
420 .;
'"~
éi5 Long transverse 280
f
V
840
140
10
20 30 Strain, 0.001 in./in.
40
Copper (Cu)/515
Copper (CU) 90
630
80
560
70
60 ~ 50
~
éi5 40
¡.....--
~
1( ,...--......
--- "-76K\ 195
K
~
V
""4~
295
Cold drawn 60%. Bar thickness: 19 mm (3/4 in.) 490 1\20
K
ro
350 ~ rñ
IJ)
280
K\ '
30
~ (f)
210
~
20
140
10
70
0.3
0.2
0.1
SOUTce: R.P. Reed and R.P. Mikesell, Low Temperature Mechanical Properties of Copper and Selected Copper Alloys, NBS Monograph 101, Institute for Materia1s Research, Nationa1 Bureau of Standards, 1967
420
l\
\
Cu.OOl Oxygen-free copper (UNS Cl0200) bar, stress-strain curves showing effect of low temperatures
0.4
o
0.6
0.5
Strain, in.lin.
60
Cu.002 Electrolytic tough-pitch copper (UNS Cll000) strip, stress-strain curves showing effect of cold rolling
420
1 55
V-/'
50
/
45 40
g¡ gf ~
30
/
éi5 25
2- 350
-3
V ....
./
~ ~ ----
/)~
~
V
0.5
280
4
175 140 105
70 5
r-
35 2
2.5 3 3.5 4 Strain, 0.001 in.lin.
4.5
&.
:2 210 rñ
"-
1.5
315
245
/. 1//
15
5
/v
1--r-...-V
V~V
20
10
/
/ V 1/V J
._ 35
V
385
¡.-
5
5.5
~
(f)
Copper strip 1.0 mm (0.040 in.) thick, having a ready-tofinish grain size of 0.015 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 /..lm (lO /..lin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the closest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, half hard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 371°C (700 °F) for 1 h SOUTce: RA. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 7
516/Copper (Cu)
60
---
55 50 45 40
/-V
._ 35 ~
/
gf 30 !!! é'i5 25
ij
lA
20 15 10 5
~
/Ij//
/'
~ /'
V
v
~
!-""
V V
280 245 ca a. :2 210 ui 175
'" ~
en
140 105
hV
5
70 35
lr
1.5
2
2.5 3 3.5 4 Strain, 0.001 in.lin.
4.5
5
--
./
60
V
/~V
50
/f /'
11;~
~~
V
.--295 K
[-195
Cu.004 Phosphorus-deoxidized, high residual phosphorus (UNS C12200) bar, stress-strain curves showing effect of low temperatures
490
Bar in annealed condition. Bar thickness: 19 mm (3/4 in.) t\K 420
~
76 K\
~
350
\
ca :2
a.
280 !Ji
:1<
i
\
1\ \
en 210
k
140
l' 0.1
70
0.2
0.3
Source: R.P. Reed and R.P. Mikesell, Low Temperature Mechanical Properties of Copper and Selected Copper Alloys, NBS Monograph 101, Institute for Materia1s Research, Nationa1 Bureau of Standards, 1967
-4K'
~
Copper strip 1.0 mm (0.040 in.) thick, having a ready-tofinish grain size of 0.045 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 ¡.tm (10 ¡.tin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the c10sest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, halfhard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 427 oC (800 °P) for 1 h Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 7
5.5
560
70
10
315
4- r----
f-- ¡--
80
20
350
3
~
V
385 1
2
1//"
0.5
30
Cu.003 Electrolytic tough-pitch copper (UNS Cl1000) strip, stress-strain curves showing effect of cold rolling
420
0.4 0.5 0.6 Strain, in.lin.
0.7
0.8
0.9
o
1.0
Copper (Cu)/517
560
Cu.005 Phosphorus-deoxidized, high residual phosphorus (UNS C12200) bar, stress-strain curves showing effect of low temperatures
490
Bar cold drawn 26% and aged. Bar thickness: 19 mm (3/4 in.)
630
90 80
...--
/
70
~
.-
.......
'~5K
60
r--
~ 50
4K
~ ~ i'ií 40
~20K
1\
,,\K
\
\
'""'\ \ 295~
30
420 350
(J)
280 (/) ~
\
210
20
140
10
70
o
0.1
O
g¡'"
Source: R.P. Reed and R.P. Mikesell, Low Temperature Mechanical Properties oi Copper and Selected Copper Alloys, NBS Monograph 101, Institute for Materials Research, National Bureau of Standards, 1967
0.3
0.2
o
0.5
0.4
0.6
Slrain, in./in.
420
60 55
50
v
/'
45 40 ._ 35 1i
I
iliJo
~
~
i'ií 25
~~ /" ...........
~~
20
15
/
10
I
5
o
Y
O
---
385
.-- 1
350
-
!-"2
/ /f' /'~ / -
315 280
---
3
245 a.'" ~
210
4
~
175 i'ií 140
J"
105 70
I
I
5
35
~I 2
3
4
5
6
Cu.006 Arsenical tough-pitch copper (UNS C14200) strip, stress-strain curves showing effect of cold rolling
7
Slrain, 0.b01 in./in.
8
9
10
Copper (99,50% Cu, 0.45% As) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.050 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 !lm (10 !lin.) were used. These tests were conducted in accOfdance with ASTM E 8. The tests predate the UNS designations, but the closest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA). It was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%, temper, half hard. Curve 4: B&S, 1; RA, 11.0%; temper, quarterhard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 704 oC (1300 °P) for 1 h Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 21
518/Copper (Cu)
60
v
55
/
50
40 ._ 35 g¡ ~
25
,J J'
20 15
2,~. 1,3
10
I
5
o
lI"
O
.......
1/
60 ~ 50
40
0
280 245
4
:2:
210 Ul
70
5
35 4
5
v---- \ ~K
6 7 8 0.001 in.lin.
,\ \
76
9
10
4K~ ::"\.20 K
11
~
Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 21
630
Cu.008 Zirconium copper (UNS C15000) bar, stressstrain curves showing effect of low temperatures
560
Bar cold drawn and aged. Bar thickness: 19 mm (3/4 in.). Composition: 0.18% Zr
490
Source: R.P. Reed and R.P. Mikesell, Low Temperature Mechanical Properties of Copper and Selected Copper Alloys, NBS Monograph 101, Institute for Materials Research, National Bureau of Standards, 1967
420
"
350
280 (f) ~
30
210
20
140
10
70
0.2
§;:'"
\
0.3 Strain, in.lin.
0.4
0.5
Copper (99.50% Cu, 0.45% As) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.020 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 ¡..tm (10 ¡..tin.) were used. Tested in accordance with ASTM E 8. The tests predate the UNS designations, but the closest current designation is given for reference. The cold working of each curve was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage units and the reduction in area (RA) and assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, half hard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed 371 ° C (700 °P) for 1 h
o
12
K
\\ \
0.1
rf
105
3
295~
315 _3
140
~
~
350
V
~
90
70
385
175
Strain,
80
Cu.007 Arsenical tough-pitch copper (UNS C14200) strip, stress-strain curves showing effect of cold rolling
~2
.,/
'PV
--
2
V f--
f' v
/
/
:i 30
~
~
/
45
(f)
420 1
o
0.6
Copper (Cu)/519
Cu.009 Dispersion strengthened copper (UNS C15725) plate, engineering stress-strain showing effects of temperature
400 1
ro
300
/'"
250
/~
/ VI
Il.. ::;E
'" ~
200
150
100
50
1
23.8 oC (75 °F) __
350
V
,...-¡.--
100 1oC (21 ~ °F)
.,,-
200 oC (392°F)
--
-
300 1oC
jjV V- -
Dispersion strengthened (DS) copper AL25, LOX-80 plate (99.43 eu, 0.25 Al, aluminum oxide 0.48% by weight). Plate 2.5 X 102 X 102 cm (1 X 40 X 40 in.), extruded and cross roUed, annealed at 1000 oc.
(57~ °F)
Source: J.W. Davis, ITER Material Properties Handbook, aries.ucsd.edu web site, May 2002
350 1oC (662 °F)-
......
./
/1/ IJ'1 lf
V
2
3
4
5
6
7
8
9
10
Strain, 0.001 cm/cm
Cu.Ol0 Copper beryllium (U NS Cl7200) bar and rod, TFOO temper, tensile and compressive stressstrain and compressive tangent modulus curves
eompressive tangent modulus, GPa r -____,28______5,6____-,84 ______1T12______ 14ro____-.16~400
Typical for bar and rod 41.27-101.6 mm (1.625-4.000 in.) thick. Test direction: L, longitudinal; ST, short transverse. Ramberg-Osgood parameters: n(L, tension) = 11, n(ST, tension) =9.6, n(L, compression) =7.1, n(ST, compression) = 6.7
·~----~--~~~----4------+----~1120
840 ro
.¡¡;
Il.. ::;E
""
'"
'"
~
560
40~_4--4-----_+-----_4------+---_+~----~280
L-----·~-----L-----~--
4
8
____~__~_L_ _ _ _~o
12 16 Strain, 0.001 in./in.
20 6
eompressive tangent modulus, 10 psi
24
~
Source: MIL-HDBK-5H, Dec 1998, p 7-18
520/Copper (Cu)
Cu.011 Copper beryllium (UNS Cl7200) bar and rod, TH04 temper, tensile and compressive stressstrain and compressive tangent modulus curves
Compressive tangent modulus, GPa
. -____,2~8~--~56------8~4----,_1~1-2-----1~4-0----~16~00
Typical for bar and rod 12.7-76.20 mm (0.500-3.000 in.) thick. Test direction: L, longitudinal; ST, short transverse. Ramberg-Osgood parameters: n(L, tension) = 8.0, n(ST, tension) = 7.9, n(L, compression) = 6.8, n(ST, compression) = 7.5
160~----~-----4-.~~+------+------~----~1120
840 ro (L
120 ~
Source: MIL-HDBK-5H, Dec 1998, p 7-19
;:¡;
IJ)
IJ)
~
ro
560
80
~
40~~~~----~------~----_+----+-+_----~280
L -____
~
4
____- L____
8
~
______L __ _
_L~
20
16 12 Strain, 0.001 in.lin.
____
~O
24
6
Compressive tangent modulus, 10 psi
200°r-----~28~----~56~--~8T4~----1T1~2----~1r4~0----~16~00
Cu.012 Copper beryllium (UNS Cl7200) tubing, TFOO temper, tensile and compressive stress-strain and compressive tangent modulus curves
160 1-----+-""~o__I--____z~-'b_<:"'_--___'_t_------+_----_1 1120
Typical for mechanical tubing with wall thickness 19.05-41.27 mm (0.750-1.625 in.). Test direction: L, longitudinal; ST, short transverse. Ramberg-Osgood parameters: n(L, tension) = 8.2, n(ST, tension) = 5.1, n(L, compression) = 8.6, n(ST, compression) = 8.5
Compressive tangent modulus, GPa
840 ro (L
120 ·00
;:¡;
-'"
IJ)
IJ)
~
~
ro
560
80
40 I----JL-+----~------~----_+----+_+_----~ 280
L------4L------L----~------~--~~2~0----~21
Strain, 0.001 in.lin. Compressive tangent modulus, 106 psi
ro
Source: MIL-HDBK-5H, Dec 1998, p 7-19
Copper (Cu)/521
70 65
50 45
30
/~ V
20
1$
10 5
3
315
V
280
j ~
V 0.5
¡.--
245 gf
4
~
210 iií 175 140
-1.5
8:.
:2
h'7
15
420
350
r--
--
/'/ / '
25
455
2 - 385
./
/ V / /' v
gf 35
P f---
V
VjI
~ 40
CIl
-
./
55
-1
,......
60
~
Cu.013 Copper gilding-metal (UNS C21000), stressstrain curves showing effect of cold working
490
105 5
70
Gilding-metal (94.59% Cu) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.015 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 ~m (10 ~in.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the closest current designation is given for reference. The cold working of each curve was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage units and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, halfhard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed 482 oC (900°F) for 1h
2
:1.5
3
3.5
4
4.5
5
Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 33
5.5
Strain, 0.001 in.lin.
Cu.014 Copper gilding-metal (UNS C21000) strip, stress-strain curves showing effect of cold working
420
60
¡....--
55
50
~
45
/~ ,......
40
1
---/
385
,/'
2
350 315
3
280
// . /
._ 35
// /
g¡ gf 30
/ ~ .......... V/ / '
~
iií 25
20 15 10
/)
5
o IP O
//1(/ ~ V
0.5
./
245
--
210 ui 4
175 140 105 70
-
5
r-1.5
2
2.5
3 3.5 4 Strain, 0.001 in.lin.
ro
o.. :2
4.5
5
5.5
35 6
o
~
CIl
Gilding-metal (94.59% Cu) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.070 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 ~m (10 ~in.) were used. Composition: 94.59% copper. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the closest current designation is gÍven for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, half hard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 538 oC (1000 °F) for 1 h Source: R.A. Wilkins aud E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 33
522/Copper (Cu)
90
80
70
........-:::::
~ ~
gf ~
i'i5 40
20
10
-
..... ~
¡}~v
50
30
4K
~P"
60
g¡
¡...---
v
j
~V
¡......-- 295K
& r
ro
)1(
280 (/) ~
~
gf
210
\
140
70
0.2
0.3
0.4 0.5 0.6 Strain, in./in.
0.7
0.8
60
50
h
45
~V
'00 40
V
/:V /
V
1.0
...-r
1/
V
55
o
0.9
./
~
~
~
(/) 30
/
385
-~ 350
V
315
4
280 ~ :2 245 g¡
V..,¿ V
~
210
V.6 ~
175
/ 11/ Vh V r--
15
140
5
105 70
lA V
lJ'
455
2
VI V
20
35 1.5
2
2.5 3 3.5 4 Strain, 0.001 in./in.
Cu.016 Commercial bronze (UNS C22000) strip, stress-strain curves showing effect of cold working
490
420
~
/. V;; ~
""gf 35
25
Source: R.P. Reed and R.P. Mikesell, Low Temperature Mechanical Properties of Copper and Selected Copper Alloys, NBS Monograph 101, Institute for Materia1s Research, Nationa1 Bureau of Standards, 1967
420
\
65
5
Bar was annealed. Bar thickness: 19 mm (3/4 in.) 490
350 ~
70
10
,
1\ '
195 K
/
0.1
76 K
560
,~
20 K
Cu.015 Commercial bronze (UNS C22000) bar, stress-strain curves showing effect of low temperatures
630
I
4.5
5
5.5
6
0
i'i5
Commercial bronze (government-gilding) (89.74% Cu) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.015 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 /-lm (10 /-lin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the c10sest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, halfhard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 482 oC (900°F) for 1 h Source: R.A. Wi1kins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p. 37
Copper (Cu)/523
65 60 55 50
~
45
[ij /J v V 1- V l/
40 .¡¡;
-" 35
(J)
~ 30
en
25 20 15
If
10 5
V' V IV W
¡........
V /' ~ / t::-
v
2
385 350 3 315
1--
./
--
280 ro
a..
245 :2 ~
V
O
ui
4
210 ~
ro
175 140 105 70
¿V
o
Cu.017 Commercial bronze (UNS C22000) strip, stress-strain curves showing effed of cold working
455
l-1 420
5
1.5
0.5
2
2.5
3
3.5
4
4.5
5
5.5
35 6
o
Source: RA. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 38
Strain, 0.001 inJin.
90 80
/
70
v.~
gj 50
l&V-
ro~
40 30 20
~/
~ ~
/
1¿ y
60
~~
~
n
V
---
~K
ft
Cu.018 Red-brass (UNS C23000) bar, stress-strain curves showing effed of low temperatures
560
Bar cold drawn 14%. Bar thickness: 19 mm (3/4 in.). Red brass (85% Cu, 15% Zn)
490
Source: RP. Reed and RP. Mikesell, Low Temperature Mechanical Properties of Copper and Selected Copper Alloys, NBS Monograph 101, Institute for Materials Research, National Bureau of Standards, 1967
420
:1:
~
¡i en
210 140
r¡¡
10
70
0.1
0.2
0.3
0.4
0.5
0.6
Strain, inJin.
g¡ro
280 ~
1\
\
630
350
195 K
295 K
~
76 K
0.7
0.8
0.9
Commercial bronze (govemment-gilding) (89.74% Cu) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.070 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer 0.254 !lm (10 !lin.) accurate to 0.254 !lm (10 !lin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the c10sest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, half hard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 760 OC (1400 °P) for 1 h
o
1.0
524/Copper (Cu)
90 /"'"
80
//
70
/
60
g¡
/
50
/~
cñ
~
iñ 40 30
~
20 10
I
J
~
~
L---
.,.....2
490
ro
350 ~
¡g
~-4
280 (/) ~
11'
210 140
5
~
70
3
2
4 5 6 Strain, 0.001 in.lin.
8
7
Source: RA. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 44
9
Cu.020 Red-brass (UNS C23000) strip, stress-strain curves showing effect of cold working
490
¿
V
./
55 50 45
/
40
/
¡g 35 ~
iñ 30
/
25
V ~
/ ~ ..-
/ /
~
/ ¡....--
.,.....
-
¿... 455 ~
420 385 350 3
-¡--
4
"
280
210
~
175 140 105
/1// IJ r 0.5
315
5 70 35 1.5
2
3.5 4 2.5 3 Strain, 0.001 in.lin.
i1.
:;¡;
245 rñ
/[.1:V /h ~
20
5
Red-brass (85.42% Cu) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.015 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 J.lm (10 J.lin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the closest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, half hard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 427 oC (800 °F) for 1 h
420
60
10
560
l.-- - 3
65
15
Cu.019 Red-brass (UNS C23000) strip, stress-strain curves showing effect of cold working
/""
70
'00 -'"
630 1
4.5
5
5.5
~ iñ
Red-brass (85.42% Cu) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.070 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 J.lm (lO J.lin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the closest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designatíon. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, halfhard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 593 oC (1100 °F) for 1 h Source: RA. Wi1kins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 44
Copper (Cu)/525
70 65
/
60
/1
-
/ /
55
1/V....
50
/. ~ f...--
45
g¡
Cu.021 Low-brass (UNS C24000) strip, stress-strain curves showing effect of cold working
490
3- ~ 455
.;:: ~~ ~W V/
40
gf 35 ~
¡¡¡ 30
420
1-
~
4
280 ~ :2 245 ui 210
#. v
20
15 10
,.
/J
5
o
O
350 315
~V
25
385
~ ¡¡¡
175 140
¡j ~
5
f// '/
105
70 35 1.5
0.5
2
~!.5
3
3.5
4
4.5
5
5.5
80-20 low-brass (80.41 % Cu) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.020 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 !lm (10 !lin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the c10sest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a cornmercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, half hard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 427 oC (800 °P) for 1 h Source: KA. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 50
6O
Strain, 0.001 in./in.
100 90
~/ ' 2
80
L
70
/~V
60
j /
40
J~ I~
30
V·
~
20
10
~
[;~?
f
/
....-
3
630
490 420
350 ui In ~
¡¡¡ 280
5
210 140
70
5 6 7 8 Strain, 0.001 in./in.
~
:2
4
tV
234
Cu.022 Spring-brass (UNS C25600) strip, stressstrain curves showing effect of cold rolling
700
560
V
V
-
.......
?
9
10
11
o
12
Special spring-brass (74.69% Cu) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.015 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 !lm (10 !lin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the spring brass composition is similar to C25600. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, half hard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 427 oC (800 °F) for 1 h Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 57
526/Copper (Cu)
100 90 80
gf 50
~
40
1/'
30
h~ ~ v
630
-1
/
560 2
490
V
V
/
60
V
V
/
70
V-
420
_3
4
210 140
1-'1
I
5
2
3
4
70
5
6 7 8 Strain, 0.001 in.lin.
9
10
11
100 90
V
80 70
¿
60
'/
gf 50
Ay
E'!
üí
40
~
30 20 10
J
If
'"
o.. ::2!
350 ti)rñ ~ (f) 280
¡J
20 10
Cu.023 Spring-brass (UNS C25600) strip, stressstrain curves showing effect of cold rolling
700
_1
/
O
Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 57
700
Cu.024 Cartridge brass (UNS C26000) strip, stressstrain curves showing effect of cold working
630
70-30 cartridge brass (69.83% Cu) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.015 mm. A 2268 kg (5000 lb) capacíty hydraulic testing machine and Templin automatic extensometer accurate to 0.254 /lm (10 /lin.) were used: These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the closest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a COmmercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, halfhard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 482 oC (900 °P) for 1 h
12
560
~2
490
~3
420
350 rñ
v
280 210
5
P
140 70
2
3
4 Strain,
5
0.001
6 in.lin.
'"
o.. ::2!
,-4
7
8
9
Special spring-brass strip (74.69% Cu) 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.095 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 /lm (10 /lin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the closest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercíal temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, half hard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 593 oC (1100 °P) for 1 h
~ üí
Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 62
Copper (Cu)/527
100
700
90
630
_1
80
i/
l¿V
60
V
/V
40
420
~
280
4
210 140
L
5
".
70
1(
2
3
4 6 5 Strain, 0.001 in.lin.
7
Cu.026 Cartridge brass (UNS C26000) thin-wall tu bes, von Mises true stress-strain curves
800 Campressian 700
rf.
Tarsian 600
rñ
Ul
,g;
500
Ul Q)
.sg¡
400
Axial tensian fallawing tarsian prestrain
Ul
~
g 300 200
100
00
Cií
70-30 cartridge brass (69.83% Cu) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.070 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 /lm (lO /lin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the closest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, half hard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 704 oC (1300 °F) for 1 h Saurce: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 62
9
8
900
::;;
'" ::;;
350 rñ
3
f-
f"
20
490
1-2
a.
bV
30
10
560
V
70
Cu.025 Cartridge brass (UNS C26000) strip, stressstrain curves showing effect of cold working
A
0.5
B
C
O
1.5 2 van Mises true strain
2.5
3
3.5
Results of path-change experiments on 70-30 brass. Curves (A) through (D) represent axial tension in thinwall tubes following torsional prestraining to von Mises strains indicated. A series of experiments were conducted by prestraining in torsion followed by uniaxial tension. All specimens were thin-wall tubes. Test sections were 25.4 mm (1 in.) long, 12.14 mm (0.48 in.) in diameter, and 0.589 mm (0.023 in.) in wall thickness. Specimens were carefully machined, annealed, and electropolished before twisting. After twisting, they were unloaded, reelectropolished, and strain gaged for tension testing. The resulting tensile curves are shown superimposed on the previous torsion and compression curves. The two curves at smaller prestrains showed little uniform elongation; most of the deformation occurred in a localized neck. Hence, these flow curves are questionable. The two curves for large prestrains definitely show that significant p1astic flow in tension following torsional prestraining takes much higher stresses than does continued torsion. In fact, the flow curves are very close to that observed for compression at the same von Mises strain level. Source: G. Krauss, Ed., Deformation, Processing, and Structure, papers presented at the ASM Materials Science Serninar, 23 Oct 1982 (St. Louis MO), American Society for Metals, 1984, p 12
528/Copper (Cu)
800
700 /
600 Uniaxial tensianjl
ro
D.. :2 500
ji
~
1ií 400 Q) (/)
~
c: o
"' ....
........
Thin-wall tubes, 25.4 mm (1.00 in.) long, 12.14 mm (0.48 in.) diameter, 0.589 mm (0.023 in.) wall thickness. Comparison of stress-strain curves for 70-30 brass for uniaxial tension, uniaxial compression, and torsion. Tension and torsion were carried out on identical thinwall tubes. Compression was carried out on solid rod, which was remachined often to avoid barreling.
Tarsian
-
Saurce: G. Krauss, Ed., Deformation, Processing, and Structure, papers presented at the ASM Materials Science Seminar, 23 Oct 1982 (St. Louis MOl, American Society for Metals, 1984, p 7
f
(/)
>
/
'" '"
'" '"
Cu.027 Cartridge brass (UNS C26000) thin-wall tubes, von Mises true stress-strain curves
Úni;i~ ~~p::i~n
.... ...
300
I
200
100
0.5
1.5
2
2.5
3
van Mises true strain
Cu.028 Cartridge brass (UNS C26000) thin-wall tubes, von Mises true stress-strain curves
600
500
f1.
:2 vi (/)
V
A
400
1ií
!!l
300
.¡"
~
~
~ 200
100
V .../V2
/~ ~
~
~~
Thin-wall tubes, 25.4 mm (1.00 in.) long, 12.14 mm (0.48 in.) diam, 0.589 mm (0.023 in.) wall thickness. Comparison of stress-strain curves for thin-wall 70-30 brass tubes. Curve 1: uniaxial hoop tension. Curve 2: the results for three different stress states-torsion, plane strain with no length change (Ez = O), and plane strain with no diameter change (100 = O). Curve 3: uniaxial tension. Curve 4: balanced biaxial tension
V3
7{
/'
Source: G. Krauss, Ed., Deformation, Processing, and Structure, papers presented at the ASM Materials Science Seminar, 23 Oct 1982 (St. Louis MOl, American Society for Metals, 1984, p 8
.1.
~
oO
~
0.05
0.1
0.15
0.2
0.25
0.3
van Mises true strain
0.35
0.4
0.45
0.5
Copper (Cu)/529
75
65
V
60
./ /"
v
55
/ "/
45 '00
"': 40 (J) (J)
~ 35
ro
30 25
fa
20
~V // ~ ' / /. ~ ~ p
---
--
2
455
3-
350 4 1-- 315
¡.--
10
J
5
ol/
o
rñ
245 ~ 210 5
175
105
W
70 35 1.5
0.5
2
2.5
3 3.5 4 Stmin, 0.001 in./in.
4.5
5
70
5.5
6
¡)....-
65 60
55 50
A~
45 '00
""_40 (J) (J)
/
~ 35
//
30
// /"
25
~~
20
.....-: -p 'l
525
Cu.030 High-brass (UNS C27000) strip, stress-strain curves showing effect of cold rolling
490 455
rñ
245 gJ 210 ii5
---
175 140 105
5
70
)r'
35
V 0.5
1.5
2
2.5
3 3.5 4 Slrain, 0.001 in./in.
ro
a..
280 :2
D'
o o
Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 72
315
4
4.5
5
5.5
6
Common high-brass (66.49% Cu) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.015 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 ¡lm (10 ¡lin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the c10sest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, halfhard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 371°C (700°F) for 1 h
o
V . / 420 . . . v . . . Jv'2' 385 V¿ ~ t-- I-J 350
IV U
15
5
ro
140
75
10
ro
a..
280 :2
). !7
15
420 385
P:V
50
490
V
~V
Cu.029 High-brass (UNS C27000) strip, stress-strain curves showing effect of cold rolling
525
1
70
o
Common high-brass (66.49% Cu) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.070 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 ¡lm (10 ¡lin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the c10sest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, half hard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 538 oC (1000 °F) for 1 h Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 72
530/Copper (Cu)
100 90
v
,/
80
; ~
70
/
60
~
/
~ 50
~
U5
IÍ.
40 30
L
20 10
J
If'
¿
630
~2
560
490
~
420
:::::::::!
~"
~
280
5
140
".
70
V
2345678 Strain, 0.001 in./in.
80
/
70 60
L
~ 50
/
9
10
40
,
/)
/
r
/'
V
--
~1
Cu.032 Muntz metal copper (UNS C28000) strip, stress-strain curves showing effect oi cold rolling
630
Muntz metal (60.50% Cu) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.045 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254!lm (10 !lin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the cIosest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, half hard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 538 oC (1000 °P) for 1 h
420
3
280 210 140
70
2
3
'"
:::; 350 ui
5
~
700
490
V
4
~/
Source: RA. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 82
560
_2
4 5 6 7 Strain, 0.001 in./in.
8
9
10
Muntz metal (60.50% Cu) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.015 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 !lm (lO !lin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the closest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve'!: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, half hard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 482 oC (900 °P) for 1 h
o
11
D..
¡J ~
~
U5
10
U5
210
90
20
lE
:::; 350 ui en
100
30
Cu.031 Muntz metal copper (UNS C28000) strip, stress-strain curves showing effect oi cold rolling
700 1
~ U5
Source: RA. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 82
Copper (Cu)/531
100 90
-
V
V
80
1 - 630
l-- 2
~~
560
/'
70
./ ~
60
490
¡....-- 3
420
~
# J, ~ ¡....---
¡:f 50 ~
éi5 40
~
30
rf
:2
350 rñ
i
4
(f)
280
V
210
5
1/ JV
20 10
Cu.033 High leaded brass (UNS C33200) strip, stress-strain curves showing effect of cold rolling
700
140 70
V
2
4
3
5
6
7
8
9
10
o
11
Source: RA. Wilkins and ES. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 100
Strain, 0.001 inJin.
100
630
80
,V /
70 60
~
¡:f 50 40
J~
30
lP
20
!
'/
l/
V
-1
¡....--
560 490
~2
420
l'
350 ¡:f
3
~
~
280
-
4
210 140
L
5
2
3
'"
IJ..
:2
/; ~ ~
~
éi5
10
Cu.034 High leaded brass (UNS C33200) strip, stress-strain curves showing effect of cold rolling
700
90
4
5
70 6
7
Strain, 0.001 inJin.
8
9
10
o
11
High leaded brass (65.19% Cu, 1.09% Pb, balance Zn) strip LO mm (0.040 in.) stock, having a ready-to-finish grain size of 0.015 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254/lm (lO /lin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the c10sest in composition current designation is given for reference. (C33200 is for tube.) The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, half hard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 427 oC (800 °P) for 1 h
éi5
High leaded brass (65.19% Cu, 1.09% Pb, balance Zn) strip LO mm (0.040 in.) stock, having a ready-to-finish grain size of 0.080 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254/lm (lO /lin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the c10sest CUfrent designation in composition is given for reference. C33200 is for tube. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, half hard. Curve 4: B&S, 1; RA, 11.0%; temper, quarterhard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 649 oC (1200 °P) for 1 h Source: RA. Wi1kins and ES. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 100
532/Copper (Cu)
100
Cu.035 High leaded brass (UNS C34200) strip, stress-strain curves showing effect oi cold rolling
700
___ 1 90 80
~~
70
~~ lAV ~v
60
gf 50 40
/~
30
10
~
I
~
20
630
V
~ ...
2
560 490
1-3 420
'"
280
5
ti
140
j'l
70
If
2
3
4
5
6 7 Strain, 0.001 in.lin.
80
V
70 ~
60
8
9
10
50
~ ¡-~ ./
vi
'"~
Cií 40
v- 1
-
630
Cu.036 High leaded brass (UNS C34200) strip, stress-strain curves showing effect oi cold rolling
560
High leaded brass (63.35% Cu, 2.79% Pb, balance Zn) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.080 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 ¡..tm (10 ¡..tin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the c10sest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, halfhard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard, Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 760 oC (1400 °P) for 1 h
420 350
vi
'"
4
210 140
J
5
3
4
g¡'"
280 (f) ~
~
2
Source: R.A. Wilkins and E.S. Bunn. Copper and Copper Base Alloys, McGraw-Hill, 1943, p 106
490
2
ItV
V
o
11
-3
I~
20 10
?
~
".,
V /Í
30
~
210
90
g¡
o.. '"
:2 350 vi
4
5
6 7 Strain, 0.001 in.lin.
70
8
9
10
High leaded brass (63.35% Cu, 2.79% Pb, balance Zn) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.015 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 ¡..tm (lO ¡..tin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the c10sest current designation is given for reference. The cold working . of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, halfhard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 427 oC (800 °P) for 1 h
o
11
Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 106
Copper (Cu)/533
90
V
80
V
70
V
~~
60
~ v~
]l 50
.......¡...--
3
~
¡¡¡ 40
J I!
Lancashire brass (73.53% Cu, 2.24% Pb, balance Zn) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.015 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 ¡.tm (10 ¡.tin.) were used. These tests were conducted in accordance with ASTM E 8. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, half hard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 427 oC (800°F) for 1 h
4
'"
350 ~
ui ti)
280
~
10
560
420
¡......-
/V
30
Cu.037 Lancashire brass strip, stress-strain curves showing effect of cold rolling
490
~ ~~
:i
20
./
2
630 1
~
(/)
210
5
140
2
4
3
5
7
6
70
Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 96
420
Cu.038 Deep-drilling copper (UNS C35330) rod, stress-strain curves showing effect of cold drawing
8
Strain, 0.001 in.lin.
60 55
50 45
/
40
JV/
._ 35
IP
g¡
:i 30
~ 25
I
15
5
/
V
/
385 350
V
¡.....-1--
315
2
280
V
245 ~ :;
3
210 ui ti)
/
~ 175 (/)
V/V
20
10
1
V /'
I
140
JíV f. . . .1--
105
4
70 35
V
2
3
4
5 6 7 Strain, 0.001 in.lin.
8
9
10
o
11
Deep-drilling copper (62.11 % Cu, 4.00% Pb, balance Zn) rod les s than 25.4 mm (1 in.) in diameter, previously extruded to a grain size of 0.050 mm. A 45,359 kg (100,000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 ¡.tm (10 ¡.tin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the closest current designation is given for reference. The cold working of each specimen was defined by the reduction in area: curve 1,32%; curve 2, 19.5%; curve 3, 10%; curve 4,32%, also annea1ed at 649 oC (1200 °F) for 1 h Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 122
534/Copper (Cu)
60 55
V / ..-//
50 45 40 ._ 35 ~
gf 30
~ 25
20 15 10 5
/ )' II If'
/
385 350
_2
315 280
1/
245 210 175
Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 124
105
35
'ji
3
789 Strain, 0.001 in./in.
4
5
6
10
/'"
90 80
/ 0 :::::=f.-V .....-
70 60
~
¡J / ¡)~
40
~
700
Cu.040 Pen-metal copper strip, stress-strain curves showing effect of cold rolling
630
Pen-metal copper (83.32% Cu, 1.32% Sn, balance Zn) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.015 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 ¡.tm (10 ¡.tin.) were used These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, this alloy is in the farnily of Cu-Zn-Sn tin brasses. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, halfhard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 538 oC (1000 °F) for 1 h
560
2
3
490
420
V
350
4
5
210
70
3
ui
~
(IJ
280
140
2
ro
Il..
:2
If
J I!
O
11
-1
¡.....-
10
(IJ
140
3
100
20
ui !J)
~
Standard brass (60.05% Cu, 2.12% Pb, balance Zn) forging rod less than 25.4 mm (1 in.) in diameter, previous1y extruded to a grain size of 0.010 mm. A 45,359 kg (100,000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 ¡.tm (10 ¡.tin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the closest current designation is given for reference. The cold working of each specimen was defined by the reduction in area: curve 1,17.5%; curve 2, 8.5%; curve 3, 17.5%, also annealed at 482 oC (900°F) for 1 h
70
2
30
ro
Il..
:2
¡--
!IJ 1$
Cu.039 Forging brass (UNS C37700) forged rod, stress-strain curves showing effect of cold drawing
420
~1
4 5 6 7 Strain, 0.001 in./in.
8
9
10
o
11
Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 143
Copper (Cu)/535
100 90
630
80
./
60
) .JJ
30
10
/J
560
1--
2
490 420
-3
350
280
~
~
210
W
140 5
70
IY
2
o..'"
:2
~
)
40
~/ >--
1
~
. . .V
/ VI-'" /(,
70
20
Cu.041 Pen-metal copper strip, stress-strain curves showing effect of cold rolling
700
3
4
5
7
6
8
Pen-metal copper (83.32% Cu, 1.32% Sn, balance Zn) strip 1.0 mm (0.040 in.) tmck, having a ready-to-finish grain size of 0.080 mm. A 2268 kg (5000 lb) capacity hydraulic testing macmne and Templin automatic extensometer accurate to 0.254 ~m (10 ~in.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, this alloy is in the family of Cu-Zn-Sn tin brasses. The cold working of each specímen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercíal temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, half hard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 704 oC (1300 °F) for 1 h Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 143
9
Strain, 0.001 in.lin.
90r---r---~--.----~--'---~---r---r--~---,630
Cu.042 Admiralty brass (arsenical) (UNS C44300) bar, stress-strain curves showing effect of low temperatures
80~--+--~+---+----~--~--~--~--~---+~~560
Bar in annealed condition_ Bar thickness: 19 mm (3/4 in.) 70 t---t-.-t---r---r---:;;j¡a¡.~ 't---+---t'--c..r 490
Source: R.P. Reed and R.P. Mikesell, Low Temperature Mechanical Properties of Copper and Selected Copper Alloys, NBS Monograph 101, Institute for Materials Research, National Bureau of Standards, 1967
60~--+--~+---~~~--~~~~~--~---+--+1420
.195K '" ~ 50 r---t---7f7L-b,.L..-r---t---t:::::;;;;;;j;-=-r~v----1350 ~
~
l
~5K
m~
~b
en
20~~~---+---+----}---~--~--~--~---+--~140
10U---+---+---+---+---4---~--~--~---+--~70
ooL---L----L---~--~--~---L---L---L---L--~O
0.1
0.2
0.3
0.4
0.5
0.6
Strain, in.lin.
0.7
0.8
0.9
1.0
536/Copper (Cu)
110
1
100
/
90
/~ V
80
V
60
#~
ui
~
in
)
40
20 10
/)
490 420
4
f--
rn
~
1ií
280 5
210
If
r
§¡"' ui
350
~I
30
560
v
50
700
630
'--2
~3
¡;V ...
70
g¡
Cu.043 Admiralty brass (antimonial) (UNS C44400) strip, stress-strain curves showing effect of cold rolling
770
140 70
2
3
4
5
6
7
8
9
Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 147
Strain, 0.001 in.lin.
100
90
",....-
80
/
70
/
¡i 50 ~
1ií 40
j,
30
10
#
-1
630 560
_2
V
490
1P?
420
~ J "..-
~
3
350 ui
4
280 210 140
5 70
2
3
"'
11.
:;¡;
j,'
V
Cu.044 Admiralty brass (antimonial) (UNS C44400) strip, stress-strain curves showing effect of cold rolling
700
,/
60
20
1/
-
4
5
6
7
Strain, 0.001 in.lin.
8
9
Admiralty brass (70.37% Cu, 1.01 % Sn, balance Zn) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.015 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 /-lm (10 /-lin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the closest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, halfhard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 427 oC (800°F) for 1 h
~
Admiralty brass (70.37% Cu, 1.01 % Sn, balance Zn) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.080 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 /J-ill (lO /-lin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the closest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, half hard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 649 oC (1200 °F) for 1 h Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 147
Copper (Cu)/537
120 110
/""
90
~
80 ~
gj 60
~
(f)
50 40
770
20 K_
100
._ 70
Cu.045 Naval brass (UNS C46400) bar, stress-strain curves showing effect of low temperatures
840
~
~-r;,
700
560
l----,... 76 K 'x
490 o.. '"
::¡;
.'\ ,\x
¡ //. ~
rv
Source: R.P. Reed and R.P. Mikesell, Low Temperature Mechanical Properties of Copper and Selected Copper Alloys, NBS Monograph 101, Institute for Materials Research, National Bureau of Standards, 1967
630
~
Ó ¡f V __ ~ ./
Bar in annealed condition. Bar thickness: 19 mm (3/4 in.)
)(
420 gf ~
350
ro
280
fF
30
210
20
140
10
70 0.1
0.2
0.3
0.5
0.4
Strain, in.lin.
110 100
./
90
V
~ ¡...--
80
--
~ ~ ~ ¡...-- 4 V
70
~ 60 vi
ID
¡7.) 50
j
40
30
I
20 10
Cu.046 Naval brass (UNS C46400) strip, stress-strain curves showing effect of cold rolling
770
I~
P"
1
700 630
2
560
¡....-- 3 490 420
rJi
350 ~
V
(f)
280
~"
210
5
¡..--
140
/
70
If
2
3
g¡'"
4
5
Strain,
6
7
0.001 in.lin.
8
Naval brass (61.51 % Cu, 0.57% Sn, balance Zn) strip 1 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.015 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 ¡.tm (10 ¡.tin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the closest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reductÍon in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, halfhard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 482 oC (900°F) for 1 h Source: R.A. Wi1kins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 155
538/Copper (Cu)
100 90
/' ___ 2
/ V 1--
70
g. ~ /1 ".......
60
30 20 10
630
/1
80
40
Cu.047 Naval brass (UNS C46400) strip, stress-strain curves showing effect of cold rolling
700
4
560 490
3
420 4
~
In
~
(/)
¡;f JI/ JJV
280 210 5
140 70
1{
3
2
ca
Cl..
:2 350 cñ
4
5
7
6
8
9
10
Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 155
O 11
Strain, 0.001 in.lin.
140
120 110 100
--
,,---
130
/"
/~ ~
r-
....---
90 .¡¡;
80
""~
70
~ (/) 60
50
r--.....
910
~
840 770
'T \
700 630 560 ~
:1<
"
:2
490
"'\
350
i
280
30
210
20
140
10
70 0.1
0.2
~
420 iií
295K\ \
40
Copper alloy No. 510 cold drawn 85%. Bar thickness: 19 mm (3/4 in.)
4K
\ 76 K
r-....195 K
Cu.048 Phosphor bronze (UNS C51000) 5% grade A bar, stress-strain curves showing effect of low temperatures
980 20 K
0.3 Strain, in.lin.
0.4
0.5
0.61
Naval brass (61.51 % Cu, 0.57% Sn, balance Zn) strip 1 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.080 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extenso meter accurate to 0.254 ¡..tm (10 ¡..tin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the closest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, half hard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 649 oC (1200 °F) for 1 h
Source: R.P. Reed and R.P. Mikesell, Low Temperature Mechanical Properties of Copper and Selected Copper Alloys, NBS Monograph 101, Institute for Materia1s Research, Nationa1 Bureau of Standards, 1967
Copper (Cu)/539
100
V /'
90
h ~/
60
~
,
50
¡¡;;....-
490
~3
420
1--4
350 ui In 280
A
30 20
j
5
140 70
V
234 5 678 Strain, 0.001 in./in.
O
9
10
O
11
100
80
// V~ ."....-
70 60
/ jV
50
en 40 30 20 10
, I
h~
¡..--
V
./"
-
--
Cu.050 Phosphor bronze (U NS C51000) 5 % grade A strip, stress-strain curves showing effect oí cold rolling
630 ~1
560 490
2
420
:2
350 ui In 280
4
210
1;1
)/'
III
a..
3
140 5
70 2345678 Strain, 0.001 in./in.
9
10
O
11
5% grade A phosphor bronze (4.09% Sn, 0.035% P, balance Cu) 1.0 mm (0.040 in.) thick, having a ready-tofinish grain size of 0.015 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254/lm (lO /lin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the closest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, halfhard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 538 oC (1000 °F) for 1 h Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 269
700
90
¡i
~
210
1/
o
~
III
a..
:2
JÍv
40
10
560
/~V
70
¡i
630
1/,...,-1-- 2
80
Cu.049 Phosphor bronze (UNS C51000) 5% grade A strip, stress-strain curves showing effect oí cold rolling
700
1
~
5% grade A phosphor bronze (4.09% Sn, 0.035% P, balance Cu) 1.0 mm (0.040 in.) thick, having a ready-tofinish grain size of 0.070 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254/lm (10 /lin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the closest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, halfhard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 760 oC (1400 °F) for 1 h Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 269
540/Copper (Cu)
140 , - - - , - - - - - - - - , - - - , - - - - - ¡ - - - - , - - - - - , 980 1301-----+----=
Cu.051 Aluminum bronze D (UNS C61400) bar, stress-strain curves showing effect of low temperatures
!'--------I 910
-------1840
Bar in annealed condition. Bar thickness: 19 mm (3/4 in.)
11 O f---,#J'K-_+_--?~_t---+--_==__:_:_-+---+_--__l 770
Source: R.P. Reed and R.P. Mikesell, Low Temperature Mechanical Properties of Copper and Selected Copper Alloys, NBS Monograph 101, Institute for Materials Research, National Bureau of Standards, 1967
50~--_+_--~---+__--_+---+_--~350 40~---+---~---1_--_+---+_--~280
30~---+---~---1----+---+_--~210 20~--_+_--~---+__--_+---+_--__l140 10~--_+_--_t---+__--_+---+_--__l70
0.1
0.3
0.2
0.4
O.¡jl
0.5
Strain, in./in.
65
Cu.052 Aluminum bronze (UNS C63000) extruded rod, stress-strain curves showing effect of cold working and annealing
455 1
60
......... ~ F-
55 50
I~
45
420
3
385
V
350 315
/¡V
40 '00
"" 35 (Ji
I!
en
~ 30
~
(/)
25 20 15 10
I
5
oV O
280
~ ./"
!J / // l'
V
ro
c..
-
245 ::;: 2
210 ~
ro
175 140 105 70 35
2
3
4
5 6 7 Strain, 0.001 in./in.
8
9
10
O
11
10% aluminum bronze (88.83% Cu, 10.02% Al, 0.77% Fe, 0.31 % Mn) previously extruded rod. Applicable to rod less than 25.4 mm (1.00 in.) diameter. A 45,350 kg (100,000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 !lm (10 !lin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the c10sest current designation is given for reference. The cold working of each specimen was defined by the reduction in area: curve 1,5%; curve 2, 0% as extruded 25.4 mm (l in.) diam; curve 3, 5%, also annealed at 260 oC (500°F) for 1 h Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 262
Copper (Cu)/541
100
700
90
630
80
v
70
/
60
40
/
30
J
560 490 420
350 ui 280
e?'" ro
210
~
V
ctl
a.
:2
70
7 4 5 6 Strain, 0.001 in.lin.
3
2
~
....--""
~
~
1\
\
\ \ \
100
\
90
\
.¡¡; 80
9
10
o
11
980
Cu.054 Copper-nickel-silicon (UNS C64700) bar, stress-strain curves showing effect of low temperatures
910 840
Bar thickness: 19 mm (3/4 in.). Aged at 450 oC (842°F) for 2 h. This alloy was the strongest tested in this series of low-temperature tests.
20 K 770
~
700 630
*~
-"
8
b6K
295 K\
t
560
:l
&
:2
li
70
490
li
C/J
60
420
ro
50
350
~
Silicon aluminum bronze (7.01 % Al, 1.98% Si, balance Cu) previously extruded rod. Applicable to rod less than 25.4 mm (1 in.) in diameter. A 45,359 kg (100,000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 ¡.tm (10 ¡.tin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the closest current designation is given for reference. The cold working of each specimen was defined by the reduction in area: curve 1, 10.5%; curve 2, 8%; curve 3, 10.5%, also annealed at 649 oC (1200 °F) for 1 h Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 265
140
130
110
V- ~2 "..-
V-
140
120
1
3
Jv
20 10
~
v'~V V..
v
v- r-,,/'"
Cu.053 Silicon aluminum bronze (UNS C6421O) rod, stress-strain curves showing effect of cold working and annealing
1\195K
~
40
280
30
210
20
140
10
70 0.1
0.2
0.3 Strain, in.lin.
0.4
0.5
0.!P
Source: R.P. Reed and R.P. Mikesell, Low Temperature Mechanical Properties of Copper and Selected Copper Alloys, NBS Monograph 101, Institute for Materials Research, National Bureau of Standards, 1967
542/Copper (Cu)
90 80
~
70
/~.--h ~V ¡...--Y ~ /'
60
g¡
50
~
iñ 40 30 20 10
~
~~
560
Type B silicon bronze rod less than 25.4 mm (l in.) diameter, (1.76% Si, 0.35% Mn, balance Cu) having a ready-to-finish grain size ofO.115 mm. A 45,359 kg (100,000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 ¡.Lm (10 ¡.Lin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the c10sest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, half hard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 649 OC (1200 °P) for 1 h
3
420
4
350 ~
ro
280
~
(f)
210
) I ~~
Cu.055 low-silicon bronze type B (UNS C651 00) rod, sfress-strain curves showing effect of cold drawing
490
¡f~
1(
630
140
-
5
3
2
4
5
6
7
8
9
70
10
o
11
Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 248
Strain, 0.001 in./in.
110 100 90 80 ._ 70 g¡
~ 60 ~
iñ
50 40 30
Cu.056 High-silicon bronze A (UNS C65500) bar, stress-strain curves showing effect of low temperatures
840
120
¿
700
~f7sK ¿ /,~/ V- I19sK /1 V/ ~ ~
-
f//V V/
560
l
490
:\ \\
420
(f)
\l
280
140
10
70 0.3
0.4 0.5 0.6 Strain, in./in.
0.7
i 350
210
0.2
ro
o.
2:
20
0.1
Specimen in annealed condition. Bar thickness: 19 mm (3/4 in.)
630
/V
/"
770
~ ')(
0.8
0.9
o
1.0
Source: R.P. Reed and R.P. Mikesell, Low Temperature Mechanical Properties of Copper and Selected Copper Alloys, NBS Monograph 101, Institute for MateriaIs Research, Nationa1 Bureau of Standards, 1967
Copper (Cu)/543
Cu.057 Copper-nickel1 0% (UNS C70600) bar, stress-strain curves showing effect of low temperatures
100~----,,-----,------,-----~------,------,700
90~----~----~------4------4------+-----~630
20 K
Specimen in annealed condition. Bar thickness: 19 mm (3/4 in.)
60~----~~~~~----4------4-----++_----~420
~
g
~
50 r---~~IL--::;:;:;....,,==:::=:=;;t------'lrl-------r------j 350
ro
~
Source: R.P. Reed and R.P. Mikesell, Low Temperature Mechanical Properties of Copper and Selected Copper Alloys, NBS Monograph 101, Institnte for Materials Research, National Bureau of Standards, 1967
~
(J)
40~~~~----~~----4-~~-4------+_----~280
30~~--~-------~----4----1~------+------1210
2o------~-------~----~-----4------+_----~140
10~----~-------~----~----_4------+_----~70
°OL------OL.1------0.L2-----~0.-3-----0~.4------0~.5----~0.~ Slrain, inJin.
90 1
80
V 2 i-?""': ~3
70
/
60
~
~ 50
iñ 40 30 20 10
560
80-20 copper-nickel (78_18% Cu, 20.65% Ni, O_51 % Mn) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.015 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 ¡..Lm (10 ¡..Lin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the closest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, halfhard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 649 OC (1200 °P) for 1 h.
420 ro
350 ~
4
¡.--
280 (J) ~'" 210
/f
5
140
/1
If
Cu.058 Copper-nickeI20% (UNS C71000) strip, stress-strain curves showing effect of cold rolling
490
W v
I/ V ti /'
'"~
lo-
630
70
2
3
4
5
Slrain, 0.001 inJin.
6
7
8
Source: R.A. Wilkins and E.S. BUI1Il, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 237
544/Copper (Cu)
80
..?-
70
10
2
490 3
420 (\l
350 ~
/V
40
20
1 - 560
~V
Vi
30
-
VíV-
~ 50
~
~
V
60
ro
Cu.059 Copper-nickeI20% (UNS C71000) strip, stress-strain curves showing effect of cold rolling
630
90
¡jI ~ '( 1/
,
Vi IJ)
--
280 U) ~ 4
210 140 5
ff
70
2
3
4
5
6
7
8
9
o
Strain, 0.001 in.lin.
110 ¡ - - - - - - , - - - - , - - - , - - - - , - - - , - - - - - - , 770
..,..
100 I--¡---I-~:::I
,--l'\c----! 700
90r---i-----t~~~---~~~=t~----_¡630 80~--4--_7.~-~~+_--_+---~--~560
70~--~~_7~---+_--_+---r+--~490
40~-~~~-~---+_--_+-~~r_--~280 30~~-4---~---+----+---r---~210
20~--~--~---+_--_+---t_--~140 10~--4---~---+----+---r---~70
°0L---~0.-1---0~.-2---0~.3---0~.4---0L.5--~0.~
Strain, in.lin.
80-20 copper-nickel (78.18% Cu, 20.65% Ni, 0.51 % Mn) strip 1 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.055 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 ¡.tm (10 ¡.tin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the closest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a cornmercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, halfhard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 871 oC (1600 °P) for 1 h Source: RA. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 237
Cu.060 Copper-nickel 30% (UNS C71500) bar, stress-strain curves showing effect of low temperatures
Specimen in annealed condition. Bar thickness: 19 mm (3/4 in.) Source: R.P. Reed and R.P. Mikesell, Low Temperature Mechanical Properties of Copper and Selected Copper Alloys, NBS Monograph 101, Institute for Materia1s Research, National Bureau of Standards, 1967
Copper (Cu)/545
90 ./
80
60
J
Ií'
gf 50
ip
~
40 30
10
V W /
70
20
j
~
f"'~
",..-
630
1
i--- 2
560
/ - --3
490 420 4
280
J 1(1
5
140
I
70
V
2
5 6 Strain, 0.001 in.lin. 4
3
8
7
Cu.062 Copper-nickel 30% (UNS C71500) rod, stress-strain curves showing effect of cold drawing
630 2
1VV ¡....¡...-' ¡....-¡...--
y V ~ .-'"
70 60
gf 50 40 30
j
1/
~
~
V ~~
¡....-
~ 3
0.5
490
280 210 4
140 70 1.5
2
2.5 3 3.5 4 Strain, 0.001 in.lin.
&.
:::¡¡
350 ui
¡Jw
1/1
560
420
~
4.5
5
5.5
70-30 copper-nickel (68.94% Cu, 29.61 % Ni) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.015 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 /..lm (10 /..lin.) were used These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the c10sest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, half hard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 704 oC (1300 °P) for 1 h Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 230
9
700
80
10
~
210
90
20
&.
:::¡¡
350 ui
100
~
Cu.061 Copper-nickel 30% (UNS C71500) strip, stress-strain curves showing effect of cold rolling
700
100
~
70-30 copper-nicke1 (68.56% Cu, 30.48% Ni, 0.39% Pe, 0.57% Mn) rod, having a ready-to-finish grain size of 0.035 mm. A 45,359 kg (100,000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 /..lm (lO /..lin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the c10sest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, half hard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 704 oC (1300 °P) for 1 h Source: R.A. Wi1kins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 233
546/Copper (Cu)
100
700
90
630 1
80
h
70
/ ~
60
JVI lAVV XIf r
gf 50 ~
ro
40 30 20 10
V
p-
560
2
490
3
"...-
Cu.063 Copper-nickel 30% (UNS C71500) strip, stress-strain curves showing effect of cold rolling
420
&.
:2
350 ~
UJ
~
ro 280
4
210
h
140
I!-
5
70
If
2
3
4
5
7
6
8
Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 230
9
Strain, 0.001 in./in.
110
¡.....-- f----
/'" _
90 80
V
70
g¡
60
gf ID
c7.¡ 50
j
40
?,...I¿ rr
1
2
560
3
490
V
'"
420 ~
4
¡--
UJ
350 280
5
210
II!
20
140
Jr/
I
700 630
~V
~~
30
10
Cu.064 Nickel silver (UNS C74400) strip, stressstrain curves showing effect of cold rolling
770
100
70 2
3
4
5
6
7
Strain, 0.001 in./in.
8
9
70-30 copper-mckel (68.94% Cu, 29.61 % Ni) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.070 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 f..lm (10 f..lin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the closest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, half hard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annea1ed at 871°C (1600 °F) for 1 h
10
ro~
5% nickel silver (63.55% Cu, 5.14% Ni, balance Zn) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of O. O15 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 f..lm (10 f..lin.) were These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the closest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, halfhard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 482°C (900°F) for 1 h Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 220
Copper (Cu)/547
110
770
100
700
90
V
80 70
g¡
/'
60
~
¡:f Q)
$
40
10
490
420
g¡
350 ~ 280
4
210
Jrt/
/J¡ v
If
560
¡..--- 2
¡:f
d [t-
30
630
3
lúv
50
20
~
1
¡.--
Cu.065 Nickel silver (UNS C74400) strip, stressstrain curves showing effect of cold rolling
140
5
70 2
4
3
5
6
7
8
Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-HilI, 1943, p 220
10
9
Strain, 0.001 in./in.
110 100
¿
90 80 70
g¡
J
60
Q)
50
.¡..-- 3 560 490
420
4
I
280
5
140
J
70 2
3
4 5 6 7 Strain, 0.001 in./in.
g¡
350
210
lfI-
20
700 630
¡j"
30
1
2
+-
I!I
40
10
l~
V l-V
V
J f/ ~-
'" $
Cu.066 Nickel silver (UNS C74500) strip, stressstrain curves showing effect of cold rolling
770
¡.......-1--
8
5% nickel silver (63.55% Cu, 5.14% Ni, balance Zn) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.110 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 ¡..tm (lO ¡..tin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the closest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, halfhard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 760 oC (1400 °P) for 1 h
~
Uí
10% nickel silver (66.02% Cu, 10.73% Ni, balance zinc) strip, having a ready-to-finish grain size of 0.015 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 ¡..tm (10 ¡..tin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the closest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, half hard. Curve 4: B&S, 1; RA, 11.0%; temper, quarterhard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 593 oC (1100 °P) for 1 h Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-HilI, 1943, p 215
548/Copper (Cu)
110
770
100
700 ....-= 1
90 80
¿,
70
g¡ ¡\5 50
/
./
-
~
420 ~
3
,,;
'"
350 ~
1/
40
#
30 20 10
490 ro
v
,,;
560 2
¡..-
/
gj 60
630
V
/
9
m
280
4
V
210
If
140
5
Ir
70
1/
2345678 Slrain, 0.001 in./in.
9
10
110
90
~
80
/
70
/
gj 60
/ I
,,;
g¡ ¡\5 50
11 30 20 10
¡...--
v
McGraw-Hill, 1943, p 215
Cu.068 Nickel silver 65-18 (UNS C75200) strip, stress-strain curves showing effect of cold rolling
.~
700
1
2
630
~t-
V
560
)/
490
V
ro
/"
f.--
420 ~
4
,,;
350 ~'" m
hfJ/ V /
280
/l / W/1
210
5
140 70
V
2
3
4
5
6
7
Slrain, 0.001 in./in.
8
9
10
1P
10% nickel silver (66.02% Cu, 10.73% Ni, balance zinc) strip, having a ready-to-finish grain size of 0.080 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 ¡..tm (10 ¡..tin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the c10sest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, half hard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 704 oC (1300 °F) for 1 h Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys,
1P
770
100
40
Cu.067 Nickel silver (UNS C74500) strip, stressstrain curves showing effect of cold rolling
18% deep-drawing nickel silver (66.00% Cu, 18.00% Ni, balance Zn) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.015 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 ¡..tm (10 ¡..tin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the c10sest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, halfhard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 593 oC (1100 °F) for 1 h Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys,
McGraw-Hill, 1943, p 200
Copper (Cu)/549
Cu.069 Nickel silver (UNS C75400) strip, stressstrain curves showing effect of cold rolling
770
110
/? -
100
700
_1
90
630
1--2
80 70
lb v
~ 60
'"
-
420 ~
4
li
/'
ID
~ 50
40
350 ~ 280
/)
30
10
490
V
J v f/V
li
20
~
560
__ 3
5
If 1-""
I v /V
IV
....-
210 140 70
3
2
~.......
~
4
5
6
7
8
9
Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys,
10
McGraw-Hill, 1943, p 208
Strain, 0.001 in./in.
110
770
100
700
90
630
V -b
¡..-- 1
80 70
JV
li ID
~ 50
20 10
350 ~ 280 4
¡..-
210
// / ' L-2
ui 1/) (/)
í. '1"
IV
'"
420 ~
3
)1 /l
40 30
490
V
~ 60
Cu.070 Nickel silver (UNS C75400) strip, stressstrain curves showing effect of cold rolling
560
-2
--
3
140 5
70
4
5
6
7
Strain, 0.001 in./in.
8
9
10
15% nickel silver (66.18% Cu, 15.05% Ni, balance Zn) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.015 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 !lm (10 !lin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the closest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, half hard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 593 oC (1100 °F) for 1 h
1P
15% nickel silver (66.18% Cu, 15.05% Ni, balance Zn) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.100 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 !lm (10 !lin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the closest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, half hard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 760 oC (1400 °F) for 1 h Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys,
McGraw-HiII, 1943, p 208
550/Copper (Cu)
100 90
630
/'
80
)~
gf 50
~
40
350 Ul cñ
I"
140
5
70
If
2
3
4 5 6 Strain, 0.001 in./in.
v
100
VV
90
7
¡....--
8
700 ~2
630 560
~V
70
V /'"
60
cñ Ul
())
40 30 20
~~
,t §
!l ~ ....-
490
_3
ro
420 ~ 4
cñ
Ul
350 ~
V
en
280 210 5
140
'/
I
Cu.072 Nickel silver 55-18 (UNS C77000) strip, stress-strain curves showing effect of cold rolling
770
1
70 2345678 Strain, 0.001 in./in.
9
10
12% nickel silver (66.24% Cu, 11.57% Ni, balance Zn) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.080 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 ¡.tm (10 ¡.tin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the closest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, half hard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 760 oC (1400 0F) for 1 h Source: R.A. Wi1kins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 212
9
1/V
80
50
~
210
110
10
4
280
if
20
¡¡¡
420 ro a.
jJ/
30
g¡
3
:2:
g,V
~
en
560 490
j V
60
1
¡....--
¡...-- 2
~/
70
10
Cu.071 Nickel silver 65-12 (UNS C75700) strip, stress-strain curves showing effect of cold rolling
700
1P
18% spring-stock nickel silver (56.56% Cu, 17.77% Ni, balance Zn) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.080 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 ¡.tm (10 ¡.tin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the closest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, half hard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 760 oC (1400 °F) for 1 h Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-HilI, 1943, p 203
Copper (Cu)/551
1.---
90
630
/.. .--2
560
V
/ v V / ..,/"
70 60
~ 50
420
40
280
~
J
I V
210
1/
140 70
2
3
4 5 6 Strain, 0.001 in.lin.
8
7
Cu.074 Leaded nickel silver (UNS C79000) strip, stress-strain curves showing effect of cold working
700
90
630 -1
~
80
/
70
J
60
~ 50 ~ (J)
~
/
40
20
)
I
490
2
¡--
420 350
!
v;:V- -----
3
./"'"
4
V
5
280 210 140 70
2
3
ro
a.
:2
V
j
30
V
560
V
4
5
6
Strain, 0.001 in.lin.
7
8
9
Leaded 12% nickel silver (65.49% Cu, 12.11% Ni, 1.96% Pb, balance Zn), strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.015 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 Jlm (10 Jlin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the c10sest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60 .. 5; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, half hard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 538 oC (1000 °F) for 1 h Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 225
9
100
10
~
5
~
30
ro
a.
:2 350 Ulrñ
4
I~ v
~
490
¡..-- 3
J.{/
1i5
10
1
/"
80
20
Cu.073 Leaded nickel silver (UNS C79000) strip, stress-strain curves showing effect of cold working
700
100
rñ
~
Leaded 12% nickel silver (65.49% Cu, 12.11 % Ni, 1.96% Pb, balance Zn) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.060 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 Jlm (10 Jlin.) were used. These tests were conducted in accordance with ASTM E 8. The tests predate the UNS designations, but the c10sest current designation is given for reference. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, halfhard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 816 oC (1500 °F) for 1 h Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 225
552/Copper (Cu)
110 100
'/
80 70
I~
60
'"al
¡7J 50
490 ca
420
5
2
3
5
4
7
6
8
90
¿
80
h
70
--
j;7
~
á
60
~V
¡7J 50
/
40
10
Silicon brass No. 1 (77.74% Cu, 1.30% Si, balance Zn) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.090 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 ¡..tm (lO ¡..tin.) were used These tests were conducted in accordance with ASTM E 8. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, half hard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 704 oC (1300 °F) for 1 h
70
Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 181
770
Cu.076 Silicon brass No. 2 strip, stress-strain curves showing effect of cold rolling
9
Strain, 0.001 in./in.
100
20
~
140
M
30
li éií
210
110
g¡ lial
g¡
280 4
~
"
560
350
11/v
30
2
3
v ~ /. ~
40
10
-
Rv
cñ
20
v
630
..- :..--
~/
1 - 700
r-
V /"
90
g¡
Cu.075 Silicon brass No. 1 strip, stress-strain curves showing effect of cold rolling
770
/)
t/
~
~
V ...-
1--
--
V
1 - 700
2 - 630
560 3
490 ca
420
g¡
350
~
cñ
4
280 210 5
140
JV'
70
1/
2
3
4
5
6
7
Strain, 0.001 in./in.
8
9
10
Silicon brass No. 2 (72.36% Cu, 0.47% Si, balance Zn) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.015 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.254 ¡..tm (lO ¡..tin.) were used. These tests were conducted in accordance with ASTM E 8. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, halfhard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 538 oC (1000 °F) for 1 h Source: RA. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 185
Copper (Cu)/553
110
770
100
700
90 80
rñ
e¡III
h J~
50
40
---
4
/¿,¡...-
30
h
20 10
3
/: t?"
gj 60
630 560
2
490 ca
420
¡:f 280 210 140 5
70
2
3
4 5 6 7 Strain, 0.001 inJin.
2000~----4_~~_+~--~------+_----~----~
1500
:2
¡:f
46.5 vol% fiber
~
Ci.í
1000r---~~--~~----~------+_----~----~
500r-r+~-4_----_+----~------+_----~----~
11.9 vol% fiber __~---~----T-~-¡ Copper 0.4
0.8
Source: R.A. Wilkins and E.S. Bunn, Copper and Copper Base Alloys, McGraw-Hill, 1943, p 185
1.2 1.6 Strain, % elongation
Cu.078 Tungsten copper composite wires, comparison of stress-strain curves Experimental composites with tungsten wires in a copper matrix at the volume percentage shown. Source: R.W.K. Honeycombe, The Plastic Deformation of Metals, 2nd ed., American Society for Metals, 1984, p 260 (After D.L. McDanels, R.W. Jech, and J.w. Weeton, Metal Progress, Vol 78, Dec 1960, p 118)
"
Tungsten wire
ca
Silicon brass No. 2 (72.36% Cu, 0.47% Si, balance Zn) strip 1.0 mm (0.040 in.) thick, having a ready-to-finish grain size of 0.080 mm. A 2268 kg (5000 lb) capacity hydraulic testing machine and Templin automatic extensometer accurate to 0.2541lm (10 Ilin.) were used. These tests were conducted in accordance with ASTM E 8. The cold working of each specimen was defined by the change in strip thickness based on the Brown and Sharpe (B&S) wire gage and the reduction in area (RA) and was then assigned a commercial temper designation. Curve 1: B&S, 8; RA, 60.5%; temper, spring. Curve 2: B&S, 4; RA, 37.2%; temper, hard. Curve 3: B&S, 2; RA, 20.7%; temper, halfhard. Curve 4: B&S, 1; RA, 11.0%; temper, quarter hard. Curve 5: B&S, 6; RA, 50.0%; temper, extra hard; annealed at 649 oC (1200 °F) for 1 h
8
2500,-----,------,-----,------,------,-----,
a.
g¡
350 ~
~
t~
r
V
V A
70
v
V ¡...--
_1
Cu.077 Silicon brass No. 2 strip, stress-strain curves showing effect of cold rolling
2.0
2.4
554/Copper (Cu)
140
980
130
910
4~
110 20 K 100 90 .¡¡; 80
"'g" 70 ~
iií
60
50
fI"<
..,/'~ Ix
120
h W/
;tV
/76 K 19:JS-
840
---- -
V __
--X
/'" /".-- 1---295 K
U
V/" I/~ V
700 630 560 ~ ::;;; 490 g ~
350
40
280
30
210 140 70 0.04
As cast. Brittle at low temperature. Composition: 9.95% Al, 5.20% Ni, 3.35% Fe, 0.3% Mn, balance Cu
770
420 iií
V
0.02
Cu.079 Copper-nickel-aluminum sand cast billet, stress-strain curves showing effect of low temperatures
0.06 Strain, inJin.
0.08
0.10
0.11>
Source: R.P. Reed and R.P. Mikesell, Low Temperature Mechanical Properties of Copper and Selected Copper Alloys, NBS Monograph 101, Institute for Materia1s Research, National Bureau of Standards, 1967
Magnesium (Mg)/555
Magnesium (Mg) Mg.OOl Magnesium single crystal, stress-strain curves
600r-------,------.------.------,-------r-----~
Arrows indicate yield strengths_ Relationship between specimen and slip plane orientation is shown_
Ao' area normal to tensile direction
500
I
Source: c'R. Brooks, Heat Treatment, Structure, and Properties of Nonferrous Alloys, American Society for Metals, 1982, p 6 (as published in E,C, Burk and W R. Hibbard, Trans AlME, Vol 194, 1952, p 295)
Normal to slip plane
N
E 400 E
Resolved area = Aa/cos <1>
Eel
Slip direction, resolved force =FcosA
I
u) (/)
~
Resolved shear stress =: cOSAcos
-¡¡;
§ o z
F
200 A = 58' <1>
= 31'
100
00
100
200
300
400
500
600
Shear strain, 10-6
35
25
""
I
r
20
~
Ci5 15
/
I
LV
Source: ASM Specialty Handbook, Magnesium and Magnesium Alloys, ASM International, 1999, p 166 175
Compression
140
I
~
:2
gf ~
105 Ci5
/
70
35
0,2
Composition: Mg-3AI-IZn_ UNS MI 1311
210
V
10
5
~nsion i--
/
30
'iñ
Mg.002 AZ31 B-F magnesium alloy extrusion, tensile and compressive stress-strain curves
245
0,6
0.4 Strain, %
0,8
o
1,0
556/Magnesium (Mg)
50
o
14
Compressive tangent modulus, GPa 28 42 56
Mg.003 AZ31 B-H24 magnesium alloy sheet, tensile and compressive stress-strain and compressive tangent modulus curves
70
Typical room-temperature values. Ramberg-Osgood parameter: n(tension) = 4.3; n(compression) = 15. Composition: Mg-3AI-IZn. UNS M11311
280
40
Source: MIL-HDBK-5H, Dec 1998, p 4-14 /¡enSiOn
~
·00 -'"
ui en ~
¡¡:¡ 20
10
25
20
15 ·00
I
7
14
ui en
140
\
10 8 6 Strain, 0.001 in.lin. Compressive tangent modulus, 106 psi
4
Compressive tangent modulus, GPa 28 42 56
/ /
'---~ 1/
--
o
12
Mg.004 AZ31 B-O magnesium alloy sheet and plate, tensile and compressive stress-strain and compressive tangent modulus curves
.--T,Tenslon T
-Compression
1\
Source: MIL-HDBK-5H, Dec 1998, p 4-11 105
ui en
35
10 8 6 Strain, 0.001 in.lin. Compressive tangent modulus, 106 psi
4
ro
11.
:2
70
2
Typical room-temperature values. Ramberg-Osgood parameter: n(longitudinal, tension) = 12, n(longitudinal, compression) = 30. Composition: Mg-3AI-IZn. UNS MI1311
140
/
/
~
70
/
~
ro
11.
:2
70
2
o
ui en
5
~~mpreSSion
J
-'"
10
210
< V
30
o
12
~ en
Magnesium (Mg)/557
Mg.005 AZ61A magnesium alloy extrusion, low- and high-temperature effects on tensile properties
Temperature, oc
-129 -18 93 204 316 427 5or-------,--------,--------r-------,---------,35o
F tu' ultimate tensile strength; F ty ' tensile yield strength.
Composition: Mg-6AI-IZn. UNS M1l61O Data from tbree sources: circle, Mg-43, AlZoy Digest, Aug 1959; triangle, Properties and Selection of Metals, Vo11, 8th ed., Metals Handbook, American Society for Metals, 1961; square, C.R. Tipton, Reactor Handbook, Vol 1, 2nd ed., Interscience Publishing, 1960. As pub1ished in Aerospace Structural Metals Handbook, Vol 3, Code 3603, CINDAS/ USAF CROA Handbooks Operation, Purdue University, 1995, p 3
40~------~------~~._----~------_r------~280
210
30 'iij
:2 ui en
en
~
~
140
20
10~------4--------4-------~~--~~+--------470
OL-------L-------~-------~-------L------~O ~
'"
Q.
-"" ui
80r-------,---------,---------r-------,---------,
E E
.~ 40 ~------+_-------+--___.......~I"__------+_------__l
'".S e
o
15el e
o
W ~2LO-0------~0--------2-0-0-------4~OLO-------6~0-0-------1800 lemperature, °F
Cií
558/Magnesium (Mg)
40
//v
30
/
10
Mg.006 AZ61 A magnesium alloy extrusion, tensile stress-strain curve
280
Composition: Mg-6AI-IZn. UNS M11610
~
210
V
ro
a. ~
140 ui
V
I/l
~
éií
J
1/
Source: "Magnesium Design," Dow ChemicaI Co., 1957. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3603, CINDAS/ USAF CRDA Handbooks Operation, Purdue University, 1995, p 3
70
2
4
6 8 Slrain, 0.001 in.lin.
10
30
210
25
175
Mg.007 AZ61 A magnesium alloy extrusion, compressive stress-strain curve
Composition: Mg-6AI-IZn. UNS M11610
/ 20
/
.¡¡;
'"ui I/l
~
15
éií 10
5
o
/
O
/
I
140
;/
ro
a. ~
105 ui
V I
I/l
~
éií 70
35
2
Source: "Magnesium Design," Dow ChemicaI Co., 1957. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3603, CINDAS/ USAF CRDA Handbooks Operation, Purdue University, 1995, p 4
/
4 Slrain, 0.001 in.lin.
6
Magnesium (Mg)/559
Mg.008 AZ61 A magnesium alloy forging, tensile stress-strain curve
280
40
Composition: Mg-6AI-IZn. UNS M11610
r V/ /
30
/
v
8?
::¡;
//
10
/
Source: "Magnesium Design," Dow Chemical Co., 1957. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3603, CINDASI USAF CRDA Handbooks Operation, Purdue University, 1995, p 3
210
140
V
~
70
Vi
4
2
6
8
10
Strain, 0.001 in./in.
30
Mg.009 AZ61 A magnesium alloy forging, compressive stress-strain curve
210
1/
25
/
Composition: Mg-6AI-IZn. UNS M11610 175
Source: "Magnesium Design," Dow Chemical Co., 1957. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3603, CINDASI USAF CROA Handbooks Operation, Purdue University, 1995, p 4
/ 20 .¡¡; -"
'"~
1i5 10
5
/
/
I
/ / / / fj-li
140
'"
Q.
::¡;
105
'"~
1i5 70
35
2
4 6 Strain, 0.001 in./in.
8
0 10
560/Magnesium (Mg)
Mg.Ol0 AZ63A-F, AZ63A-T4 magnesium alloy sand cast bar, tensile stress-strain curves at room and elevated temperatures
25,-------r-------~------,_------,_------,175
RT, room temperature. Composition: Mg-6Al-3Zn. UNS M1l630
20r-------~------_t--------r_------+_------~140
.¡¡; -'" tñ Cf)
15
105 400°F (204 OC)
ro o.. :2
Source: "Room and Elevated Temperature Properties of Magnesium CastAlloys," BuIletin No. 141-176, Dow Chemical Co., 1958. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3603, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 3
tñ Cf)
~
~
(J)
10
70
500°F (260 OC)
(J)
600°F (316 OC) 5
35 700 °F (371°C)
00
.¡¡; -'" tñ Cf) ~
2
4 6 Strain, 0.001 in./in.
8
O 10
30 ,-------,-----r------¡-----,-------,210
Mg.Oll AZ63A-T6 magnesium alloy sand cast bar, tensile stress-strain curves at room and elevated temperatures
25 1--------+----+----+----+---=-"""1 175
Composition: Mg-6Al-3Zn. UNS Ml1630
20
Source: "Room and Elevated Temperature Properties of Magnesbm Cast AIloys," BuIletin No. 141-176, Dow Chemical Co., 1958. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3603, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 4
140 ro o.. :2
15
105 tñ Cf) ~
ro
ro 10
70
35
2
4
6
Strain, 0.001 in./in.
8
o
10
Magnesium (Mg)/561
Mg.012 AZ63A-T6 magnesium alloy sand cast bar, high-temperature effect on tensile properties
Temperature, oC
-18 50
38
93
204
149
26~50
F,u' ultimate tensile strength; F,y' tensile yield strength. Tested at room temperature after exposure to elevated temperatures. Composition: Mg-6Al-3Zn. UNS M1l630 280
40
fiu
e .¡¡; -" rñ en ~
'"
O-
::¡;
30
210
Exposure (tested at room temperature)
¡¡¡
0100 h e1000h
•
20
.b
•
140
fi y 10
70
~
~
C>
c:
o ¡jj
1
00
1
100
t
200
t
300
lismperature, °F
t
400
1
500
rñ
~
Source: "Magnesium Design," Dow Chemical Co., 1957. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3603, CINDAS/ USAF CRDA Handbooks Operation, Purdue University, 1995, p 3
562/Magnesium (Mg)
Mg.013 AZ63A magnesium altoy sand cast bar, high-temperature effect on tensile properties
Temperature, oC
-129 50
40
"00
"'rñ" '"~
30
/, /Í ~
..¡
1ñ
93
-18
I
~
'" T4 ... T5 • T6
~\
\
c:
ro
42~50
20
"" :5
10
ro
a.
::¡¡
210 gf
~
~
"00
c:
$
\~ \
"*
~
140 E
5
70
l~
o
o
3o,-------,--------,-------,--------,-------,21o
OL-------L-------~------~------J-------~O
n~~IrfLFd -200
O
Source: "Magnesium Design," Dow Chemical Co., 1957. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3603, CINDAS/ USAF CRDA Handbooks Operation, Purdue University, 1995, p 4
280
~
E
316
Effect of 10 min exposure and test temperature on three tempers. Composition: Mg-6Al-3Zn. UNS M1l630
"00
$ $
204
200
400
Temperature, °F
600
I 800
Magnesium (Mg)/563
Mg.014 AZ80A-T5 magnesium alloy extrusion, tensile and compressive stress-strain curves
40 Ten~ V
35
/~
30 25 ·00
""cñm ~
20
/
iií 15 10 5
/
-
'r
Composition: Mg-8.5AI-O.5Zn. UNS Ml1800 Source: ASM Specialty Handbook, Magnesium and Magnesium Alloys, ASM International, 1999, p 166
-
200
-
150 ::;¡¡
'"
[L
cñ m ~
iií
1/
/ 1/
250
~ompreSSion
-
100
-
50
/
0.2
0.4
0.6
0.8
1.0
Strain, %
4or---------~--------_,--------_r--------_.280
Mg.015 AZ80A-T5 magnesium alloy forging, tensile and compressive stress-strain curves Composition: Mg-8.5AI-O.5Zn. UNS Ml1800 Source: "Magnesium Design," Dow Chemical Co., 1957. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3501, CINDASI USAF CRDA Handbooks Operation, Purdue University, 1995, p 2
30~--------~------~--~--~~----4_----------210
~
&.
::;¡¡
~ 20~--------~--_7L---_4----------+_--------_4140 cñ ~ ~
iií
iií
10~·----~~+_---------~--------~--------_470
2
4 Strain, 0.001 in.lin.
6
564/Magnesium (Mg)
25
y
20
~ rñ en ~
15
1ñ .l!1 .¡¡; t:
~
10
/
/ V
V
/
175
Mg.016 AZ91 A-F magnesium alloy die-cast bar, tensile stress-strain curve
140
Source: "Magnesium Design," Form No. 141-91-457, Dow Chemical Co., 1957. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3402, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 12
V
Composition: Mg-9AI-O.7Zn. UNS M11910
V
rf. :;¡;
105
rñ
~
.l!1 '¡¡; t:
70
~
35
5
4
2 Strain,
6
8
O
0,001 in.lin.
Mg.017 AZ91C-T4 magnesium alloy sand cast bar, tensile stress-strain curves at room and elevated temperature
25.-------,--------,-------,--------,-------,175
Composition: Mg-9AI-O.7Zn. UNS M11914
~------~------+_------+_------~------~140
ro
.¡¡; -"" rñ en
105
g¡ rñ en
~
~
1ñ .l!1
.l!1
'¡¡; t:
70
~
Strain,
0.001 in.lin.
'¡¡; t:
~
Source: "Room and Elevated Temperature Properties of Magnesium Cast Alloys," Bulletin No, 141-176, Dow Chemical Co" 1958. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3402, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 12
Magnesium (Mg)/565
Mg.018 AZ91C-T6 magnesium alloy sand cast bar, tensile stress-strain curves at room and elevated temperature
3or-------~------,_------_r------_r------_,210
25~-------~-------+--------r-~--~~-------4175
Composition: Mg-9AI-O.7Zn. UNS M11914
20~------+_------+_~~--~--~~_F~----_l140
Source: "Room and Elevated Temperature Properties of Magnesium CastAIloys," BuIletin No. 141-176, Dow Chemical Co., 1958. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3402, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 12
&.
::2
gf ~------~--~--~~--~~~------~------__1105 ~ .!!1 'ijj
<:
¡!!:1 ~----+.~L-----~------~------~------_170
~~L---+_------+_------_r------_r------_435
2
4 Strain,
6 0.001 in.lin.
8
425°F (218 oC) 24r-------,-------,-------,-------_r------~168
Mg.019 AZ91 C-T4 magnesium alloy sand cast bar, effect of elevated temperature on room-temperature properties
Composition: Mg-9AI-O.7Zn. UNS M11914 22~------~------_+---------~------+_------~154
--79--------- 112
16 J--------f-+_
14~----~~--~--~=-------~------~-------98 20r-------~------,-------_r-------,-------
E 15J--------~-------+--------J--------~------_+ E ;e. .~
'" 10
.5 c: o
~
~
5~------~-~--~~~----~r-------~--~~~
o
¡¡¡
10
lO'
Exposure time, h
lO'
4
10
Source: "Magnesium Design," Form No. 141-91-457, Dow Chemical Co., 1957. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3402, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 16
566/Magnesium (Mg)
Mg.020 AZ91C-T4 magnesium alloy sand cast bar, isochronous stress-strain curves
,----,----,----,------,----:--,-------,14o
F,n' ultimate tensile strength; F ty, tensile yield strength. Composition: Mg-9AI-O.7Zn. UNS M1l914 105
C\l
a.
'ijj
::;;:
-'"
rñ
rñ
U)
U)
~
70
1ñ
~ 'ijj
~
1ñ ~ 'ijj
"
" ~
~
35
o 140
20 400°F (204 OC)
105
ro
a.
'ijj
::;;:
-'"
rñ
rñ
(f)
(f)
~
70
1ñ ~
~
1ñ ~ 'ijj
'ijj
"
c: ~
~
35
L -____-L____
2
~L-
4
____
~
____
~
6 Strain, 0,001 in./in,
______
~
10
_____"O
12
Souree: "Isoehronous Stress-Strain Curves of Magnesium Casting Alloys," Dow CheITÚeal Co., 31 Oet 1958. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3402, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 12
Magnesium (Mg)/567
Temperature,
-18
38
93
oc
149
204
260
Mg.021 AZ91-T4, AZ91-T6 magnesium alloy sand cast bar, tensile stress-strain curves at room and elevated temperatures
316
5or_-----r------~----~------,_------r_----,350
• "" T6 condition O T4 condition
Composition: Mg-9AI-O.7Zn
40~--~~------+------4------~------~-----4280
~
30
210
ui
'" jg 140
20
10~-----~------1---·---4------~------~~~~70
~
OL------L------L-----~----~------~----~O
-g- 80 E
• O
""
.5 N
o..
ui
'"
~
ro
::a:'"
1Ql min
I
>10 min} Attemperature
40
........ L? ~
cr~
100
~
200
300 lemperature, °F
400
500
600
rJl
Source: "Room and Elevated Temperature Properties of Magnesium CastAlloys," Bulletin No. 141-176, Dow Chemical Co., 1958. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3402, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 14
568/Magnesium (Mg)
45
315
Mg.022 AZ91 E-T6 magnesium alloy sand cast bar, effect of elevated temperature on room-temperature tensile properties
40
280
Composition: Mg-9AI-O.7Zn. UNS M11918
35
~
~
.
~u
-- 1----.,
Source: B. Geary, "Corrosion Resistant Magnesium Casting Alloys," Magnesium Elektron, Ltd, Manchester, England. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3402, CINDAS/ USAF CRDA Handbooks Operation, Purdue University, 1995, p 14
245 ro
o.. ;:¡; 210 rñ
~
ro 175
25
20
...-.
~y
140
•
135
15 6
iS
...&.
:!. e
O
~
'"o
4
r"'"
~
............
...........
e
.
¡¡j
200
400
600
Exposure time, h
800
1000
Magnesium (Mg)/569
Mg.023 AZ91 C-T6/AZ91 E-T6 magnesium alloy casting, typical tensile stress-strain curves at room and elevated temperatures
~----~-----r-----,--~~.------,-----.175
~-----+------rT---~--~~+------r----~140
105 ·00 ~
a.'"
:2
rñ
rñ
Ul
Exposure: 1/2 h. Ramberg-Osgood parameter: n(room temperature) = 4.5; n(300 °F [or 149 OC]) = 3.9; n(400 °F [or 204 OC]) = 5.3. Composition: Mg-9Al-0.7Zn. The C and E versions have similar mechanical properties. The E version is purer and more corrosion resistant. AZ91C: UNS M11914. AZ9IE: UNS M11918 Source: MIL-HDBK-5H, Dec 1998, p 4-32
Ul
~
~
70
ro
~~--4------r----~------+-----~----~35
L-----~--
2
__
~
4
______L __ _ _ _
~
6 8 Straín, 0.001 ín.lín.
_ _ _ _ _ L_ _ _ _
10
~O
12
28,---------,----------,--------,---------.196
24~--------~-------~~----~~----------
168
20~--------~------~-7L-----~--------~140
8~--~~~~----·--~--------~--------~56
4~~~----~----·--~--------~--------~28
°0L-------,-2~----·--~4--------~6--------~80
Straín, 0.001 ín.lín.
Mg.024 AZ92A-F, AZ92A-T4, AZ92A-T6 magnesium alloy cast bar, tensile stress-strain curves at room temperature Composition: Mg-9AI-2Zn. UNS M11920 Source: MIL-HDBK-5, 1958. As published iu Aerospace Structural Metals Handbook, Vol 3, Code 3403, CINDASJUSAF CRDA Handbooks Operation, Purdue University, 1995, p 3
570/Magnesium (Mg)
28r---------.---------,---------.---------~196
24~--------+---------4-------~~--------~168
20~--------+---------~--------~--------~140
Mg.025 AZ92A-F, AZ92A-T4, AZ92A-T6 magnesium alloy cast bar, compressive stress-strain curves at room temperature
Composition: Mg-9Al-2Zn. UNS M11920 Source: MIL-HDBK-5, 1958. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3403, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 4
8~--_.~~+_--------+_--------~--------~56
~~~----+---------~--------~--------~28
4
2
6
Strain, 0.001 in./in.
28
196
,
24
20
--~\
g¡ 16
'" (/)
~ (J)
\6 \
12
T~
8
4
o
O
2
168
140
i'-....
----
4 Strain, 0.001 in./in.
1'\
6
56
~ 28
Mg.026 AZ92A-F, AZ92A-T4, AZ92A-T6 magnesium alloy cast bar, tensile tangent modulus stress-strain curves at room temperature
Composition: Mg-9Al-2Zn. UNS Ml1920 Source: MIL-HDBK-5, 1958. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3403, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 4
Magnesium (Mg)/571
28
196
24
168
Mg.027 AZ92A-F, AZ92A-T4, AZ92A-T6 magnesium alloy cast bar, compressive tangent modulus stressstrain curves at room temperature
Composition: Mg-9Al·2Zn. UNS Mll920
\T6 20
-
g¡ 16
E12
C/)
8
T4 F
Solirce: MIL-HDBK-5, 1958. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3403, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 4
140
\\
~" .~
112&: ::;¡:
""
gf ~
84 Cií
~
.......
~
""~
56
4
28
o
4
2
O
Strain,
6
0.001 in.lin.
Mg.028 AZ92A-T5, AZ92A-T6 magnesium alloy cast bar, temperature effects on tensile properties
Temperature, oC
-18
38
93
149
204
260
316
371
5o.----,~---,-----,----~----~----~----~350
F tu ' ultimate tensile strength; F ty ' tensile yield strength. Composition: Mg-9Al-2Zn. UNS Mll920
.¡¡;
30
f---------jl-~------j+----'l.-I----_I_----_I_----_+----__I
210 &: ::;¡:
~
j
20
140
10r-----r~--~-----~----_I_-=~~~~~----__I70
o~----~~--~-----~----~----~----~-----"o 80r----,r----,-----,----~----~----~----~
~40¡_---¡¡_--_¡--_=:~~~~~==~~~~----~ e
O
¡¡¡
100
200
300
400
Temperature, °F
500
600
700
l
Source: "Magnesium Design," Form 141-91-57, Dow Chemical Co., 1957. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3403, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 5
572/Magnesium (Mg)
Mg.029 AZ92A-T6 magnesium alloy casting, typical tensile stress-strain curves at room and elevated temperatures
r-----,------,------,------,------.-----~175
Exposure: 1/2 h. Composition: Mg-9Al-2Zn. UNS M1l920
~----4------+~L---~r_---+------~----~140
Source: MIL-HDBK-5H, Dec 1998, p 4-38 105
.c;;
ro
O-
:;¡; rñ (fj
""'rñ" (fj
~
~
(J)
(J)
70
~hY~~----~------4------+------+-----~35
L -____
~
2
25
o
14
""'rñ" C/)
~
_ _ _ _ _ _L -____~____~O
6 8 Strain, 0.001 in./in.
Compressive tangent modulus, GPa 28 42 56
~
/
Uí
5
~
10
Mg.030 AZ92A-T6 magnesium alloy casting, typical compressive stress-strain and tangent modulus curves at room temperature
Composition: Mg-9Al-2Zn. UNS M1l920 Source: MIL-HDBK-5H, Dec 1998, p 4-38 140
105
.......
~
(J)
70
35
2
10 6 8 Strain, 0.001 in./in. Compressive tangent modulus, 106 psi
4
ro
O-
:;¡; rñ C/)
/
/
12
70
X 1/ \
15
10
4
\ /
20
.c;;
_____ L_ _ _ _
o
12
Magnesium (Mg)/573
Mg.031 AZ92A-T6 magnesium alloy sand cast bar, isochronous stress-strain curves
24 , . . - - - , - - - - , - - - - , - - - - , - - - - , - - - - - , 1 6 8 300°F (149 OC)
Composition: Mg-9Al-2Zn. UNS M11920
155
20
16
112 ro o.. ::¡;
~ ui
'" ~
Souree: "Isoehronous Stress-Strain Curves of Magnesium Casting Alloys," Lett. Ene., Code 1.8 HB, Dow Chemieal Co., 31 Oet 1958. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3403, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 7
12
84
8
56
ui
~'" (f)
4~~~-+-~~-4~---~~~~_+~~~+_~~~28
o
t
o
24
•
168 400°F (204 OC)
20
140
16
112 155 ro o.. ::¡;
'w -'"
ui
84
'"
!!:'
ui
'"
~
i'i5 56
4
28
2
4
6 8 Sllrain, 0.001 in.lin.
10
574/Magnesium (Mg)
Temperature,
oc
Mg.032 AZ92A-T6 magnesium alloy sand cast bar, effect of exposure and test temperature on tensile properties
501~8________-,93__________ 2T04__________ 31~6_________4~2150
F tu ' ultimate tensile strength; F ty ' tensile yield strength. Composition: Mg-9Al-2Zn. UNS Ml1920 40r-~~-----r--------~----------+---------~280
210
30
::¡; ui
ui
'" ~
'" ~ 140
20
10~--------+---------+-~~~~~--------~70
Exposure
• 1/2 h O 100 h ... 1000 h oL---------~--------~----------~--------~O
160
........
6'
:!-
80
O>
'o"
üi
ro
o..
~
,gro
Source: "Mechanical Properties at Various Temperatures of AZ 92 A-T6 Sand Castings," Data Sheet, Alcoa Research Laboratories, 29 Aug 1957. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3403, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 5
----
J
,..,
.,....
I
~
~
200
400 Temperature, °F
600
800
Magnesium (Mg)/575
28
196
24
20
g¡
~
16
/~ .. ,
(/) 12
!
1/
8
4
'1 / ",.'
1/
L---
---
140
~
,,'
.
,,'
/.
."
.....
.. _0. ., _.. -
3 h exposure
/.,
"
_._._._.
-_..- _. ..-_-.. -.
28
28
o 196
24
r
20
/ L v· 1/// 11/ 8
56
55
- - - - 30min 1h 2h 10 h
l
~
~
.....
-
-::.. _.-
~ : .. ... .. ,:.. .. .. 400°F (204 oC) ."".
-
140
600°F (316 OC)
--
.-- .- -~ : :-:::-. - - . ~.- .-.-" ._.-" '-'-'- '._.o_u_ .. ._0'_ .. .. .,' , ..
/~~ - 1/.. , .. . ·
168
",oo.
~--
56
~
4
o o
2
4
6 8 Strain, 0.001 in.lin.
10
Composition: Mg-3Di-0.5Zr. Didymium is a natural mixture of rare-earth elements neodymium and praseodymium given the quasi-chemical symbol Di . 1.99 mm (0.505 in.) bar cut from large forging Source: "Magnesium Forging Alloys for Elevated Temperature Service," Dow Chemical Co., 1963. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3502, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 5
5 00°F (260 OC)
....
.'
o
168
// ................. --.-.-.- .-.-.- .--",....-.tI~ / ...~ ..... -' ".::.::.: ....... .. - .. - .. - ..-~
m
g
..... ~
...--.:-: .. .' -300°F (149 oC)
Mg.033 EK31XA-T6 magnesium alloy forging, isochronous stress-strain curves
28
576/Magnesium (Mg)
Mg.034 EZ33A-T5 magnesium alloy sand cast test bar, tensile stress-strain curve at room and elevated temperatures
25r-------,--------,-------,--------,-------, 175
20
Room temperature
300 'F (149 'e) '00 -'"
400 'F (204 'e
'"
500 'F (260 'e)
CI;
Composition: Mg-3RE-3Zn-O.7Zr. UNS M12330
140
ro
105 ~
Source: "Room and Elevated Temperature Properties of Magnesium CastAlloys," Bulletin No. 141-176, Dow Chemical Co., 1958. As puhlished in Aerospace Structural Metals Handbook, Vol 3, Code 3404, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 9
ui
~
tí
'"~
tí
~
~
'00
lO
~
70
600 'F (316 'e)
'00 lO
~
I
700 'F (371 'e) 5
35
800 'F (427 'e)
L -_ _ _ _ _ _L -______
~
______
~
_______ L_ _ _ _ _ _
6 Strain, 0.001 in./in.
~O
10
8
Mg.035 EZ33A-T5 magnesium alloy sand cast test bar, isochronous stress-strain curves at 204 oC (400°F)
150
- 20
Specimens exposed to elevated temperature for 3 h before loading. Composition: Mg-3RE-3Zn-O.7Zr. UNS M12330
125
ro
15 s f..-::::::;:::
100
o..
::¡;
/~
ui
~
75
~
'00 lO
~
50
25
I
.;::::::::;no¡;-
-
-
'00 -'" ui
r
'"
- 10
~
~
'00 lO
~
I I
-
0.4
Source: Properties and Selection: Nonferrous Alloys andSpecialPurpose Materials, Vol 2, ASM Handbook, ASM Intemational, 1990, p 504
15
0.8
1.6 Strain, %
1.2
2.0
2.4
5
o
2.8
Magnesium (Mg)/577
100
Mg.036 EZ33A-T5 magnesium alloy sand cast test bar, isochronous stress-strain curves at 260 oC (500°F)
- 14
90
- 12 1h 2 5--= 10 -10
80
t:::::=--= /¡ ~ ~ 15 s 15 min
70 ro
c..
::2;
60
ID U) ID
.¡¡¡ 50 -º1
·00 c:
~
40
~
~~
---=
¡---
f.--
Specimens exposed to elevated temperature for 3 h before loading. Composition: Mg-3RE-3Zn-O.7Zr. UNS M12330 Source: Properties and Selection: Nonferrous Alloys and SpecialPurpose Materials, Vol 2, ASM Handbook, ASM International, 1990, p 504
- 8
l;f V'
-=
6
-
4
-
2
30 20 10
0.4
0.8
1.2 1.6 Strain, %
2.0
2.4
o
2.8
60
Mg.037 EZ33A-T5 magnesium alloy sand cast test bar, isochronous stress-strain curves at 316 oC (600°F)
8
Specimens exposed to elevated temperature for 3 h before loading. Composition: Mg-3RE-3Zn-O.7Zr. UNS M12330
30min 1h 2
ro
6
c..
'00
::2;
-"
5
ID U)
00" U)
~
10
1ií -º1
4
~
-º1
·00 c:
·00 c:
~
~
20 2 10
ooL-----L-----L-----L----~----~----~--~O
0.4
0.8
1.2 1.6 Strain, %
2.0
2.4
2.8
Source: Properties and Selection: Nonferrous Alloys and SpecialPurpose Materials, Vol 2, ASM Handbook, ASM International, 1990, p504
578/Magnesium (Mg)
Mg.038 EZ33A-T5 magnesium alloy sand cast test bar, isochronous stress-strain curves at 371°C (700°F)
5or-----,-----.-----.-----~----~----_r----~
7
40r-----r---~----~----_+----_+----_+----~
Specimens exposed to elevated temperature for 3 h before loading. Composition: Mg-3RE-3Zn-O.7Zr. UNS M12330
6
5 '00
5min 10 15 20
4
Source: Properties and Seleetion: Nonferrous Alloys and SpeeialPurpose Materia/s, Vol 2, ASM Handbook, ASM Intemational, 1990, p 505
"'
~
..!!1 '00
3 e ~
1h 2
2
5 10
°OL-----L-----L----~----~----~----L---~O
0.4
0,8
1.2 1.6 Strain, %
2.0
2.4
2.8
Mg.039 EZ33A-T5 magnesium alloy sand cast test bar, isochronous stress-strain curves at 427 oC (800°F)
50r----,----~----~----_,----_,----_r----,
7
40r-----~----~----+-----+-----4-----4-----~
Specimens exposed to elevated temperature for 3 h before loading. Composition: Mg-3RE-3Zn-O.7Zr. UNS M12330
6
5 ro
o..
~ 30r-----r---~----~----_+----_+----_+----~
~1ií ..!!1 '00 e
'00
"'
g
m
15 S
30
2min
~
5 10
20 1h 5
0.4
0.8
1.6 1.2 Strain, %
2.0
2.4
'00
3 e ~
2
15
10
..!!1
Source: Properties and Se/eetion: Nonferrous Alloys and SpecialPurpose Materia/s, Vol 2, ASM Handbook, ASM Intemational, 1990, p 505
Magnesium (Mg)/579
25
20
I
/
15
'"
~
U5
5
l.----
--
/
1/
Source: MIL-HDBK-5H, Dec 1998, p 4-43
105
o..'"
::¡;
/
70
35
2
Ramberg-Osgood parameter: n(room temperature) = 15. Composition: Mg-3RE-3Zn-O.7Zr. UNS M12330
140
1/
'iii -'"
10
Mg.040 EZ33A-T5 magnesium alloy cast, tensile stress-strain curve at room temperature
175
4
6 Strain, 0.001 in.lin.
8
10
~
580/Magnesium (Mg)
Dístance frem chill, mm
O
25
51
76
102
3or---------~---------r--------~--------~210 ~
a..
::¡;
~
• 1 ín. Á 2 ín.
~ al
.¡¡¡
~
(25 mm) thíck (51 mm) thíck
~
251---~....--~;;;::_-----+----__+----___i
al
175 .¡¡¡
~ ~
~
~
~
<:
~
~
~
"
E
:5
E
20
140
20r---------r---------,---------,--------.140
10L---------L---------L---------L-------~70
6
E E
~
!!?.
.5 N
4
.!:
"
~Cl
"o
¡¡¡
20
2 Dístance from chill. ín.
3
4
:5
Mg.041 EZ33A-T5 magnesium alloy sand cast plate, effect of end chill on tensile properties
Thickness: 1 in. (25 mm) and 2 in. (51 mm). Composition: Mg-3RE-3Zn-O.7Zr. UNS M12330 Source: B. Lagowski and J.W. Meier, Premium Strength in Sand-Cast Magnesium Alloys, AFS Trans., Vol 72, 1964, P 673-685. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3404, CINDAS/ USAF CRDA Handbooks Operation, Purdue University, 1995, p 9
Magnesium (Mg)/581
Mg.042 EZ33A-T5 magnesium alloy sand cast bar, effect of exposure at elevated temperatures on room-temperature tensile properties
210
30
Exposure:
• 400 'F (204 'C)- 196 ~ ... 500 'F (260 'C) • 600 'F (316 'C)
~ 28
~ 22
154
22
154
.( .
l•
--
140 ~ :::¡;
~
:5 el 126 ~ (¡j "O
Qi
.>'
.,
:¡g
112 c: ~
14
98
6 ~
E E
~ .5
4
'" .s c:
o
~
el
c:
o üJ
2
~ ~
. 1000
2000
3000
Exposure time, h
4000
5000
Composition: Mg-3RE-3Zn-O.7Zr. UNS M12330 Source: "Magnesium Design," Form No. 141-91-457, Dow Chemical Co., 1957. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3404, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 9
582/Magnesium (Mg)
Mg.043 HK31A magnesium alloy separately cast bar, tensile stress-strain curves
15or-----r-----r----,-----,-----,----~----~
20
Composition: Mg-3Th-0.7Zr. UNS M13310 Source: Properties and Selection: Nonferrous Alloys and SpecialPurpose Materials, Vol 2, ASM Handbook, ASM Intemational, 1990, p 505
149 oC (300°F)
I
204 oC (400 °F) 260 oC (500°F) 316 oC (600 °F)
15 ·00
-'"
I
"''"
371°C (700°F) 10
~
.l!1 ·00 e
~
50~-++_~--~----_4----_+----_+----_+----~
427 oC (800°F)
5
25~----~~~-----4-----+-----+-----+----~
°0L-----0.L2----0~.-4----0~.6-----0~.8-----1~.0-----1L.2----~1.; Slrain, %
300.-------,-------,-------,-------,------, 40
~-i---
24 oC (75°F)
200~------~--~~~------~------~----~30 149 O? (300°F) 204 oC (400 °F)
Mg.044 HK31A-H24 magnesium alloy sheet, tensile stress-strain curves at various temperatures Sheet thickness: 1.63 mm (0.064 in.). Test direction: longitudinal. Typical yield strength: 21°C (70 °F), 205 MPa (30 ksi); 149 oC (300°F), 165 MPa (24 ksi); 204 oC (400°F), 145 MPa (21 ksi); 260 oC (500°F), 115 MPa (17 ksi); 316 oC (600°F) 48 MPa (7 ksi); 343 oC (650°F), 28 MPa (4 ksi). Composition: Mg-3ThO.7Zr. UNS M13310 Source: Properties and Selection: Nonferrous Alloys and Pure Metals, Vol 2, 9th ed., Metals Handbook, American Society for Metals, 1979, p 558
100~--~+7~------~------~------~------
_ - I - - - - t - - 316 oC (600°F)
10
--+----¡-- 371°C (700°F)
I__ ~
_ _ _ _ _ _L __ _ _ _ _ _L __ _ _ _ _ _L __ _ _ _
0.4
0.8
1.2 Strain, %
~~
1.6
____
~O
2.0
Magnesium (Mg)/583
Mg.045 HK31A-H24 magnesium alloy sheet, tensile stress-strain curves at various temperatures
300~------~------r-------~------~------.
40
_-1----24 oC (75°F) 250~--~~~~~~~~~~+-~~~+-~~~
200~--~---~~~~+-~~~+-~~~+-~--~
30
T
149 (300°F) 204 oC (400 °F)
ro
a.
::;:
-00
~150~~~-fh?~~~-~~~~+_~~~+_~~~
~
260 oC (500°F)
20
CJ)
"'uien" ~
1ií
Sheet thickness: 1.63 mm (0.064 in.). Test direction: transverse. Typical yield strength: 21°C (70°F), 205 MPa (30 ksi); 149 oC (300°F), 165 MPa (24 ksi); 204 oC (400°F), 145 MPa (21 ksi); 260 oC (500°F), 115 MPa (17 ksi); 316 oC (600°F) 48 MPa (7 ksi); 343 oC (650°F), 28 MPa (4 ksi). Composition: Mg-3Th-0.7Zr. UNS M13310 Source: Properties and Selection: Nonferrous Alloys and Pure Metals, Vo12, Metals Handbook, American Society for Metals, 1979, p 558
100~--~~~--~~-~~~~+-~~~+-~--~
316 oC (600°F) 10
371°C (700°F)
DA
0.8
12 Strain,
1.6
O
2.0
%
300r-------,-------·r-------~------,_----__,
40 250~--~~+_~~~+-~~~+_~~~+_~~~
Sheet thickness: 1.63 mm (0.064 in.). Test direction: longitudinal. Composition: Mg-3Th-0.7Zr. UNS M13310
200~~~~+_--~~+_~~~+_~~~+_~~~30
100~--~~~~~~~~~~+_~~~+_~~~
10 50~~~~+_--~~+_~~~+_~~~+_~~~
DA
0.8
1.2 Strain, %
1.6
Mg.046 HK31A-H24 magnesium alloy sheet, compressive stress-strain curves at various temperatures
Source: Properties and Selection: Nonferrous Alloys and Pure Metals, Vo12, Metals Handbook, American Society for Meta1s, 1979, p 558
584/Magnesium (Mg)
3oo,-------,-------,--------,-------,--------,
Mg.047 HK31A-H24 magnesium alloy sheet, compressive stress-strain curves at various temperatures
40 250~------+-------~-------+------_4------~
200~------+-------~-------+------_4------~
::¡;
24 oC (75°F) 149 oC (300°F) 204 oC (400°F)
~
260 oC (500°F)
ro
Sheet thickness: 1.63 mm (0.064 in.). Test direction: transverse. Composition: Mg-3Th-0.7Zr. UNS M13310 Source: Properties and Selection: Nonferrous Alloys and Pure Metals, Vo12, Metals Handbook, American Society for Metals, 1979, p 558
30
_ _- -
o..
~
~150~----~~~q_--~----~=+~~--_4------~
20
i'i5
''"" ~
i'i5
100~--~~~------~-------+------_4------~ ~
_ _¡_-316 oC (600°F)
10
50~++--~~------~------_+------_4------~
--,-:-\..---+---T- 371°C (700°F) L -_ _ _ _-L______
OA
~
______L __ _ _ _
0.8
12
~
______
1B
~O
2~
Strain, %
140,-----,-----,-----,-----,-----,-----,-----'20
16
Mg.048 HK31A-H24 magnesium alloy sheet, isochronous stress-strain curves at 204 oC (400°F)
Sheet thickness: 1.63 mm (0.064 in.). Specimens exposed to elevated temperatures for 3 h before loading. Composition: Mg-3Th-0.7Zr. UNS M13310 Source: Properties and Selection: Noriferrous Alloys and Pure Metals, Vol 2, Metals Handbook, American Society for Metals, 1979, p 560
40~~~-----4-----+-----+-----+-----r----~
4 20~----~----+-----+-----+-----~-----r----~
°0L-----OLA-----OL.8-----1~.2-----1~.6-----2~.-0----2~.-4----~2.R Strain, %
Magnesium (Mg)/585
140~----~----~----~----'------r-----r-----'20
_ _- i - - - ¡ 5min 10
16
100~--~~~~+---~~~--~~~~~~-+15
Mg.049 HK31A-H24 magnesium alloy sheet, isochronous stress-strain curves at 260 oC (500°F)
Sheet thickness: 1.63 mm (0.064 in.). Specimens exposed to e1evated temperatures for 3 h before loading. Composition: Mg-3Th-0.7Zr. UNS M13310 Source: Properties and Selection: Nonferrous Alloys and Pure Metals, Vo12, Metals Handbook, American Society for Meta1s, 1979, p 560
20 30
4
~--~----~------L----~----~----L---~O
0.8
004
1.2
1.6
2.0
204
2.8
Strain, %
14or-----~----,-----·,------,-----r-----,-----,20
120~----+-----+-----·~----~----~-----+-------
16 100~----+-----+------~----~----~-----+------1
_....._-1 10
4
100 h 0.8
1.2
1.6
Strain, %
2.0
2.4
Sheet thickness: 1.63 mm (0.064 in.). Specimens exposed to elevated temperatures for 3 h before loading. Composition: Mg-3Th-0.7Zr. UNS M13310 Source: Properties and Selection: Nonferrous Alloys and Pure Metals, Vo12, Metals Handbook, American Society for Metals, 1979, p 560
~--~----~-----k----~----~----L---~O
0.4
Mg.050 HK31A-H24 magnesium alloy sheet, isochronous stress-strain curves at 316 oC (600°F)
2.8
586/Magnesium (Mg)
-- -
Mg.051 HK31A-H24 magnesium alloy sheet, tensile stress-strain curves at room and elevated temperatures
35,-----,-----,------,-----,-----,------,-, 245
30r-----+-----~----~~---+----~------r-~
210
175
~ 20~----r-_t~~~~r-----t=~~~.---t_~ 140 ~
::!!:
ui
i ro
ui
I/l
15r-----+,H~--~----~-----+----~----~r-~ 105
-
600°F (316 OC)
- - --
--
~
¡¡¡
Test direction: longitudinal and transverse. Typical shear ultimate strength in the lowest strength direction, 180 MPa (26.0 ksi) for sheet 0.406--6.350 mm (0.0160.250 in.) thick and plate 25.42-76.20 mm (1.0013.000 in,) thick. Composition: Mg-3Th-0.7Zr. UNS M13310 Source: "Magnesium in Design," Form No. 141-213-67, Dow Chemical Co., 1967. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3503, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 6
70
5~ur~r_----~----r_----r_----r_----r__1
35
°OL-----~----~----~----~----~----~~~O
0.2
0.4
0.6 0.8 Strain, %
1.0
1.2
210
Mg.052 HK31 A-H24 magnesium alloy sheet, compressive stress-strain curves at room and elevated temperatures
25
175
20
140
Test direction: longitudinal and transverse. Typical bearing ultimate strength in the lowest strength direction with edge-to-diameter ratio of 2.5, 450 MPa (65.0 ksi) for sheet 3.20-6.350 mm (0.126-0.250 in.) thick and plate 25.42-76.20 mm (1.001-3.000 in.) thick. Composition: Mg-3Th-0.7Zr. UNS M13310
30 - - Longitudinal - Transverse
70 °F (21 OC)
'"
~
!l..
::!!:
ui I/l 15
105 ui
~
~
10
70
- --
600 °F (31 6 oC) 35
5
O O
0.2
0.4
0.6 Strain, %
0.8
1.0
O
1.2
Source: "Magnesium in Design," Form No. 141-213-67, Dow Chemical Co., 1967. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3503, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 9
Magnesium (Mg)/587
Mg.053 HK31A-H24 magnesium alloy sheet, effect of elevated temperatures on room-temperature compressive properties
182
26
400°F (204 oC) 24
.¡¡; .:.: "i
22
\
~
Source: "Magnesium in Design," Form No. 141-213-67, Dow Chemical Co., 1967. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3503, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 7 154
r_____500 °F (260 OC) r---. _ 1----
'" ~
20
18
-
~
----~
~
112 5000
300
- 40
-
200
30
'"
o.. ::¡:
24 oC (75°F) 150
éñ 100
50
Mg.054 HK31A-O magnesium alloy sheet, tensile stress-strain curves at various temperatures
Sheet thickness: 1.63 mm (0.064 in.). Test direction: longitudinal. Composition: Mg-3Th-0.7Zr. UNS M13310
250
f!!
~
126
4000
2000 3000 Exposure time, h
~
gf
140
1000
gf
Composition: Mg-3Th-0.7Zr. UNS M13310
168
1:
¡; V
-
.1
149 (300°F) 204 'C (400 'F)
:
260 oC (500 'F)
I
I T
316 'C (600 'F)
371
0.4
0.8
1.2 Strain, %
,¿
(700 'F)
1
1.6
-
10
Source: Properties and Selection: Nonferrous Alloys and Pure Metals, Vo12, Metals Handbook, American Society for Metals, 1979, p 559
588/Magnesium (Mg)
300
Mg.055 HK31 A-O magnesium alloy sheet, tensile stress-strain curves at various temperatures
40
-
Sheet thickness: 1.63 mm (0.064 in.). Test direction: transverse. Composition: Mg-3Th-0.7Zr. UNS M13310
250
200
'"
gf 150 ~
éií 100
50
24 oC 75°F)
V
a.
:;¡;
k
/~
Source: Properties and Selection: Nonferrous Alloys ami Pure Metals, Vol 2, Metals Handbook, American Society for Metals, 1979, p 559
30
-
I
{
-,'. I
149 oC (300°F) I 204 oC (400 °F) 260 oC (500°F)
-
316 oJ (600°F)
-
-1
11
~/ "
10
371 od (700°F)
-1
DA
0.8
1.2
o
1.6
2.0
Strain, %
Mg.056 HK31A-O magnesium alloy sheet, compressive stress-strain curves at various temperatures
300 -
40
250
Sheet thickness: 1.63 mm (0.064 in,). Test direction: longitudinal. Composition: Mg-3Th-0.7Zr. UNS M13310 -
200
Source: Properties and Selection: Nonferrous Alloys and Pure Metals, Vol 2, Metals Handbook, American Society for Metals, 1979, p 559
30
~
~ 24 oC (75°F)
~149°C(3oo°F) ./ 204l (400°F)
, 100
50
~
/,
f;
20
260 oC (500°F)
I
316 oC (600 °F)
I
¡---
IV
DA
-
10
371°C (700°F)
0.8
1.2 Strain, %
1.6
o
2.0
'"
~
éií
Magnesium (Mg)/589
Mg.057 HK31A-O magnesium alloy sheet, compressive stress-strain curves at various temperatures
300 -
40
250
Sheet thickness: 1.63 mm (0.064 in.). Test direction: transverse. Composition: Mg-3Th-0.7Zr. UNS M13310 -
200 CIl
a.
.,.,..-¡.....--
::;¡;
¡¡f 150
/; ~ ~
~
100
50
7~ ~
24 oC
(í
Source: Properties and Selection: Nonferrous Alloys and Pure Metals, Vol 2, Metals Handbook, American Society for Metals, 1979, p 559
30
5 °F) -
_ 149 oC /300 °F) ::::- 204 oC (400°F) 260 oC 500°F)
316°'[ (600°F)
-
10
371 oJ (700°F) 0.8
0.4
1.2
1
o
1.6
2.0
Strain, %
30 __ 1
-
-
LOngitudi~al 70°F (21°C)
1.
Ci5
/;, ~
10
5
300 ~~49~~ ~OO ~f. (204 °Cl.
500°F (260 OC)
'/
1'1) -:/
r
Test direction: .longitudinal and transverse. Composition: Mg-3Th-0.7Zr. UNS M13310
140
_ ~-- ,....._.- ---
15
175
.......
./
20 .¡¡;
Mg.058 HK31 A-O magnesium alloy sheet, tensile stress-strain curves at room and elevated temperatures
Transverse
25
"'ui" '"~
210
0.2
CIl
-
a.
::;¡;
105 ui
~
70
600°F (316 OC) 35
0.4
0.6 Strain, %
0.8
1.0
1.2
o
Source: "Magnesium in Design," Form No. 141-213-67, Dow Chemical Co., 1967. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3503, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 6
590/Magnesium (Mg)
Mg.059 HK31A-O magnesium alloy sheet, complete tensile stress-strain curves at low temperatures
6or----,-----,-----,----~----_r----_r----,420
Composition: Mg-3Th-O.7Zr. UNS M13310 50~----~--~r_----+_--~~~--~----1_----~350
280
40
o..'"
.¡¡;
::¡;
-'"
uf (/) ~
Source: R.P. Reed, R.P. Mikesell, and R.L. Greeson, "Sorne Mechanical Properties of Magnesiurn Alloys al Low Ternperatures," ASTM STP 287, 1961, P 61-73. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3503, CINDAS/USAP CRDA Handbooks Operation, Purdue Universily, 1995, p 7
210 (/) uf
30
~
éi5 20
140
10
70
00
5
10
15
20
O 35
30
25
Strain, %
Mg.060 HK31A-O magnesium alloy sheet, compressive stress-strain curves at room and elevated temperatures
175
25 - - Longitudinal -- Transverse
Composition: Mg-3Th-O.7Zr. UNS M13310
140
20
--
Source: "Magnesiurn in Design," Porm No. 141-213-67, Dow Chemical Co., 1967. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3503, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 9
70°F (21°C)
--
I
400°F (204 OC) 500 °F (260 OC)
105
o..'"
::¡; uf
(/)
600°F (316 OC) 70 700°F (371°C)
35
L -_ _ _ _
~
0.2
_ _ _ _- L_ _ _ _- J_ _ _ _ _ _
DA
0.6 Strain, %
~
0.8
____
~
1.0
____
_JO 1.2
~
Magnesium (Mg)/591
120
15
100
'"
80
c..
::¡;: ui
'" Q)
1;;
60
~
-
/"
V/ '
iP
V
16
Sheet thickness: 1.63 mm (0.064 in.). Specimens exposed at testing temperature for 3 h before loading. Composition: Mg-3Th-0.7Zr. UNS M13310
10
30
-::::-
Mg.061 HK31A-O magnesium alloy sheet, isochronous stress-strain curves at 204 oC (400°F)
-
Source: Properties and Selection: Noriferrous Alloys and Pure Metals, Vol 2, Metals Handbook, American Society for Metals, 1979, p 561
12
-100h
'00
.>::
ui
'"~
"tí -
'00
8
~
'00
e
e
~
~
40 -
4
20
0.4
0.8
'1.2
1.6
2.0
o
2.8
2.4
Strain, %
Mg.062 HK31A-O magnesium alloy sheet, isochronous stress-strain curves at 260 oC (500°F)
120 -
16
Sheet thickness: 1.63 mm (0.064 in.). Specimens exposed at testing temperature for 3 h before loading. Composition: Mg-3Th-0.7Zr. UNS M13310
100
'"
80
c..
::¡;: ui
'" Q)
1;;
60
~
'00
e
~
40
I
?
V--
~
I
20
V
-
15 S
---
'00
1 min 1h
.>:: ",-
2
~-
V
en
- 8
-
~
'00
c:
4
-1'1'" 0.8
~ ~
-
0.4
Source: Properties and Selection: Nonferrous Alloys and Pure Metals, Vol 2, Metals Handbook, American Society for Metals, 1979, p 561
12
1---30
1.6 Strain, %
'1.2
2.0
2.4
o
2.8
592/Magnesium (Mg)
120 -
Mg.063 HK31A-O magnesium alloy sheet, isochronous stress-strain curves at 316 oC (600°F)
16
Sheet thickness: 1.63 mm (0.064 in.). Specimens exposed at testing temperature for 3 h before loading. Composition: Mg-3Th-0.7Zr. UNS M13310
100
I
I
40
20
Source: Properties and Selection: Nonferrous Alloys and Pure Metals, Vol 2, Metals Handbook, American Society for Metals, 1979, p 561
- 12 .¡¡; -'"
tñ
'"e!
~ r=:::
ft ~
~
¡..--
t::-~
--
15 s _ 8 1 min 5
¡..---
~
-
100 h 0.8
1.2
1.6
2 .¡¡; c: ~
1020
¡..---
:...--
0.4
¡¡¡
2.0
2.4
4
o
2.8
Strain, %
Mg.064 HK31A-T6 magnesium alloy sand cast test bar, tensile stress-strain curves at room and elevated temperatures
150r-----r-----r----,-----,-----,----~----~
20 125~----~--~~--~~--~----_+----_+-----
Specimens exposed at testing temperature for 3 h before loading. Composition: Mg-3Th-0.7Zr. UNS M13310
149 oC (300°F)
I
204 oC (400 °F) 260 oC (500°F 100 ~-+-~~8f~==t~;;; 316 oC (600 °F) ~
Source: Properties and Selection: Nonferrous Alloys and Pure Meta/s, Vo12, Metals Handbook, American Society for Metals, 1979, p 583
15
o.. :2
.¡¡; -'"
I 371°C (700°F) '" ~ 75~--~~~~----~----~--=-_+----_r----~ tñ
tñ
'"e! ¡¡¡
10 2 .¡¡;
2 .¡¡;
c: ~
c: ~ 50~~~~--~----~----_+----_+----_r----~
427 oC (800°F)
5
25~--~~~~----~----_+----_+----_r----~
0.2
0.4
0.6
0.8
Strain, %
1.0
1.2
1.4
Magnesium (Mg)/593
Mg.065 HK31A-T6 magnesium alloy separately cast test bars, isochronous stress-strain curves at 204 oC (400°F)
150 - 20
125
I
~
~
~
~
15 s ..........: 10 h
Specimens exposed at testing temperature for 3 h before loading. Composition: Mg-3Th-O.7Zr. UNS M13310
p--
Source: Properties and Selection: Nonferrous Alloys and Pure Metals, Vol 2, Metals Handbook, American Society for Metals, 1979, p 583
- 15
v
~ ui rn ~
;¡;
- 10 ..!!1 '00
J
t:
~
50
25
I
-
5
1/ 0.4
0.8
1.2
2.0
1.6
2.4
2.8
Strain, %
150 -
125
&.
I
100
J
::¡;
¡j
ui
~
1ii
./.
75
r/~
(1)
~
t:
~
~
~
5h
1--
Mg.066 HK31A-T6 magnesium alloy separately cast test bars, isochronous stress-strain curves at 260 oC (500°F)
20
Specimens exposed at testing temperature for 3 h before loading. Composition: Mg-3Th-O.7Zr. UNS M13310
_
10 h -
Source: Properties and Selection: Nonferrous Alloys and Pure Metals, Vol 2, Metals Handbook, American Society for Metals, 1979, p 583
15 '00
-"
ui ti) ~
;¡; - 10 ..!!1 '00 t:
~
~
50
25
I
-
5
I
0.4
0.8
1.2
1.6
Strain, %
2.0
2.4
2.8
594/Magnesium (Mg)
150
Mg.067 HK31A-T6 magnesium alloy separately cast test bars, isochronous stress-strain curves at 316 oC (600°F)
20 125
Composition: Mg-3Th-O.7Zr. UNS M13310 15 min
ro
100
1h 2
a. ~
!Ji (/)
~
30
~
15 '00
-'"
5 10
75
Source: Properties and Selection: Nonferrous Alloys and Pure Metals, Vol 2, Metals Handbook, American Society for Metals, 1979, p 583
'00
!Ji (/) ~
10
tí ~
'00
e
e
~
~
50 5 25
0.4
0,8
1.2
1.6
2.0
2.4
2.8
Strain, %
Mg.068 HK31A-T6 magnesium alloy sand cast test bar, complete tensile stress-strain curves at low temperatures
5o.-------------.-------------.-------------~350
-424 'F (-253 'C)
Composition: Mg-3Th-O.7Zr. UNS M13310 -109 'F (-78 'C) 80 'F (27 'C) 30~--+7------~L-----~~~_+------------~210
ro
a. ~
!Ji (/) ~~~~------+_------------1_------------~140
10~------------+-------------1-------------~70
°0L-------------~5------------~10------------~1~
Strain, %
~
Source: R.P. Reed, R.P. Mikesell, and R.L. Greeson, "Sorne Mechanical Properties of Magnesium Alloys at Low Temperatures," ASTM STP 287, 1961, P 61-73. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3503, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 7
Magnesium (Mg)/595
225 200 175
//¡
150
~
al
J
o.. ::;; 125
g
m ~
Cñ 100 75 50 25
V
/
--
24 oC (710F)
-
Mg.069 HM21A-T8 magnesium alloy sheet, tensile stress-strain curves at various temperatures
30
Test direction: longitudinal. Specimens held at test temperature 3 h before testing. Composition: Mg-2ThO.8Mn. UNS M13210
25 149 oC (300°F)
¡...---
I
204 oC (400°F)
Source: Properties and Selection: Nonferrous Alloys and Pure Metals, Vol 2, Metals Handbook, American Society for Metals, 1979, p 562
-
20 '¡¡j
V"
260 oC Joo °F) _ 15 316·C r o °F)
~P--
/¡ '?/./"'" .¡--
371°C (700°F) -
"'
~
10
/'
1/ If
0.2
- 5
0.4
0.6
0.8
1.0
o
1.4
1.2
Strain, %
Mg.070 HM21A-T8 magnesium alloy sheet, tensile stress-strain curves at various temperatures
225
- 30
200 175
V
150
/ l--:: ~~
al
o.. ::;; 125
m ~
Cñ 100 75 50 25
~
~
~-
) V,.- ¡.f-
--=
0.2
25
Source: Properties and Selection: Nonferrous Alloys and Pure Metals, Vol 2, Metals Handbook, American Society for Metals, 1979, p 562 149 oC (300°F) 204 oC i400 °F\ 260 oC (1000F) _
20 '¡¡j
"'
316°C r00F)
371°C (iOO °F) -
/?V
V
10
- 5
0.4
0.6
0.8
Strain, %
Test direction: transverse. Specimens held at test temperature 3 h before testing. Composition: Mg-2ThO.8Mn. UNS M13210
24 oC (75°F)
1.0
1.2
o
1.4
m ~
Cñ
596/Magnesium (Mg)
Mg.071 HM21A-T8 magnesium alloy sheet, compressive stress-strain curves at various temperatures
150 20 125
15
100 ro o..
:¡; ui rJ)
Test direction: longitudinal. Specimens held at test temperature 3 h before testing. Composition: Mg-2ThO.8Mn. UNS Ml3210 Source: Properties and Selection: Nonferrous Alloys and Pure Metals, Vo12, Metals Handbook, American Society for Meta1s, 1979, p 562 .¡¡;
""ui
75
rJ)
10
~
ro
~
ro
50 5 25
1.0
1.2
1.4
Strain, %
Mg.072 HM21A-T8 magnesium alloy sheet, compressive stress-strain curves at various temperatures
150 20
-
Test direction: transverse. Specimens held at test temperature 3 h before testing. Composition: Mg-2ThO.8Mn. UNS Ml3210
125
/'
100
11
ro o..
:¡; ui UJ
75
~
ro
50
25
+-
24 oC (75°F) 15
-
~
I
ui UJ
/ /
-
10
-
5
1/ 0.2
Source: Properties and Selection: Nonferrous Alloys and Pure Metals, Vo12, Metals Handbook, American Society for Meta1s, 1979, p 562
0.4
0.6
0.8
Strain, %
1.0
1.2
1.4
ro~
Magnesium (Mg)/597
140
-
I
I~ ~ v 1/
100
'"
~
60
~
40
16
Mg.073 HM21A-T8 magnesium alloy sheet, isochronous stress-strain curves at 204 oC (400°F)
Sheet thickness: 1.63 mm (0.064 in.). Specimens held at test temperature 3 h before testing. Composition: Mg2Th-0.8Mn. UNS M13210 Source: Properties and Selection: Nonferrous Alloys and Pure Metals, Vol 2, Metals Handbook, American Society for Metals, 1979, p 563
100 -
I
(f)
.~
-
l'
o.. ::¡; rñ 80
20
1 m1in 1h 10
I~
120
.!!1
_158
-
I -
4
20
0.4
0.8
1.2
1.6
2.0
2.4
o
2.8
Slrain, %
Mg.074 HM21A-T8 magnesium alloy sheet, isochronous stress-strain curves at 260 oC (500°F)
Sheet thickness: 1.63 mm (0.064 in.). Specimens held at test temperature 3 h before testing. Composition: Mg2Th-0.8Mn. UNS M13210 Source: Properties and Selection: Nonferrous Alloys and Pure Meta/s, Vol 2, Metals Handbook, American Society for Metals, 1979, p 563
40
I I -4
2oH-----r---~-----~----~----_+----_+----~
°0L-----OL.4----~0.-8----·~1.~2----1~.6-----2~.0-----2~.4-----"2.¡ Strain, %
598/Magnesium (Mg)
100
90 80 70
'"
Il.
:2 60 cñ
g¡
ti
50
.l!1 .¡¡;
~ 40 30
I
-
~ ~V -
155
-
Mg.075 HM21A-T8 magnesium alloy sheet, isochronous stress-strain curves at 316 oC (600°F)
12
Sheet thickness: 1.63 mm (0.064 in.). Specimens held at test temperature 3 h before testing. Composition: Mg2Th-0.8Mn. UNS M13210
21 h----= - 10
Source: Properties and Selection: Nonferrous Alloys and Pure Metals, Vol 2, Metals Handbook, American Society for Metals, 1979, p 563
1 min 2~
5 10
¡...--f~ ~ ~ ..-,t¡¡ ~ po- ¡....--f.,.---
-
30
5 10
~ ~::::~/
--
V
14
-
.¡¡; ..>:
-
8
.l!1 .¡¡; -
6
-
4
-
2
20 10
0.4
0.8
1.6 1.2 Strain, %
cñ
'"~
1ñ
100-
2.0
2.4
o
2.8
t:
~
Magnesium (Mg)/599
3or-------,-------~--------r_------,_------_,210
Mg.076 HM21A-T8 magnesium alloy sheet, compressive stress-strain curves at room and elevated temperatures
25~------~-------+--------~------~------~175
Top curves are for the longitudinal direction. Bottom curve is transverse. Composition: Mg-2Th-O.8Mn. UNS Ml3210
140
o.. :2
~ tJi
105
ID
~
tJi
ID
~
iií 70
~~~--+_------+_------4_------~------_435
L -_ _ _ _ _ _L -_ _ _ _ _ _L _ _ _ _ _ _
~
_ _ _ _ _ __ J_ _ _ _ _ _
~O
30
210
25
175
20
¡,- -,
rñ 15
ID
o.. :2 105 rñ
1/
~
iií
5
140
/'
~
10
70°F (21°C)
I
/ V
o
O
!
UJ
/
70
35
2
4-
6
Strain, 0.001 in./in.
8
Source: "Magnesium in Aerospace Design," Bulletin 141-213, Dow Chemical Co., 1963. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3504, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 8
600/Magnesium (Mg)
40r------,-----,------,------,------r-----~
280
Mg.077 HM21 A-T81 magnesium alloy sheet, tensile stress-strain curves at various temperatures
35~----~----~------+------+----_=~~--~
245
Sheet thickness: 4.826 mm (0.190 in.). Composition: Mg2Th-0.8Mn. UNS M13210
30~----~----~------+-~---+------~----~
210
25~----~----~_7L-~~-----+------~----~
175
Source: "Magnesium in Aerospace Design," Bulletin 141-213, Dow Chernical Co., 1963. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3504, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 6
Il..
:2
140 ui
'"~
ro
600 'F (316 'C) 105 700 'F (371 'C)
70
800 'F (427 'C)
4
2
10
8
6
35
Strain, 0.001 in.lin.
Mg.078 HM31 A magnesium alloy extrusion, tensile stress-strain curves at various temperatures
400
350
300
/
250
Il..
:2 ui 200
'"~
V
ro
150
100
50
~
/
l&
Source: Properties and Selection: Nonferrous Alloys and Pure Me/als, Vol 2, Metals Handbook, American Society for Metals, 1979, p 566
149 'C (300 'F)260 'C \500 °Fí - 20 316 'C (600 'F)
~
371 'C
JI-
~700 'F) _
10
427 'C \800 'F)482 'C ~900 'F)
¡..---;o"
0.4
- 40
204 'C 1400 'F)
¡....-"7
0.2
Extrusion ratio of 25:1 approximate. 50.8 x 25.4 mm (2 x 1 in.) rectangles tested in the longitudinal direction. Composition: Mg-3Th-1.5Mn. UNS M13312
-
/ v-r
~ b.~
24 'C (75 'F)
- 50
0.6
0.8
Strain, %
1.0
1.2
o
1.4
Magnesium (Mg)/601
350
-
Mg.079 HM31A magnesium alloy extrusion, tensile stress-strain curves at various temperatures
50
Extrusion ratio of 67: 1 approximate. 9.525 x 50.8 mm (0.375 x 2 in.) rectangles tested in the longitudinal direction. Composition: Mg-3Th-1.5Mn. UNS M13312
300
- 40 250
f1.
200
'" ~
/
150
100
50
ji ~
l-----
24 'C (75 'F)-
Source: Properties and Selection: Nonferrous Alloys and Pure Metals, Vol 2, Metals Handbook, American Society for Metals, 1979, p 566
- 30
~
149 'C (300 'F)
/'
'"~
é'ií 204 'C (400 'F)1 '- 20 260 'C (500 'F) 1
Vi' ¡..--t
V ) l.--....
/
V
:2
~
I
316 'C (600 'F)
~
7
371 'C 1(700 'FL
/
10
'1'
427 'C (800 'F)
-/
I
482 'C 1(900 'F)
0.2
OA
0,6
0.8
1.0
1,2
Slrain, %
250
I,
-
35
-
30
-
25
Mg.080 HM31A magnesium alloy extrusion, compressive stress-strain curves at various temperatures
i
200
150 ro a.
24 'C (75 'F)
~r-¡1;-
'"~
é'ií
Source: Properties and Selection: Nonferrous Alloys and Pure Metals, Vol 2, Metals Handbook, American Society for Metals, 1979, p 566
~
:2
50
j~
v
0,2
- 20~
1
149 'C 1300 204 'C (400 260 'C (500 316 'C (600
i
100
~
'Fl 'F) 'F) 'F)
g
-
15
- 10
- 5
OA
Extrusion ratio of 25:1 approximate. 50.8 x 25.4 mm (2 x 1 in.) rectangles tested in the longitudinal direction. Composition: Mg-3Th-1.5Mn. UNS M13312
0.6
0,8
Slrain, %
1.0
1.2
o
1A
en
602/Magnesium (Mg)
Mg.081 HM31A magnesium alloy extrusion, compressive stress-strain curves at various temperatures
25or-----,-----,-----.-----,-----~----~----~
35
200~----~----+_----+_----4-----~----~----~
_-Ir--- 24 oC (75°F)
'"
I
150
25
Source: Properties and Selection: Nonferrous Alloys and Pure Metals, Vol 2, Metals Handbook, American Society for Metals, 1979, p 566
I
149°C (300°F)----+----l J-.-,f--¡- 204 oC (400°F)
20~ rñ
260 oC (500 °F) I 316 OC (600 °F)
15 1i5
I
Il.
:;; rñ en ~
1i5
Extrusion ratio of 67: 1 approximate. 9.525 x 50.8 mm (0.375 x 2 in.) rectangles tested in the longitudinal direction. Composition: Mg-3Th-1.5Mn. UNS M13312
30
100
~
10 50~_¿+-~----+_----+_----4_----~----~----~
5
°OL-----OL.2-----0~.4-----0~.6-----0~.8----~1.-0-----1.L2----~1.; Strain, %
40.------.------,------,------.------,------~
Mg.082 HM31A-F magnesium alloy extrusion, stressstrain curves at room and elevated temperatures
280
Extrusions up to 25.8 cm2 (4.0 in. 2) cross section tested in longitudinal direction. Composition: Mg-3Th-1.5Mn. UNS M13312
75°F (24 OC) 210
300°F (149 OC)
'"
Il.
:;; 140 en rñ ~
1i5
700°F (371°C) 70 800°F (427 OC) 900 °F (482 OC) 0.2
0.4
0.6 Strain, %
0.8
1.0
O
1.2
Source: "HM3IXA Magnesium Alloy Extrusions," Bulletin No. 141199, Dow Chemical Co. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3505, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 4
Magnesium (Mg)/603
Mg.083 HM31A-F magnesium alloy extrusion, compressive stress-strain curves at room and elevated temperatures
30 ,------.--------,---------,--------,210 75°F (24 OC) 25 I------+-------t-~""""'--_t_----_j 175
Extrusions up to 25.8 cm2 (4.0 in. 2) cross section tested in longitudinal direction. Composition: Mg-3Th-l.5Mn. UNS M13312
20
Source: "Magnesiurn in Design;' Form No. 141-213-67. Dow Chernical Co., 1967. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3505, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 6
140
&.
~
:2
<ñ In 15
~---------h~L,~·--~----~__~~----------1105 ~
~
~
UJ ~-----~~~~------~-------_r--------l70
1---.~~---_t_--------~----------+_---------j35
L---------L-----·--~--------~--------~O
0.8
Strain, %
80
560
Mg.084 HM31A-F magnesium alloy extrusion, complete stress-strain curves at low temperatures
490
Tested in longitudinal direction. Composition: Mg-3Th1.5Mn. UNS M13312
420
Source: R.P. Reed, R.P. Mikesell, and R.L. Greeson, "Sorne Mechanical Properties of Magnesiurn Alloys at Low Ternperatures," ASTM STP 287, 1961, p 61-73. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3505, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 5
./ 1240F (-253 OC)
70
V~
60
/ -1---
50
-323°F (-197 OC)
-109°F (-78 OC) 350
V
o-
V---
30
_ 80°F (27 OC)
:2 280 In<ñ
~
210
20
140
10
70
o
O
5
10 Strain,
15 %
604/Magnesium (Mg)
24
20
Mg.085 HM31A-F magnesium alloy extrusion, isochronous stress-strain curves at 149 oC (300°F)
168
I
15 s 1 min
~ V
10 h
Solid extrusions up to 25.8 cm2 (4.0 in. 2) cross section, exposed to elevated temperature for 3 h prior to loading. Composition: Mg-3Th-1.5Mn. UNS M13312
140
112
16
ro
o..
Source: "HM31XA MagnesiumAlloy Extrusions," Bulletin No. 141199, Dow Chemical Co. As pub1ishect in Aerospace Structural Metals Handbook, Vol 3, Code 3505, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 8
:2 84 rñ (/) ~
üí 8
56
4
28
0.8
24
2.4
15 s 1 min 10 h
/'"
I
o
3.2
168
I
20
16
1.6 Strain. %
~
I
140
Solid extrusions up to 25.8 cm2 (4.0 in. 2 ) cross section, exposed to elevated temperature for 3 h prior to loading. Composition: Mg-3Th-1.5Mn. UNS M13312
112
Source: "HM31XA MagnesiumA110y Extrusions," Bulletin No. 141199, Dow Chemical Co. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3505, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 8
8:.
:2 84 rñ (/)
~ 8
56
4
28
0.8
1.6 Strain. %
2.4
Mg.086 HM31A-F magnesium alloy extrusion, isochronous stress-strain curves at 204 oC (400°F)
o
3.2
Magnesium (Mg)/605
24.---------r---------.----------r--------~168
20~--i/--~~========~========~15S------~140 I ff. I
1 min
~-=-+-------+-------1 r~ min
16~_1~~~~t=====~=1~=-~---t10h,------~112
~12
84~
V
~'71 4
Mg.087 HM31 A-F magnesium alloy extrusion, isochronous stress-strain curves at 260 oC (500 °F) Solid extrusions up to 25.8 cm 2 (4.0 in. 2) cross section, exposedto elevated temperature for 3 h prior to loading. Composition: Mg-3Th-1.5Mn. UNS M13312 Source: "HM31XA MagnesiumAlloy Extrusions," Bulletin No. 141199, Dow Chemical Co. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3505, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 8
56~ a
I
°OL--------~--------~----------L-------~O
0.8
1.6
2.4
3.2
Strain, %
20
140
I
16
12 "¡¡; -'" rñ Ul
~
Ci.í
8
I~
~
~
V-
¡..--
-
15 s
~
¡..~
~
--
112 1 min 10 min 30 min 2h 5h 10 h
84
56
~
28
4
0.8
1.6 Strain, %
2.4
o
3.2
Mg.088 HM31A-F magnesium alloy extrusion, isochronous stress-strain curves at 316 oC (600 °F) Solid extrusions up to 25.8 cm2 (4.0 in. 2) cross section, exposed to elevated temperature for 3 h prior to loading. Composition: Mg-3Th-1.5Mn. UNS M13312 Source: "HM31XA Magnesium Alloy Extrusions," Bulletin No. 141199, Dow Chemical Co. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3505, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 8
606/Magnesium (Mg)
24
168
20
140
I
r
16
4
25.4 cm (10 in.) OD x 8 mm (0.315 in.) wall. Short-time tests after 5 s exposure to test temperature plior to loading. Composition: Mg-3Th-1.5Mn. UNS M13312
5s 10 s 112
I I I
8
Mg.089 HM31A-F magnesium alloy extruded tubing, isochronous stress-strain curves at 260 oC (500°F)
ro
a.
Source: "HM31XA Magnesium Alloy Extrusions," Bulletin No. 141199, Dow Chemical Co. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3505, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 9
:2 84 rñ UJ ~
i'i5 56
28
1/ 0.8
1.6 Strain, %
2.4
o
3.2
24
168
20
140
Mg.090 HM31A-F magnesium alloy extruded tubing, isochronous stress-strain curves at 316 oC (600°F)
25.4 cm (lO in.) OD x 8 mm (0.315 in.) wall. Short-time tests after 5 s exposure to test temperature plior to loading. Composition: Mg-3Th-1.5Mn. UNS M13312
30 s 16
112
10 min
ro
.¡¡; -'"
a.
:2 84 rñ UJ
gf 12 ~
~
i'i5
i'i5 8
56
4
28
00
0.8
1.6 Strain, %
2.4
O 3.2
Source: "HM31XA Magnesium Alloy Extrusions," Bulletin No. 141199, Dow Chemical Co. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3505, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 9
Magnesium (Mg)/607
Mg.091 HM31A-T5 magnesium alloy extrusion, stress-strain curves at room and elevated temperatures
350
50 70°F 21 OC) 40
280
30
210
~
Extrusions up to 25.8 cm2 (4.0 in. 2 ) cross section tested in longitudinal direction. Composition: Mg-3Th-l.5Mn. UNS M13312
&.
::E
,¡¡
,¡¡
'"~
'"
(jj
20
500°F (260 OC)
140
600 °F (316 OC) 700°F (371°C) 10
800°F (427 OC)
70
ooL------o.~2----~O.-4--·---0~.-6-----0~.8------1~.O----~1.f
Strain, %
~
Source: "Magnesium in Design," Forro No. 141-213-67, Dow Chemical Co., 1967. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3505, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 4
608/Magnesium (Mg)
30
210
Mg.092 HM31A-T5 magnesium alloy extrusion, compressive stress-strain curves at room and elevated temperatures
175
Top curves for extrusions with cross section less than 6.45 cm2 (1 in. 2). Bottom for extrusions with cross section 6.45-25.8 cm2 (1-4 in. 2). Tested in longitudinal direction. Composition: Mg-3Th-1.5Mn. UNS M13312
70°F (21°C)
I
300°F (149 OC)
25
I
400°F (204 OC)
I
20
500°F (260 OC)
140
I
600°F (316 OC)
'c;;
""
'" U5 U)
~
ro
o.. :::¡; 15
105 '" U) ~
U5 10
70 800°F (427 OC) 35
o
O
30
210
25
175
20
140
ro
'c;;
""rñ U)
~
o.. :::¡; 15
105 '" U) ~
(f)
U5 10
70 800°F (427 OC) 35
~------L-------~------~-------L------~o
0.2
004
0.6
Strain, %
0.8
1.0
Source: "Magnesium in Design," Form No. 141-213-67, Dow Chemical Co., 1967. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3505, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 6
Magnesium (Mg)/609
18
126
15
105
12
84
Mg.093 HZ32A-T5 magnesium alloy sand cast bar, tensile stress-strain curves at various temperatures Composition: Mg-3.2Th-2.1Zn-O.7Zr. UNS M13320
'"
o...
'iij
-'"
ui In
~
Source: "Design," Booklet by Magnesium Elektron Ltd. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3408, CINDAS/ USAF CRDA Handbooks Operation, Purdue University, 1995, p 3
:2
63 ui In
9
~
ro 42
6
~~----+-------~-------~-------r------~21
0.2
0.6
0.4
0.8
Strain, %
140
-
20
-
18
-
16
-
14
120
100
'"
o...
:2 ui In
80
.91
':?! 60 ~
40
20
/
tp
12 ~
-
10
1il
-
8
.91 'iij <=
ui In
~~
(1)
10 h
p-
6
f il
- 4 -
0.4
0.8
Specimens exposed to elevated temperature for 3 h before loading. Composition: Mg-3.2Th-2.1Zn-O.7Zr. UNS M13320
-
2 min
-:::::
~
Mg.094 HZ32A-T5 magnesium alloy separately sand cast test bar, isochronous tensile stress-strain curves at 204 oC (400°F)
1.2
1.6
Strain, %
2.0
2.4
2
~
Source: Properties and Selection: Nonferrous Alloys and Pure Metals, Vol 2, Metals Handbook, American Society for Metals, 1979, p 585
610/Magnesium (Mg)
32
Mg.095 QE22A-T6 magnesium alloy sand casting, stress-strain curves at room and elevated temperatures
r-------r-------,-------,--------,------~224
28
Composition: Mg-2.5Ag-2.0Di-OAZr. Didymium is a natural mixture of rare-earth elements neodymium and praseodymium given the quasi-chemical symbol Di. UNS M18220
24
20 ro
·00 -'" ui"
a.
482°F (250 oC)
en 16
:2
~------~~F_--~,_=---+_------~------~112
~
ui"
Source: "Design," Booklet by Magnesium Elektron Ltd. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3406, CINDAS! USAF CRDA Handbooks Operation, Purdue University, 1995, p 4
en ~
Cñ 12
8
4
O L-------~------~------~------~------~O 0.2 0.4 0.6 0.8 1.0 O Strain, %
Mg.096 QE22A-T6 magnesium alloy casting, typical stress-strain curves at room and elevated temperatures
50r------,-----,------,------,------,-----~350
~----~----~------+_----_+------~~--~280
210
ro
a.
·00 -'" ui"
:2
en
ui"
Cñ
~ 140
en
~
~--~~~~~------+_----_+------+_----~70
~-----2L-----~----~------~----~----~ll
Strain, 0.001 in./in.
RT, room temperature. Specimens exposed to elevated temperatures for 0.5 h. Ramberg-Osgood parameters: n(RT) = 6.5, n(300 °P [or 149 OC]) = 7.9, n(400 0p [or 204 OC]) = 9.0, n(600 0p [or 314 OC]) = 4.8, n(700 0p [or 371°C]) = 3.9. Composition: Mg-2.5Ag-2.0Di-OAZr. Didymium is a natural mixture of rare-earth elements neodymium and praseodymium given the quasi-chemical symbol Di. UNS M18220 Source: MIL-HDBK-5H, Dec 1998, p 4-47
Magnesium (Mg)/611
Mg.097 QE22A-T6 magnesium alloy sand cast test bar, effect of temperature on tensile properties
Temperature, oc
-129
-240 60
50
---
-18
~
O-
-" ui
~
30
'"~
204
316
427 420
F tu' ultimate tensile strength; F ty ' tensile yield strength.
40 .¡¡;
93
~ ~
éií
"~u ~
280
o..'"
::2
......
20
210
~
140
~
70
o
o 120
E E
80
----
.~
.,
N
.
§ 40
~
....-~
Cl
'"
o ¡¡:¡
~oo
-200
o
200 Temperature, °F
V
400
/
ui
~
éií
~~
10
é
Composition: Mg-2.5Ag-2.0Di-0.4Zr. Didymium is a natural mixture of rare-earth elements neodymium and praseodymium given the quasi-chemical symbol Di. UNS M18220
350
V 600
800
Source: J.B. Hallowell and H.R. Ogden, "An Introduction to Magnesium Alloys," DMIC Report 206, Battelle Memorial Institute, 1964. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3406, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 4
612/Magnesium (Mg)
~ 120r---------,---------~----------r_--------, el
r:::
~
100~--------~--------_1----------+_--------~
Composition: Mg-2.5Ag-2.0Di-0.4Zr. Didyrnium is a natural mixture of rare-earth elements neodymium and praseodyrnium given the quasi-chemical symbol Di. UNS Ml8220
80~--------~----~~~~~~-L--~--------~
Source: "Crucible Melting of Magnesiurn Alloys," Bulletin No. 181-27, Oow Chemical Co. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3406, CINOAS/USAF CROA Handbooks Operation, Purdue University, 1995, p 4
..!!1 '0;
r:::
2
~
E
~
ro
:5""
572 °F (300 OC)
'O Ql
el
l'l r:::
~
~
60L---------~--------~----------~--------~
120
! o
'#.
100
~
e..r::: o, r:::
~
80
"C
Qi ';;'
..!!1 '0;
r:::
~ ~
Mg.098 QE22A-T6 magnesium alloy sand cast bar, effect of overaging on tensile properties
60
'O
\~ ¿~
~ ~
""
~82OF(2500C)
¿~ t--
----
572 °F (300 'C)
Ql
el
~ 40 ~ Ql
a.
20 0.1
10 Time, h
10
10
Magnesium (Mg)/613
280
.¡¡;
::E
:i
'"~
~ 245
éi5
35
~~~-~~~--------~----------~--------~210
- - Chilled casting - - - - Unchilled casting 25L---------~------·--~----------~--------~175
20r----------r------·--~----------,_--------_,
E E
.~ 10f~~~::~----~=-~~====::::t=======~ ..: -~1-_
.ª
~
" ~
III
a.
-'"
N
F lu ' ultimate tensile strength; F ly ' tensile yield strength. Effect of casting process is shown. Composition: Mg2.5Ag-2.0Di-0.4Zr. Didyrnium is a natural mixture of rare-earth elements neodymium and praseodymium given the quasi-chernical symbol Di. UNS M18220
315
45
*
Mg.099 QE22A-18 magnesium alloy sand cast, effect of cold work on tensile properties
350
50
__
----
-------
°oL----------2~--------~4~--------~6--------~8 Reduction, %
Source: B. Lagowski and J.W. Meier, Effect of Cold Work on Tensile Properties ofMagnesium Alloys, AFS Trans., Vol 76, 1968, p 174-182 . As published in Aerospace Structural Metals Handbook, Vol 3, Code 3406, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, P 4
614/Magnesium (Mg)
35
30
~
/
25
~
W
~
-¡¡; 20 -'"
"' en
~
1ií
15
10
5
/
/ V
F I
Mg.100 lE10A-H24, lE10A-O magnesium alloy sheet, tensile stress-strain curves
245
Curves generated with a strain rate of 0,005/min. Solid line curves for 1.0 mm (0.040 in.) thick sheet and dashed line curves for 3.18 mm (0.125 in.) thick sheet. Composition: Mg-IZn-0.2RE. UNS Ml6100
210
175
=--=
v
140
&. :2
105
~
1ií
70
35
4
2
6 8 Strain, 0.001 in./in.
10
o
12
Mg.101 lE10A-H24, lE10A-O magnesium alloy sheet, compressive stress-strain curves
210
-¿-- ---
-r
/
25
20
lr
.¡¡; -'"
"' 1ií
en 15 ~
10
/
/
Source: "Stress-Strain Curve for ZE lOA (Sheet)," Dow Chemical Co., 1959. As published in Aerospace Structural Metals Handbook, Vo13, Code 3602, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 2
¡i
30
5
.
/
175
V
140
~-
.
--
&.
¡-
O
:2 105 "' en
~
/
70
35
2
Curves generated with a strain rate of 0.005/min. Solid line curves for 1.0 mm (0.040 in.) thick sheet and dashed line curves for 3.18 mm (0.125 in.) thick sheet. Composition: Mg-IZn-0.2RE. UNS M16100
H24
4
6 Strain, 0.001 in./in.
8
10
Source: "Stress-Strain Curve for ZE lOA (Sheet)," Dow Chemica1 Co., 1959. As pub1ished in Aerospace Structural Metals Handbook, Vol 3, Code 3602, CINDAS/USAF CROA Handbooks Operation, Purdue University, 1995, p 2
Magnesium (Mg)/615
Mg.l02 ZE41 A-T5 magnesium alloy sand casting, typical tensile stress-strain curves at room and elevated temperatures
25r------,------,------,-----~------,-----~175
RT, room temperature. Specimens exposed to elevated temperatures for 0.5 h. Ramberg-Osgood parameters: n(RT) = 3.6, n(212 °P [or 100 OC)) = 3.4, n(302 0p [or 150 OC]) = 3.1, n(392 0p [or 200 OC]) = 2.9. Composition: Mg-4Zn-lRE-0.7Zr. UNS M16410
20~-----~-----4----~~----_+--~--+_----_i140
105
.¡¡;
ca
a.
:;¡;
"'rñ"
Source: MIL-HDBK-5H, Dec 1998, p 4-52
rñ en
en ~
éií 70
~
r-~L-_r----~------~----_+------+_----_;35
L------L----~------~----~------~----_JO
2
4
8
6
10
12
Strain, 0.001 in.lin.
Mg.l03 ZE41 A-T5 magnesium alloy separately sand cast test bar, tensile stress-strain curves at room and elevated temperatures
200r-----,----~-----,-----,-----r----,-----,
25
Composition: Mg-4Zn-lRE-0.7Zr. UNS MI64lO 149 oC (300°F) ca
a.
~
204 oC (400°F)
:;¡; rñ en
15
g
en ~ .¡¡;
Source: Properties and Selection: Nonferrous Alloys and Pure Metals, Vo12, Metals Handbook, American Society for Meta1s, 1979, p 591
20
260 oC (500°F)
rñ en
gen ~ .¡¡;
c:
c:
¡.'!!
316 oC (600°F)
¡.'!!
10
5
~--~~--~----~~---L-----L----~--~O
0.2
0.4
0.6
0.8
Strain, %
1.0
1.2
1.4
616/Magnesium (Mg)
25
o
14
\
20
.¡¡;
V
V\
rñ
'"~
éií
5
140
1\/
-'"
Mg.l04 ZE41 A-T5 magnesium alloy sand casting, typical compressive stress-strain and tangent modulus curves at room temperature
70
Rarnberg-Osgood pararneter: n(compression) = 3.7. Composition: Mg-4Zn-lRE-O.7Zr. UNS Ml64lO
\
15
10
Compressive tangent modulus, GPa 28 42 56
J
105
/
rñ
'"~
'"
70
1\ I 2
ro
[L
:2
\
/
Source: MIL-HDBK-5H, Dec 1998, p 4-52
4
8 10 6 Strain, 0.001 in./in. 6 Compressive tangent modulus, 10 psi
éií
35
o
12
30
210
Mg.l05 ZH62A-T5 magnesium alloy sand casting, complete tensile stress-strain curves at various temperatures
25
175
Strain rate: O.03/min. Composition: Mg-5.7Zn-1.5ThO.7Zr. UNS M16620
20
140 ro
.¡¡;
[L
-'"
:2
rñ 15
105 rñ
'" ~
'"~
éií 70
10
5~~----+-----~~-=----~------~~----~35
~------L3------~6------~9------~12~----~1~ Strain, %
Source: H.E. Dedman, EJ. Wheelahan, and J.R. Kattus, "Tensile Properties of Aircraft Structural Metals at Various Rates of Loading after Rapid Heating," WADC Technical Report 58-440, Part 1, AS TIA Doc. No. 206074, 1958. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3407, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 3
Magnesium (Mg)/617
40
V~
v
30 ·00 -"'-
rñ
'" ~ (J)
/
20
10
Mg.106 ZK60A-T5 magnesium alloy extrusion, typical tensile stress-strain curves at room temperature
350
50
J
~
.---
Ramberg-Osgood parameter: n(room temperature) Composition: Mg-5.5Zn-0.5Zr. UNS M16600
280
= 7.0.
Source: MIL-HDBK-5H, Dec 1998, p 4-23
/
210
D..
::;¡; rñ
'"~
140
V
éií
70
V
4
2
10
8
6 Strain, 0.001 in./in.
50
1 .1 <2 in~ (12.9 cm') 2-,3 in~ (12.9-19.~ cm')k-:;:::p::
I 1--
45
3-5
in~ (19.1~~¡;"--
""""
35
Ií
30
2-40 in~ (12.9-258 cm')
210
15
::;¡; 175 rñ
'"
ST
105
If' I
10
/
70
/
35
0.2
0.4
0.6
0.8
D..
}F ~ 5-40 in~ (32.2-258 cm') 140 éií
:
LT
Test direction: L, longitudinal; LT, long transverse; ST, short transverse. Curves for extrusions in different conditions, orientations, and section sizes. Composition: Mg-5.5Zn-0.5Zr. UNS M16600
280
245
V
-, --1/ //
315
-1
1/
20
5
~
r-
¡>"F(L)
<2 in~ (12.9 cm')
1
T5(L)
40
Mg.107 ZK60A-F, -T5 magnesium alloy extrusion, compressive stress-strain curves at room temperature
350
1.0 Strain, %
1.2
1.4
1.6
1.8
o
2.0
Source: "Magnesium in Design," Form No. 141-213-67, Dow Chemical Co., 1967. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3506, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 4
618/Magnesium (Mg)
Mg.l08 ZK60A-T5 magnesium alloy extrusion, effect of temperature on tensile properties
Temperature. oC
70
60
-240
-129
-18
93
204
~ • ¡-......
-...... ~
Test direction: longitudinal. F tu ' ultimate tensile strength; 420
~
~
50
'00 40
1\
1\\
~
iií 30
20
liu
280
¡i ~
140
~
70
o
40
r
.S:: 20
'".1:
/~
e
O
10
O
o
/
-400
-200
o
Temperature. °F
/
v" 200
~
210 iií
o
~e
Source: "Magnesium in Design," Form No. 141-213-67, Dow Chemical Co., 1967. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3506, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 8 :2
~~
10
¡¡¡
UNS M16600
350
liy\ ~ ~
-" uf
F ty , tensile yield strength. Composition: Mg-5.5Zn-O.5Zr.
400
600
Magnesium (Mg)/619
Mg.l09 ZK60A-T5 magnesium alloy extrusion, stress-strain curves at room and low temperatures
1oor------,------,-----~------_r------r_----_,700
Composition: Mg-5.5Zn-O.5Zr. UNS M16600 80~-----~------+-- ---~------~----_b----__1560
ro
Source: R.L. McOee, l.E. Campbell, R.L. Carlson, and O.K. Manning, "The Mechanical Properties of Certain Aircraft Structural Metals at Very Low Temperatures," Battelle Memorial Institute, WADC TR58386,1958. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3506, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 8
a.
:::E
gf ~
~-----~----~------~~~-4~~~+---~~28000
~-----+~~~+-----~------~------~-----1140
2
4
6 8 Strain, 0.001 in.lin.
10
260 420
Mg.ll0 ZK60A-T5 magnesium alloy extrusion, effect of elevated temperature on tensile properties
350
Test direction: longitudinal. Ftu' ultimate tensile strength; Fty, tensile yield strength. Composition: Mg-5.5Zn-O.5Zr. UNS M16600
280
Source: "Magnesium in Design," Porm No. 141-213-67, Dow Chemical Co., 1967. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3506, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 8
Temperature, 'C
-18 60
38
93
149
204
50
40
ro
a.
'iii
'"rñrn ~
:::E
210 gf
30
~
00 20
140 Expos~re
10
?ft.
•
70
10 min - . - - 1000 h
O
O
E100 E
~
.5 ~ 50 c:
o
~
'"c:
o üJ
O O
100
200
300
Temperature, 'F
400
500
620/Magnesium (Mg)
40
Source: MIL-HDBK-5H, Dec 1998, p 4--23
/
30
210
1/
cñ en
20
I
10
cñ en ~
140
V
4
2
.......
35
.. 1 I I/./
30
~ %,/ ¡...
1--__
~ :;::;;;
J~-:'~ ~
If~
/~
in~
245
3-5 in~ (19.4-32.2 cm') (L) 7! f--
Test direction: L, longitudinal; LT, long transverse; ST, short transverse. Curves for extrusions in different conditions, orientations, and section sizes. Composition: Mg-5.5Zn-0.5Zr. UNS M16600
210
1---
-
f--
b:::.-
175
5-40 in' (32.2-258 cm') (L)
5-40 (32.2J58 cm!) (LT) 5-40 in~ (32.2-258 cm') (ST)
'" ::;; a.
140 cñ en
~
(f)
105
/
70
/
--T5 --F 35
1/ 0.4
Mg.112 ZK60A-F, ZK60A-T5 magnesium alloy extrusion, compressive stress-strain curves at room temperature
280
1
l' l0' (12.!.-19.",,,,, (L<:-
",-
/'
12
~<2 i~~ (12.~ cm,)(L)
¡..-L~ 1--.~:
25
o
10
6 8 Strain, 0.001 in./in.
40
0.2
1ií
70
V
15
'"
a.
::;;
/
~
1ií
5
Tested in longitudinal direction. Extrusions with crosssectional area les s than 12.90 cm2 ( 2.000 in. 2). Composition: Mg-5.5Zn-0.5Zr. UNS M16600
280
~
10
Mg.lll ZK60A-T5 magnesium alloy extrusion, compressive stress-strain curve at room temperature
350
50
0.6
0.8
1.0 1.2 Strain, %
1.4
1.6
1.8
o
2.0
Source: "Magnesium in Design," Form No. 141-213-67, Dow Chemical Co., 1967. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3506, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 6
Magnesium (Mg)/621
35 30
~
---::::::
245
~
\....-.::::-.,
!I)
~
Test direction: longitudinal. Composition: Mg-5.5ZnO.5Zr. UNS M16600
-..,
210 ~
25
175
20
140
15
105
'"
·00
"'
Mg.113 ZK60A-T5 magnesium alloy extrusion, effect of elevated temperature on compressive yield strength at room temperature
280
40
c..
Source: "Magnesium in Design." Form No. 141-213-67, Dow Chemical Co., 1967. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3506, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 6
::¡;
(f)
~
Exposure
• 200°F (93 OC) 300°F (149 0C)- 70 "'" 400°F (204 OC) o 500 °F (260 OC) 35
10
•
5
10
30 20 Strain, 0.001 in./in.
40
,----,---,-----¡-----.,----.,------,
1----+--+-+---__"""-I----+---=..-J.2 min
Mg.114 ZK60A-T5 magnesium alloy forging, isochronous stress-strain curves at 149 oC (300°F)
140
Axial specimens from aircraft wheel rimo Composition: Mg-5.5Zn-0.5Zr. UNS M16600
112
Source: "Magnesium in Design," Form No. 141-213-67, Dow Chemical Co., 1967. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3506, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 10
1h
·00
84
'"
c..
"'
::¡;
~
!I)
!I)
~
(f)
56
8
°0~---0~.4---0~.8--·--1~.2---~1.-6---2.LO--~2.;
Strain, %
é'ií
622/Magnesium (Mg)
Axial specimens from aircraft wheel riro. Composition: Mg-S.SZn-O.5Zr. UNS M16600
112
16
.¡¡;
Mg.115 ZK60A-T5 magnesium alloy forging, isochronous stress-strain curves at 204 oC (400°F)
140
20
30 s
12
Source: "Magnesium in Designo" Fonn No. 141-213-67. Dow Chemical Co., 1967. As pub1ished in Aerospace Structural Metals Handbook, Vol 3, Code 3506, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 10 84
tU
o..
-'" tfj
:2
2 min
U)
tfj U)
~
5min
i'ií
56
8
-+----t---i
~
5h
1_ _ _ _
~----~-----L----~------~----~----~O
2.4
1.2 Strain, %
0.8
140
20
16
112
12
84
Axial specimens from aircraft wheel rimo Composition: Mg-S.5Zn-O.SZr. UNS M16600 Source: "Magnesium in Design," Fonn No. 141-213-67, Dow Chernica1 CO., 1967. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3506, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 10
~ tfj U)
~
56
8 ~5
4
Mg.116 ZK60A-T5 magnesium alloy forging, isochronous stress-strain curves at 260 oC (500°F)
/
s
V -~
I~
V
~
~
~
1----
)----
0.8
1.2 Strain, %
2 min
28
15 min 1h
..-
0.4
-
30 s
1.6
2.0
o
2.4
Magnesium (Mg)/623
40
35
30
25
/
V
10
245
Forged at 316 oC (600°F) from extruded material. Composition: Mg-5.5Zn-0.5Zr. UNS M16600
210
Source: Properties of Magnesium and Magnesium Alloys, Properties and Selection of Metals, Vol 1, 8thed., Metals Handbook, American Society for Metals, 1961, p 1095-1112. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3506, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 7
175
o.. '"
/ ....rIV /!V-
15
Mg.117 ZK60A-T5 magnesium alloy forging, stressstrain curves at room and elevated temperatures
75°F (24 OC)
V
~
/
280
~
-
:2 140 ,,;
~
300°F (149 OC) 105
400°F (204 °C)_ 70
!,t---
5
35
~/
500 °F (~60 OC) 600°F (3 16 'C) 1
0.2
0.6 0.8 Strain, %
0.4
1.0
1.2
40
35
V /
30
o
300 "F (149 OC)
k---""
/// '
15
IV/' V
/J v;::,
.0
Mg.118 ZK60A-T6 magnesium alloy forging, stressstrain curves at room and elevated temperatures
245
Forged at 316 oC (600°F) from extruded material. Composition: Mg-5.5Zn-0.5Zr. UNS M16600
210
Source: Properties of Magnesium and Magnesium Alloys, Properties and Selection of Metals, Vol 1, 8th ed., Metals Handbook, American Society for Metals, 1961, P 1095-1112. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3506, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 7
175
/
5
V
280 75°F (24 OC)
/
25
10
v
o
1.4
o.. '"
:2 140 ,,;
E
CI)
~
400°F (204 °C)- 105
70
I
500°F (260 OC) ~
600°F
~
0.2
0.4
0.6 0.8 Strain, %
1.0
6 OC)
1.2
35
o
1.4
624/Magnesium (Mg)
40
35
30
/
25
/
5
j) ~
V
--r--
/
--
--
/1 I V/ V V
15
10
/
75 'F (24 'C)
-
ro
140 ui
~
400°F (204 °C)- 105
70
1
1
0.4
0.6 0.8 Strain, %
1.0
35
1.2
/ /'
.¡¡; -'"
enen 20
//
~
V/ V
--
./""
r--
¡--
-
280
Mg.120 ZK60A-T6 magnesium alloy forging, stressstrain curves at room and elevated temperatures
245
Forged at 427 oC (800°F) from cast material. Composition: Mg-5.5Zn-0.5Zr. UNS M16600
210
Source: Properties of Magnesium and Magnesium Alloys, Properties and Selection of Metals, Vol 1, 8th ed., Metals Handbook, American Society for Metals, 1961, p 1095-1112. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3506, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 7
175 300°F (149 OC)
ro
a. :::?E
140 ui
~
(f)
400°F (204 'C)
~
105
70 500°F (2 60 'C)
-r-
0.4
(1
1
600°F
~ 0.2
o
1.4
75°F (24 OC)
V
/
25
V
Source: Properties of.Magnesium and Magnesium Alloys, Properties and Selection of Metals, Vol 1, 8th ed., Metals Handbook, American Society for Metals, 1961, p 1095-1112. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3506, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 7
:::?E
600°F (3 16 OC)
/'
jj
210
---'
30
5
Forged at 427 oC (800°F) from cast material. Composition: Mg-5.5Zn-0.5Zr. UNS M16600
500°F (2 60 'C)
35
/
245
a.
40
10
Mg.119 ZK60A-T5 magnesium alloy forging, stressstrain curves at room and elevated temperatures
300 'F (149 0C)- 175
r""'"
0.2
15
280
0.6 0.8 Strain, %
1.0
16 OC)
1.2
35
o
1.4
Magnesium (Mg)/625
Mg.121 ZK60A-T5, ZK60A-T6 magnesium alloy forging, effect of temperature on tensile properties
Temperature, 'C 501r8~__~~38~______9T3________ 14r9_______2,0_4______-,26~50
"
Longitudinal specimens. Composition: Mg-5 .5Zn-O.5Zr. UNS M16600 Source: "Magnesium in Design," Form No. 141-213-67, Dow Chemica1 Co., 1967. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3506, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 8
4or----,.-~~~~----------r_------~------~280
.¡¡;
210
30
ui 11)
ui
~ CI)
1/)
~
140
20
10~------~-------+--------~------~-------470
OL--------L-------L--------L--------L------~O
~100r-------.--------r--------r_------._------__,
E E
é .~ N
50r-------~------~~------r-------~--------
.E e o
~
O>
e
o
m
ro
a. ::¡;
.><
0oL-----~-L------_L--------L--------L------~
100
200
300
Temperature, 'F
400
500
CI)
626/Magnesium (Mg)
280
Mg.122 ZK60A-T5, ZK60A-T6 magnesium alloy rolliorged rings, effect oi rolling reduction and orientation on compressive yield strength
35
245
Top: T5; bottom: T6. Roll forged rings produced directly from cast blanks. Composition: Mg-5.5Zn-0.5Zr. UNS M16600
._ 30
210
40 •
Tang~ntial
'" Axial • Radial
~
00
(1)
IJ..
::a;
25
...-
~
~
~
~
175 00
...., 20
140
15
105
40
280
35
~
I
30
/~
.---------
~
245
210
ro IJ..
::a;
00 25
t--
---=
--
175
140
20
20
30
40 Rolling reduction, %
50
60
105 70
! U)
Source: "Magnesium RolIed Rings," Code 0.4 JFPIHB, Dow Chemical Co., 1964. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3506, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 6
Magnesium (Mg)/627
Mg.123 ZK60A-T6 magnesium alloy forging, isochronous stress-strain curves at 149 oC (300°F)
28 .----,---.----,----,.----,----,----,196
24
Axial specimens from aircraft wheel rims. Composition: Mg-5.5Zn-O.5Zr. UNS M16600
20
Source: "Magnesium in Design," Form No. 141-213-67, Dow Chemical Co., 1967. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3506, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 10
----'_-- 30 min .¡¡; -'" rii m
16 r---Jhtr~~~------~-=~~--2h~-----r----~112
~
:2
10 h ~ é'ií 12 ~~~~~--~~~+_----~-----r----_r----~M
gf
~
8 ~~~r-----+_----+-----~-----r-----r----~56
4 Hm~--r-----+_----+_----~----_r----_r----_;28
°OL-----~-----~----~----~----~-----L-----JO
0.4
0.8
1.2
1.6
2.0
2.4
2.8
Strain, %
Mg.124 ZK60A-T6 magnesium alloy forging, isochronous stress-strain curves at 204 oC (400°F)
28r----,r-----,------,-----,-----,-----,----~
196
24~----+-------+_----+_----~----_r----_r----_;
168
Axial specimens from aircraft wheel rims. Composition: Mg-5.5Zn-O.5Zr. UNS M16600
20~----+-------+_----+_----~----_r----_r----_;
140
Source: "Magnesium in Design," Form No. 141-213-67, Dow Chemical Co., 1967. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3506, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p la
~ 16r-----+---~~----~--~~3~0~s----r-----t-----1
112
~
:2
rii
m
2 min
~
é'ií 121---ty
rii m
~ 84 en
56
28
°0L-----0".-4~---0~.8-----1~.2----~1.-6-----2.LO-----2L.4-----J2.~ Strain, %
628/Magnesium (Mg)
Mg.125 ZK60A-T6 magnesium alloy forging, isochronous stress-strain curves at 260 oC (500°F)
28
196
24
168
Axial specimens from aircraft wheel rims. Composition: Mg-5.5Zn-0.5Zr. UNS M16600
20
140
Source: "Magnesium in Design," Form No. 141-213-67, Dow Chemical Co., 1967. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3506, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 10
.¡¡; 16
112
-'"
'"~
ro
12
8
4
84 ..,./
v-
~5s
305 -2min 5 min 30min
r/;r-:::: ~ rr---I~
~
0.4
0.8
(~/)
56
28
2h 10 h
~
1.6 1.2 Strain, %
2.0
2.4
o
2.8
35r-------,-------,-------,-------,-------,
30~------1_------_+------~~~~~+_------~
25~------+_------~~~~~------_r~----~
.¡¡;
&. :2
ui
20 ~------1_--~~.,..¡.=------~r__
-'"
ui
~'" (/) 15 ~------__t__,'-------_+------~'-------+_------~
10~----~+_------+_------~------_r------~
5~~----+_------+_------~------_r------~35
L -______L -______~______~------~------~O
1.0 Strain, %
Mg.126 ZK61A-T5, ZK61A-T6 magnesium alloy sand cast test bar, stress-strain curves for various conditions
Composition: Mg-6Zn-O.8Zr. UNS M16600 Source: J.W. Meier and M.W. Martinson, Development of HighStrength Magnesium Casting Alloy ZK61, Trans. AFS, Vol 58, 1950, P 742-751. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3409, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 4
Magnesium (Mg)/629
Mg.127 ZK61A-T6 magnesium alloy sand cast test bar, effect of temperature on tensile properties
Temperature, 'C 501~8~______~3r8_________~93~_______1,4~9______--.20~50
F tu' ultimate tensile strength; F ty , tensile yield strength.
Composition: Mg-6Zn-08Zr. UNS M16600 Source: J.W. Meier, Characteristics of High-Strength Magnesium Casting Alloy ZK61, Trans. AFS, Vol 61, 1953, P 719-728. As published in Aerospace Structural Metals Handbook, Vol 3, Code 3409, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 4
40~---------~----~--~----------1---------~280
210 co a..
30 'iii -" ui
::¡; ui
CIl
CIl
~
~ 140
20
10~--------~-------~~-------4--------~70
o
O
E E ~
~
.S N
20
.S c:
~el c:
O
¡¡¡
00
100
200 Temperature, 'F
300
400
Nickel (Ni)/631
Nickel (Ni) 80
560
r---
60
/
v
/~
~
--
420
Ni.001 Ni 200 annealed nickel sheet, engineering stress-strain curve (full range)
Test direction: longitudinal. Sheet thickness = 0.787 mm (0.031 in.). Commercial1y pure nickel (UNS N02200). 0.2% yield strength = 185 MPa (26.9 ksi); ultimate tensile strength = 434 MPa (63.0 ksi); elongation = 39.5%; strength coefficient (K) = 138.2; strain-hardening exponent (n) = 0.387. Composition: Ni 99.0 min Courtesy of Special Metals Corporation
20
140
o
O
0.05
0.10
0.15 Strain
0.20
0.25
30
O 0.30
210
I
._ 20
g¡
V--
Ni.002 Ni 200 annealed nickel sheet, engineering stress-strain curve (expanded range)
Test direction: longitudinal. Sheet thickness = 0.787 mm (0.031 in.). Commercial1y pure nickel (UNS N02200). 0.2% yield strength = 180 MPa (26.1 ksi); ultimate tensile strength = 414 MPa (60.1 ksi); elongation = 39.0%. Composition: Ni 99.0 min Courtesy of Special Metals Corporation
rñ (J) ~
10 el
e
.~
ID
e
.5>
e W 10
I
o
O
2
4 Strain x 0.001
6
632/Nickel (Ni)
.l.rr=-
120
~
=-,,==-''' ¡.....--
..;.,:-~-:..
1 /
/
ro
c..
:::;: 560 oo rñ
V
~
280 137 ksi (945 MPa) - - - 130 ksi (896 MPa) _. _. _. 130 ksi (896 MPa)
I 0.2
0.4
I
I
0.6 0.8 Strain, %
1.0
1.2
o
1.4
Ni.004 8-1900 as-cast nickel alloy, stress-strain curves at room temperature
1120
160
120
,/
.-' -
. - .1.'
-'
-'-"
A
V-=- --- --,{ /1,
¡-rr
trI f--"J
ro
c.. :::;: 560 oo' oo ~
1ií
,1
V 0.2
25.4 mm (1 in.) gage length. Curves given for various ultimate strengths. Composition: Ni-10Co-8Cr-6Mo-6Al4Ta-1(Ti + C + Zr + B)
840
/{
40
Source: Pratt and Whitney Aircraft Communication to MPDC. As pub· lished in Aerospace Structural Metals Handbook, Vol 5, Code 4213, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 13
1ií
ji
I
25.4 mm (1 in.) gage length. Heat treatment: 1065 oC (1950 °P), 4 h, rapid air cooled + 899 oC (1650 °P), 10 h, air cooled. Curves given for various ultimate strengths. Composition: Ni-lOCo-8Cr-6Mo-6Al-4Ta-1(Ti + C + Zr+ B)
840
V
l
40
Ni.003 8-1900 as-cast and heat treated nickel alloy, stress-strain curves at room temperature
1120
160
280 139 ksi (958 MPa) - - - 136 ksi (938 MPa) - . - . - . 124 ksi (855 MPa)
I 0.4
I
0.6 0.8 Strain, %
I
1.0
1.2
o
1.4
Source: Pratt and Whitney Aircraft Communication to MPDC. As pub· lished in Aerospace Structural Metals Handbook, Vol 5, Code 4213, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 13
Nickel (Ni)/633
Ni.005 8-1900 as-cast nickel alloy, stress-strain curves at elevated temperature
1120
160 1
10J ksi (752 MPa), - . - . - . 110 ksi (758 MPa), .. 78 ksi (538 MPa), 27 ksi (186 MPa),
_.. _ _.. -
---
1100 °F 1400 °F 1800 °F 2000 °F
120
......
~
1649 OC) (760 OC) (982 OC) (1093 OC)
._0- .-.-.' l:.r
-'-"
40
!
J'
1
l 1 "'/,....
1/
.¡....---
0.2
.. .. .. ..",......
¡-.. - .. - ._'0_"
r" i
560 vi
~
r
en
280
V'
./
~/~ ~
Source: Aerospace Structural Metals Handbook, Vol 5, Code 4213, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 15 o.. ::¡;
-- "-"-"
1
840
V
/: "
1/
-- ....-- --
0.4
0.6
25.4 mm (1 in.) gage length. Curves given for various ultimate strengths and test temperatures. Composition: Ni-lOCo-8Cr-6Mo-6AI-4Ta-l(Ti + C + Zr + B)
0.8 Strain, %
1---
1.0
-- ~
1.2
1.4
o
1.6
634/Nickel (Ni)
Ni.006 Inco 713LC nickel alloy, true stress-strain flow curves in interrupted tests
500 450 400
\
350
'"
a. 300
~
250
~
200
Source: 1.P.A. Immarigeon and P.H. Floyd, Microstructural Instabilities During Superplastic Forging of a Nickel-Base Superalloy Compact, as published in Production to Near Net Shape Source Book, American Society for Metals, 1983, p 347
\
1\
~ U)
Effects of prestrain at 0.98/s (top) and 0.09/s (bottom) on flow curves at different strain rates (S-l) and 1050 oc. Composition: 74Ni-12Cr-6AI-4.5Mo
(\
'" ....
Q)
0.98/5
~
150
~
100 50
0.5
1.0
rr
10-2
1.4xW:
¡--
9.0x10 2.0
1.5
2.5
3.0
,1 _, 1.4x10_, 3.0x10_, 9.0x10 1.2
1.5
True strain
400
350
300
'" 250
a. ~
U)
~
,.......
I
"\
.~
200
1~
1ñ Q)
~
150
0.09/5
-
100
í 50
11"" 0.3
0.9
0.6 True strain
10-2
'1
Nickel (Ni)/635
700
80
560
60
420
50
350 ~
~ ui Ul
~
/ ./
(ji
'>,
~c.
al
a.
~ ~ 40
.~
Ni.007 Inconel 713C cast nickel alloy, compressive yield stress-strain curve at 1177 oC (2150 °F)
100
30
o
ü
20
l/~
10 0.1
/
:!2 CI)
'>,
210 ~
Source: D.R. Carnahan, D.S. Michlin, and V. DePierre, "Extrusion of Refractory Metals and Superalloys," AFML-TR-66-344, Dec 1966, p 137. As published in Aerospace Structural Metals Handbook, Vol 4, Code 4119, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 16
-~
~ = 28.88°·235
/
E
~
280 1ñ
Specimen diameter = 9.5 mm (0.375 in.). As cast in vacuum of 00-3 Hg). Held at temperature a minimum of 15 rnin before test. Composition: Ni-13Cr-6Al-4Mo-2Nb0.7Ti. UNS N07713
c.
~
ü
140
2
0.5
0.2
5
Strain rate, 0.1 s
80
70
V
/'
/'
/
V /
40
V
al
a. ~
420
0.01
0.02
0.05
~
i
l/
.l!1 .~
CI)
350
-;¡;
(¡j
E
5 280
V
la
490
O
,,/
30
Ni.008 Inconel 713C rolled and heat treated nickel alloy sheet, effect of strain rate on ultimate tensile strength at 1038 oC (1900 0F)
560
0.'1 0.2 0.5 Strain rate, in.lin.lmin
2
5
Rolled from 2.54-0.381 mm (0.10-0.015 in.). Heat treatment: 1177 oC (2150 °F), 40 h + 871°C (1600 °F), 24 h. Composition: Ni-13Cr-6Al-4Mo-2Nb-0.7Ti. UNS N07713 Source: H. Greenewald, Jr. and T.J. Riley, "Development of a NickelBase Alloy Sheet for High Temperature Applications," ASD-TDR-62869, Apri11963, P 86. As published in Aerospace Structural Metals Handbook, Vol 4, Code 4119, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 13
636/Nickel (Ni)
120
100
V
g¡
"'~
1ií g' 60 .~
~
~
./
._ 80 ui
Ni.009 Incoloy C276 annealed nickel alloy sheet, engineering stress-strain curve (full range)
840
/
700
560 ca o.. :;;
/
ui
Test direction: longitudinal. Sheet thickness = 1.067 mm (0.042 in.). 0.2% yield strength = 385 MPa (55.8 ksi); ultimate tensile strength = 839 MPa (121.7 ksi); elongation = 58.2%. Composition: 57.25Ni-15.5Cr-5.5 Fe-3.75W-2.5Co. UNS N10276 Courtesy of Special Metals Corporation
~
420
r1
~ c:
"55
(])
(])
c:
c:
'c,
'c, c: 280 UJ
c:
UJ 40
140
20
0.05
0.15
0.10
0.20
0.25
o
0.30
Strain
70
490
60
420
Ni.Ol0 Incoloy C276 annealed nickel alloy sheet, engineering stress-strain curve (expanded range)
/\.. 50
~ ui
~ 40
1ií Ol
c:
.~ 30 c:
'c, c:
W
20
10
350
/ / / /
ca
o.. :;; 280
gf ~
1ií Ol
c:
210 .~
c:
'c, c: UJ 140
70
/
2
4
6 Strain x 0.001
8
o
10
Test direction: longitudinal. Sheet thickness = 1.067 mm (0.042 in.). 0.2% yield strength = 372 MPa (53.9 ksi); ultimate tensile strength = 812 MPa (117.8 ksi); elongation = 55.8%. Composition: 57.25Ni-15.5Cr-5.5 Fe-3.75W-2.5Co. UNS N10276 Courtesy of Special Metals Corporation
Nickel (Ni)/637
Ni.011 Inconel 600 annealed nickel alloy sheet, engineering stress-strain curve (full range)
840
120
100
V
V
..- ~
Test direction: longitudinal. Sheet thickness =0.864 mm (0.034 in.). 0.2% yield strength = 332 MPa (48.1 ksi); ultimate tensile strength =747 MPa (l08.4 ksi); elongation = 37.5%. Composition: 72Ni-15.5Cr-8Fe. UNS N06600
700
/'
/
/
/
Courtesy of Special Metals Corporation
140
20
0.05
0.10
0.15 Strain
0.25
0.20
60
o
0.30
Ni.012 Inconel 600 annealed nickel alloy sheet, engineering stress-strain curve (expanded range)
420
r/
50
350
!--
._ 40
g¡ ¡¡f ~
1ií
g> 30
c:
.5> c:
20
10
¡:f ~
210 ~ c:
/
.~
UJ
280 ~ :2
"55
c: .5>
140
/
70
/
2
3
4 Strain x 0.001
5
6
7
c:
UJ
Test direction: longitudinal. Sheet thickness =0.864 mm (0.034 in.). 0.2% yield strength = 328 MPa (47.6 ksi); ultimate tensile strength = 721 MPa (104.5 ksi); elongation = 37.0%. Composition: 72Ni-15.5Cr-8Fe. UNS N06600 Courtesy of Special Metals Corporation
638/Nickel (Ni)
20
Ni.013 Inconel 600 annealed nickel alloy sheet, isochronous stress-strain curves at various temperatures
r-------------,-------------.-------------~140
1300 °F (704 OC) 16
~------------t-------------1-----~~~~~112
Sheet thickness
= 1.524 mm (0.060 in.). Cold work 20%,
+ anneal at 1038 oC (1900 °F), 4.5 mino Tested in argon 12
]
~------------t-------~~--1---~~--L---~84
~
:2
:i ~
Ifí
~
8 ~----~~~--+-~~~~~~~------_+----~56 100 h
4
O
8
~
~~~~~----+-------------~------------~28
L-------____
~
____________
_ L_ _ _ _ _ _ _ _ _ _ _ _
~O
r-------------,-------------.-------------~56
1500 °F (816 OC) 6
~------------+-----------~~----_,------~42
'"
a..
] ~..
:2
4
~------_1~~+-------~~--~~~~------~28
~
:i ~
Ifí
Ifí 2
500 h 1000 h 2000 h
O L-----------~------------~------------~O
8 ,-------------,-------------,-------------,56 1650 °F (899 oC) 6
~------------t-------------~------------~42
'"
.¡;; -""
:i Q)
a..
:2
4
~------------t-------------+---~~------~28
:i
~ Vl
~ 2
0~10~0~0~h~----~20~0~0~h~----------~------------~0 0.1 10 100 Total strain, %
at temperature. Composition: 72Ni-15.5Cr-8Fe. UNS N06600 Source: J.R. Wier, Jr., D.A. Douglas, and W.D. Manly, "Inconel as a Structural Material for a High Temperature Fused Salt Reactor," ORNL2264, June 1957. As published in Aerospace Structural Metals Handbook, Vol 4, Code 4101, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 14
Nickel (Ni)/639
Ni.014 Inconel 600 annealed nickel alloy sheet, isochronous stress-strain curves at various temperatures
20 .-------------,-------------,--------------,140 1300 'F (704 'C) 16 ~------------+_-------------~------------~112
._ 12 ~----------~+_-------------~~----~70--~84
""'"tJi '"~ üí
& :2
8 ~----------~~~-----~~~~~------+----156
4
tJi en
~
~~~--~--~------------~------------~28
2000 h
OL---~--------L--·----------~----------~O 8 ,-------------,--------------,--------------,56 1500 'F (816 'C) 6 ~------------+_--------------r--~~~-----142 ro o.. :2
'w
""gf
~
4 ~------------+_--~~----~~~--+_-------128 en tJi ~
üí 2
100 h 500 h 1000 h 2000 h
OL-------------L--·----------~----------~O 6 ,-------------,--------------,--------------,42 1650 'F (899 'C) ._ 4 ~------------+_-------------~------~----~28
g¡
tJi
'" ~
& :2
gf ~
2 ~------------+-~~~--~~~~~--~----~14 üí 100 h 500 h 1000 h
O~------------~-------------~------------~o 0.1 10 100 Total strain, %
Sheet thickness = 1.524 mm (0.060 in.). Annealed at 1121 oC (2050 °P), 2 h. Tested in argon at temperature. Composition: 72Ni-15.5Cr-8Pe. UNS N06600 Source: J.R. Wier, D.A. Douglas, and W.D. Manly, "Inconel as a Structural Material for a High Temperature Fused Salt Reactor," ORNL2264, June 1957. As published in Aerospace Structural Metals Handbook, Vol 4, Code 4101, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 14
640/Nickel (Ni)
Ni.015 IN 100 as-cast nickel alloy, stress-strain curves at room and elevated temperatures
160r---r---r--'---.---.---.---.---.---r---r--~1120
Composition: Ni-15Co-10Cr-5.5Al-4.7Ti-3Mo-0.95Y. UNS N13100 Source: W.F. Sirnmons and R.B. Gunia, "Compilation of Trade Names, Specifications, and Producers of Stainless Alloys and Superalloys," ASTM Data Series DS 45, 1969, P 7, 10, 115, revised by personal communication, Meteut to MPDC 13 June 1978. As published in Aerospace Structural Metals Handbook, Vol 5, Code 4212, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 24
120~~---+r--+--~--4---+---~~~-+---+--~840
40~~~~---1L--+~-+---+---+---+--~--~--~280
Strain x 0.001
Ni.016 IN 100 nickel alloy, cast and JO coated, stress-strain curves at room and elevated temperatures
1120
160
70°F (21°C)
Cast to 6.35 mm (0.25 in.) diam bar; 50.8 mm (2 in.) gage length. JO coated by TRW with PWA A47 coating plus 1079 oC (1975 °P), 4 h in vacuum, + rapid argon quenched. Composition: Ni-15Co-lOCr-5.5Al-4.7Ti3Mo-0.95Y. UNS N13100
840
120 1562 °F (850 OC)
I
.¡¡;
"'
ro
I
Il.
1697 °F (925 OC)
:2
560
80
'"~
Cií
Cií
280
40
Strain x 0.001
Souree: W.F. Simmons and R.B. Gunia, "Compilation ofTrade Names, Specifications, and Producers of Stainless Alloys and Superalloys," ASTM Data Series DS 45, 1969, P 7, 10, 123. As published in Aerospace Structural Metals Handbook, Vol 5, Code 4121, CINDAS/ USAF CRDA Handbooks Operation, Purdue University, 1995, p 25
Nickel (Ni)/641
Ni.017 Inconel 702 nickel alloy sheet, tensile stressstrain curves at various temperatures
8o.---------~--------~--------_r--------_,560
Sheet thickness = 1.016 mm (0.040 in.). Reat treatment: 1079 oC (1975 °P), 0.5 h, air cooled + 760 oC (1400 °P), 5 h, air cooled. Composition: Ni-15Cr-3AI-0.5Ti. UNS N07702
~........- - - Room1temperature
400 'F (204 'C)
60L-------~~~~~~~~~----_L--------~420 ~
gf 40 1------llhWl"'...t----"-"-"---'--'.:.~+--------+--------___j 280
E en
~ rñ
~
Source: "Research Investigation to Determine Mechanical Properties of Nickel and Cobalt Base Alloys for Inclusion in Military Handbook 5," Vol 1,11, TDR No. ML-TDR-64-116, 1964. As published in Aerospace Structural Metals Handbook, Vol 4, Code 4102, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 3
Ci5
20
140 1600 'F (871 'C) 1800 'F (982 'C)
O O
2
4 Strain, 0.001 in.lin.
6
8
O
Ni.018 Inconel 702 nickel alloy sheet, compressive stress-strain curves at various temperatures
80r---------,----------r---------r---------,560 _ _- - Room temperature
Test direction: transverse. Sheet thickness = 1.016 mm (0.040 in.). Reat treatment: 1079 oC (1975 °P), 0.5 h, air cooled + 760 oC (1400 °P), 5 h, air cooled. Composition: Ni-15Cr-3AI-0.5Ti. UNS N07702
00 'F \204 'C)
......:::~::::~~~~ 600 'F
316 'C)
601--------.~~~----~~~----+--------___j420
~
800 'F (427 'C) 1000 'F (538 'C) •• ..---1200 'F (649 'C) I 1600 'F (871 'C)
_.¡._--
~
:2
gf 40 1-------H'I---+7"'-----------+----------I-----------j 280 gf
~
~
Ci5
201--.~----+_--------~--------+--------___j140
__-t-----r---
1800 'F (982"C)
°0L---------~2------·--~4----------6L-------~80
Strain, 0.001 in.lin.
Source: "Research Investigation to Determine Mechanical Properties of Nickel and Cobalt Base Alloys for Inclusion in Military Handbook 5," Vol 1, 11, TDR No. ML-TDR-64-116, 1964. As published in Aerospace Structural Metals Handbook, Vol 4, Code 4102, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 3
642/Nickel (Ni)
12
10
r
--
. . . . r-.,..
'\
84
Ni.019 MA 6000 oxide-dispersion-strengthened nickel alloy, rolled product, tensile stress-strain curve at 1100 oC (2012 °F)
70
As hot roUed. Average grain diam 0.26 !lm. Strain rate -2.0/s. Calculated assuming uniform deformation. Composition: Ni-15Cr-4.5Al-4.0W-2.5Ti-2.0Mo-2.0 Ta-l.lyp3
56
8
ro o.. :2
~ ui en
~
ui
'"~
42
6
tí
CIl
CIl
~
~ 4
28
2
14
0.2
0.6
0.4
0.8
=
Source: J.K. Gregory. J.C. Gibeling, and W.D. Nix, High Temperature Deformation of Ultra-Fine-Grained Oxide Dispersion Strengtbened Alloys, Metall. Trans .• Vol16A (No. 5), 1985, P 777-787. As published in Aerospace Structural Metals Handbook, Vol 4, Code #4122, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995,p16
o
1.0
True strain
Ni.020 MA 6000 oxide-dispersion-strengthened nickel alloy bar, compressive stress-strain curves at room and elevated temperatures
200.-------,-------,--------,-------,--------,1400
Annealed at 1000 oc (1832 °F), 1 h, air cooled in argon10% hydrogen. Grain aspect ratio = 17: 1. Initial strain rate = 0.00015/s. Composition: Ni-15Cr-4.5Al-4.0W2.5Ti -2.0Mo-2.0Ta-l.l Y203
1050 1472 °F (800 OC)
~
ro o.. :2
I
1562 °F (850 OC)
ui
'"~
ui
700 ~ tí
tí
CIl
CIl :;¡
~
~
1832 °F (1000 OC) 350
2192 °F (1200 OC)
0.04
0.08
0.12
True strain
0.16
O
0.20
Source: B. Reppich, W. List!, and T. Meyer, Particle-Strengthening Mechanisms in ODS Superalloys, Con! High Temperature Alloys for Gas Turbines and Other Applications 1986 (Liege, Belgium), 1986, Part n, p 1023-1035. As published in Aerospace Structural Metals Handbook, Vol 4, Code 4122, ClNDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 18
Nickel (Ni)/643
2x10-'/s
/'"
160
~
Test direction: longitudinal. Annealed bar with coarse, elongated grain structure. Composition: Ni-15Cr-4.5Al4.0W-2.5Ti-2.0Mo-2.0Ta-l.l y 203
1120
~
2x1Q-'/s 840
~120
i'"
Ni.021 MA 6000 oxide-dispersion-strengthened nickel alloy bar, effect of strain rate on true stressstrain curves at 760 oC (1400 °F)
1400
200
&
:2
gi
~
80
~
O 1x10-6 /s
'"
Source: E.G. Jacobs, "Understanding !be Stress-Resisting Creep and Hot Tensile Deforrnation in ODS SuperalIoys," Dissertation, Columbia University, UMI Dissertation Inforrnation Service, 1990. As published in Aerospace Structural Metals Handbook, Vol 4, Code 4122, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 16
560 ~
~
280
40
O strer at failure, ¡mpensated fT necking
0.04
0.08
0.12
o
0.20
0.16
True strain
60 40
1652 °F (900
.;
..
20
']7
/
8
~
6
p/
/
tí o
¡¡:
1832 °F (1000 °e)/
4
2
.'
...
/;~ .... /)1
~ 10 m ~
0y
V 1/ J:.
/
V
/
V
140
V
.~
t/
/
~/O
~
56
m ~
tí ~
LL
28
V 2012 °F (1100 OC)
10 10 Strain rate, %/h
:2
.Q
/
10
ca
o..
70
42
~
14
.,
10
280
Average grain diameter: 0.26 11m. Composition: Ni-15Cr-4.5AI-4.0W-2.5Ti-2.0Mo-2.0Ta-l.l Y203
.-p
~
/
lff
Ni.022 MA 6000 oxide-dispersion-strengthened nickel alloy bar, as hot rolled, effect of strain rate and temperature on flow stress of fine-grained alloy
420
10
10
10
7
10
Source: J.K. Gregory, J.C. Gibeling, and W.D. Nix, High Temperature Deforrnation of Ultra-Fine-Grained Oxide Dispersion Strengthened AlIoys, Metal!. Trans., Vol16A (No. 5), 1985, P 777-787. As published in Aerospace Structural Metals Handbook, Vol 4, Code #4122, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 18
644/Nickel (Ni)
120
100
,
l
80
/
",/
................
/' ... ---""-
f..;;/
"'
@
r~v
60
U5 40
20
~_.
Ni.023 MA 6000 oxide-dispersion-strengthened nickel alloy rod, cyclic and monotonic stress-strain curves at various temperatures
700
Annealed: 1232 oC (2250 °P), 0.5 h, air cooled, + 954 oC (1750 °P), 2 h, air cooled, + 843 oC (1550 °P), 24 h, air cooled. Solid line: Cyc1ic load, R = -1, strain rate = 10-2/s. Dashed line monotonic, strain rate not reported. Composition: Ni-15Cr-4.5Al-4.0W-2.5Ti-2.0Mo-2.0 Ta-1.1YP3
•••• 1562 JF (850 'C)
560
................
",,,,,,,,
·00
840
1742 'F (950 'C)
o..'"
:2 420 (/)rñ @
U5
. .......... .. • •• ··1922 'F (1050 'C)
280
Source: M. Marchionni, D. Ranucci, and E. Picco, Influence of Environment on High Temperature Low Cycle Failure of an Oxide Dispersion Strengthened Nickel Base SuperaIloy, Con! High Temperature Materials for Power Engineeing 1990 (Liege, Belgium), Par! n, 1990, p 1195-1204. As published in Aerospace Structural Metals Handbook. Vol 4, Code 4122, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 24
140
! 0.4
1.6
1.2
0.8
o
2.0
Strain, %
840
Ni.024 Inconel X-750 nickel alloy sheet, tensile stress-strain curves at room and elevated temperatures
700
Sheet heat treated to an ultimate strength of 1069 MPa (155 ksi). Composition: Ni-15Cr-7Pe-2.5Ti-lNb-0.7 Al. UNS N07750
80
560
Source: Aerospace Structural Metals Handbook, Vol 4, Mechanical Properties Data Center, BatteIle Columbus Laboratories, 1981, P 9
60
:2 420
120
Room temperature 100
1000 'F (538 'C)
o..'"
·00
"'
@
g;
U5
(f)
40
280
20
140
O O
2
4 Strain, 0.001 in./in.
6
8
O
Nickel (Ni)/645
160 -423 140
~
120
i /--
60
40
20
J
(-253 'C)
~
~96'C) ~
- - 7 0 'F (21 'C)
-
r v
100
/ V
Ni.025 Inconel X-750 nickel alloy sheet, tensile stress-strain curves at room and low temperatures
1120
Test direction: longitudinal. Sheet thickness = 1.27 mm (0.050 in.). Precipitation-treated condition: 982 oC (1800 °P), 1 h, force cooled to 704 oC (1300 °P), held 20 h, air cooled. Composition: Ni-15Cr-7Pe-2.5Ti-1Nb0.7Al. UNS N07750
980
840
700 ro
o..
::¡;
560 ui
~
Source: E.H. Schmidt, "Fatigue Properties of Sheet, Bar and Cast Metallic Materials for Cryogenic Applications," Rocketdyne, R-7564, 30 Aug 1968. As published in Aerospace Structural Metals Handbook, Vol 4, Code 4105, CINDAS/USAF CROA Handbooks Operation, Purdue University, 1995, p 16
420
/
280
140
2
6
4
o
8
10
Strain, 0.001 in.lin.
Ni.026 Inconel X-750 nickel alloy bar, complete stress-strain curves at room and low temperatures
1960
280 -42l 'F (-2J3 'C) I
240
'00 160
"'ui" ~
d
V
~~
~E::::./
200
~
Bar diameter = 3.81 mm (0.150 in.). Precipitation-treated condition: solution treated + 704 oC (1300 °P), 20 h, air cooled. Composition: Ni-15Cr-7Pe-2.5Ti-1Nb-0.7Al. UNS N07750
1680
-320 'F (-1r 'C)
~ 1400 \ -110 'F (-79 'C)
"\
:...--
I
\ Room temperature
11208: ::¡;
f
éií 120
840 éií
80
560
40
280
0.05
0.10
0.15
0.20 Strain, in.lin.
0.25
0.30
0.35
o
0.40
Source: K.A. Warren and R.P. Reed, 'Tensile and lmpact Properties of Selected Materials From 20 to 300 K," Monograph 63, National Bureau of Standards, 1963. As published in Aerospace Structural Metals Handbook, Vol 4, Code 4105, CINOAS/USAF CROA Handbooks Operation, Purdue University, 1995, p 16
646/Nickel (Ni)
Ni.027 Inconel X-750 nickel alloy sheet, compressive stress-strain curves at room and elevated temperatures
12o,---------.----------.----------.---------~840
560
80 1000 °F (538 OC) 1200' °F (649 OC)
~ rñ U)
~
'"
[L
::¡¡
420
60
rñ U)
~
(f)
40
280
20
140
00
2
4 Slrain, 0.001 in./in.
6
8
Source: P.J. Hughes, l.E. Inge, and S.B. Prasser, "Tensile and Cornpressive Stress-Strain Properties of Sorne High-Strength Sheet Alloys at Elevated Ternperatures," NACA TN-3315, Nov 1954. As published in Aerospace Structural Metals Handbook, Vol 4, Code 4105, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 19
O
140,-------,--------,-------,--------,-------, 980 1200 °F (649 OC)
Ni.028 Udimet 700 wrought nickel alloy, typical stress-strain curves at elevated temperatures
120~------+_------_r------~~------t_------~
840
Fully heat treated. Composition: Ni-18Co-15Cr-5Mo4.5AI-3.5Ti-0.03B
700
Source: "Udirnet 700-Alloy Performance Data," Brochure No. 8595, Kelsey Hays Co., Metal Division, 1959. As published in Aerospace Structural Metals Handbook, Vol 5, Code 4207, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 18
1600 °F (871°C)
~
Test direction: longitudinal and transverse. Sheet thickness = 1.63 mm (0.064 in.). Precipitation-treated condition: annealed, + 704 oC (1300 °F), 20 h, air cooled. Composition: Ni-15Cr-7Fe-2.5Ti-lNb-0.7 Al. UNS N07750
80~------+_----~~~----_4--------+_------~
560
gj"
t1.
::¡¡ rñ U)
~
~
1i5 60~------+_~~--_r------~--------t_------~ 420 1i5 1800 °F (982 OC) 280 1900 °F (1038 OC) 140 2000 °F (1093 OC) ~------~2--------4L-------~6~------~8------~1~
Slrain, 0.001 in./in.
Nickel (Ni)/647
1400
200
Bar specimen
160 'c;;
-'"
vi en
~
Ni.029 Udimet 700 nickel alloy bar, stress-offset strain curves at room temperature
1680
240
120
V
V
V
V
~
y-er ~ ~~
v ~
..--V
V /
/
/"
1120 a.
'"
:2 vi en
~ 840 (/)
"'-Sheet specimen
Round bar (9.373 mm, or 0.369 in., diam) and sheet 0.368 x 0.012 in. (2 grains thick) specimens machined from 2504 mm (1 in.) diam round bar. Heat treated in argon atmosphere: solution at 1163 oC (2125 °F) for 4 h, forced air cooled, primary age at 1079 oC (1975 °F), 4 h, forced air cooled, stabilized 843 oC (1550 °F), 4 h, forced air cooled, final aging 760 oC (1400 °F), 16 h, forced air cooled. Sheet was spark machined, hand polished, and electropolished from the round bar. Composition: Ni18Co-15Cr-5Mo-4.5AI-3.5Ti-0.03B Source: C.H. Wells and c.P. Sullivan, The Low Cycle Fatigue Characteristics of a Nickel Base Superalloy at Room Temperature, Trans. ASM Quart., Vol 57, 1964, p 841-855
80
560
..
..
40 10
10
280 10
10 Offset strain
140
Ni.030 Nimonic 75 annealed nickel alloy sheet, engineering stress-strain curve (full range)
980
120
,........
100
,/
/
/
V
------
840
700
&.
:2
560 gf
~
Cl
c:
420 .~ c:
'6> c:
UJ
40
280
20
140
o
O
0.05
0.10
0.15 Strain
0.20
0.25
0.3S
Test direction: longitudinal. Sheet thickness = 3.0 mm (0.118 in.). 0.2% yield strength = 387 MPa (56.1 ksi); ultimate tensile strength = 797 MPa (115.6 ksi); elongation = 36.7%. Composition: Ni-19.5Cr-004Ti. UNS N06075 Courtesy of Special Metals Corporation
648/Nickel (Ni)
420
60
,/ 50
._ 40
g¡
i
g> 30
.~
ID
<= <=
'c, UJ
20
10
/
350
/ I I I
Ni.031 Nimonic 75 annealed nickel alloy sheet, engineering stress-strain curve (expanded range)
Test direction: longitudinal. Sheet thickness = 3.0 mm (0.118 in.). 0.2% yield strength = 385 MPa (55.9 ksi); ultimate tensile strength = 799 MPa (115.9 ksi); elongation = 36.7%. Composition: Ni-19.5Cr-OATi. UNS N06075 Courtesy of Special Metals Corporation
70
11 2
4 6 Strain, 0.001 in.lin.
8
Nickel (Ni)/649
160
1120
160
1120
140
980
140
980
120
840
120
840
100
700 Il.
::¡;
~
560
gf
-'"
gf ~
80
"'
Cñ
~ ~
1600 "F (871 "C)
40
280
40
140
20
2
4
6 8 Strain, 0.001 in./in.
10
O 12
O O
(a)
"'~
420
280
1800 "F (982 "C)
2000 "F (1093 "C)
2
4
6 8 Strain, 0.001 in./in.
10
140
O 12
(b) 1120
160
1120
140
980
140
980
120
840
120
840
100
700
100
700
tU
Il.
::¡;
-'"
~
560
160
·00
gf
::¡;
Cñ 60
O O
Il.
80
420
1800 "F (982 "C)
tU
1600"F (871 "C)
60
20
700
100 tU
·00
560
80
40
Il.
::¡;
1600 "F (871 "C)
~- 80
560 rñ
"'~ Cñ ~
1800"F (982 "C) 60
ro
·00 -'"
"'
~
420
60
420
280
40
280
140
20
140
2000 "F (1093 "C) 20
00
(e)
2
4
6 8 Strain, 0.001 in./in.
10
O 12
00
0.02
0.04
0.06 Strain, in./in.
0.08
0.10
O 0.12
(d)
Ni.032 René 41 nickel alloy sheet, tensile stress-strain curves at room and elevated temperatures Sheet solution treated 1066 oC (1950 °P), 0.5 h, rapid air eooled, aged 760 oC (1400 °P), 16 h, air eooled. (a) Sheet thickness = 1.27 mm (0.050 in.). Strain rate = 0.00060 in./in./min. (h) Sheet thiekness = 1.27 mm (0.050 in.). Strain rate =0.060 in./in./min. (e) Sheet thickness = 1.27 mm (0.050 in.). Strain rate = 6 in./in./min. (d) Sheet thiekness = 3.175 mm (0.125 in.). Strain rate = 0.005 in./in./min. Composition: Ni-19Cr-llCo-9.8Mo-3.2Ti-1.5AI-0.006B. UNS N07041 Source: "Mechanical Properties of René 41 Sheet Materia1s," Report No. BLR 61-21(M), Bell Aerosystem Co., 29 June 1962; "Tensile and Creep Properties of 0.010 and 0.050 Inch René 41 Alloy Sheet from Room Temperature to 2000F," Report PR 281-1Q-1, The Marquardt Corp., 12 Sept 1962. As published in Aerospace Structural Metals Handbook, Vo15, Code 4205, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 34
650/Nickel (Ni)
280
Ni.033 René 41 nickel alloy bar, tensile stress-strain curves at room and low temperatures
1960
-42~ °F (-253 OC) 1
240
200
.¡¡; 160
'"rñ ~'"
~
~~ V
~
--~ -;::::::::. ~ -:320
Bar diameter = 19.05 mm (0.750 in.). Heat treatment: 1079 oC (1975 °P), 4 h, water quenched, + 760 oC (1400 °P), 16 h, air cooled. Composition: Ni-19Cr-llCo9.8Mo-3.2Ti-1.5AI-0.006B. UNS N07041
1680
°F \-196 OC)
-110 °F (-79 oC)
rl::;:::::=== :::::::::::=
1400 70 °F (21 OC) 1120~ ::2;
~
rñ
(/) 120
840
80
560
40
280
0.04
0.08
0.12
0.16
Slrain, in.lin.
0.20
0.24
o
0.28
'"
~
Source: ER. Schwartzberg, S.H. Osgood, R.D. Keys, and T.E Kieffer, "Cryogenic Materials Data Handbook," ML-TDR-64-280, Air Force Materials Laboratory Report, Aug 1964; K.A. Warren and R.P. Reed, "Tensile and lmpact Properties of Selected Materials from 20 to 300 degrees K," Monograph 63, National Bureau of Standards, June 1963. As published in Aerospace Structural Metals Handbook, Vol 5, Code 4205, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 34
Nickel (Ni)/651
16or-----,------,------,-----,------,-----, 1120
160
1120
Room temperature 140~----~------~--·--~~~~r_----~----~
980
140
980
120~----~------~~:~~~~~~----~----~
840
120
840
100~----~--~~~-----~----~------+_----_1
700
1600 °F (871°C)
~
100 lO
o..
;:¡;
gl 80~----~~+4~~--·--~----~------+_----_1 560 gl
~
~
iñ
""gl ~
lO
o..
;:¡;
.,
80
560 .; ~
UJ
iñ 60~----4++4~_+------~----+_----~----_4
700 1600 °F (871°C)
'c;;
420
iñ 60
40~--~~-----+------~----+_----~----~280
420
40~--~~------~----~----~------+_----~
1800 °F (982 OC)
1800 °F (982 OC) ~~~~~~~~----~----~------~----~140
2000 °F (1093 OC)
280 140
2000 °F (1093 OC) ~-----2j-------4L---·---6L-----~8L-----~10~--~1l
2
4
6
Strain, 0.001 in./in.
8
10
O
12
Strain, 0.001 in./in.
(a)
(b)
160,-----,-----,------,-----,-----,-----, 1120 Room temperature
140~----4------+------~----+_~~~~~~ 980
800°F (427 OC)
1200 °F (649 oC)
120~----~------~--~~~~_4------~~--~
840
100~----~--_.hI~~--~----_4------+_----~
700 lO
~
o..
;:¡;
gl 80~----~~~L-~----~----~------+_----~ 560 ., .;
~
~
iñ 60~----~+---_+------~----+_----~----~
420
1600 °F (871°C) 40~--~~--~~~--~------+-----~----~
280
20~~~+-----_+----~------+-----~----~
140
1800 °F (982 OC) 2000 °F (1093 OC)
~----~-----L----~------~----~~--~O
2
4
6
8
10
12
Strain, 0.001 in./in.
(e)
Ni.034 René 41 nickel alloy sheet, compressive stress-strain curves at room and elevated temperatures
Strain rate = (a) 6 in./in./min. (b) 0.6 in./in./min. (e) 0.0006 in./in./min. Reat treatment: 1079 oC (1975 °P), 0.5 h, water quenehed + 760 oC (1400 °lF), 16 h, air eooled. Composition: Ni-19Cr-l1Co-9.8Mo-3.2Ti-1.5AI-0.006B. UNS N07041 Source: P.R. Dioguardo and R.D. Lloyd, "Investigation of the Effects of Rapid Loading and Elevated Temperatures on the Mechanical Properties of Compressive and Column Members," ASD-TR-62-199, Jan 1962. As published in Aerospace Structural Metals Handbook, Vol 5, Code 4205, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 43
652/Nickel (Ni)
-"v
200
wheelfo~
160
rI
cñ120
'"~
1ñ el
c:
"55
.g, 80 c:
w
40
.... ~ ,.----1---1,...... ....
~ .......
~
Ni.035 René 41 nickel alloy forged bar and turbine wheel forging, stress-strain curves at 538 oC (1000°F)
1400
--
~
--- --
!-----~
1120
Bar
ro
a. 840 :2.
'"'"~
1ñ el
c:
Heat treatment: 1079 oC (1975 °F), 2 h, oil quenched, + 774 oC (1425 °F), 16 h, air cooled. Wheel yield strength = 883 MPa (128 ksi); ultimate strength = 1220 MPa (177 ksi). Bar yield strength = 841 MPa (122 ksi); ultimate strength = 1151 MPa (167 ksi). Composition: Ni-19Cr-l1Co-9.8Mo-3.2Ti-1.5Al-0.006B. UNS N07041 Source: Aerospace Structural Metals Handbook, Vol 5, Mechanical Properties Data Center, Battelle Columbus Laboratories, 1978, p 22
.~
560 ~
'c,
I I I
c:
W
280
A
0.008
0.016
0.10
0.06
0.14
o
0.18
Strain, in./in.
~
100
11
cñ
.~
c:
'c,
V
...............
./
._ 80
~g> 60
Ni.036 Inconel 718 annealed nickel alloy sheet, engineering stress-strain curve (full range)
840
120
I
~
/
700
560 ro a. :2 cñ
'"~
420
~ c:
.~
c:
'c,
c:
c:
280 w
w 40
140
20
0.05
0.10
0.15 Strain
0.20
0.25
o
0.30
Test direction: longitudinal. Sheet thickness = 1.524 mm (0.060 in.). 0.2% yield strength = 346 MPa (50.2 ksi); ultimate tensile strength = 820 MPa (118.9 ksi); elongation = 53.8%. Composition: Ni-19Cr-18Fe-5.1(Nb + Ta)-3Mo-0.9Ti-0.5Al. UNS N07718 Courtesy of Special Metals Corporation
Nickel (Ni)/653
60
420
I
350
50
I
._ 40
g¡
,¡;
~g> 30 .~
c: '6> c: LU
20
10
Ni.037 Inconel 718 annealed nickel alloy sheet, engineering stress-strain curve (expanded range)
280
I I I
ro
c..
:2 ,¡;
Test direction: longitudinal. Sheet thickness = 1.524 mm (0.060 in.). 0.2% yield strength = 348 MPa (50.5 ksi); ultimate tensile strength = 821 MPa (119.0 ksi); elongation = 52.8%. Composition: Ni-19Cr-18Fe-5.1(Nb + Ta)-3Mo-0.9Ti-0.5AI. UNS N07718 Courtesy of Special Metals Corporation
~'"
210 ~ c:
"m 140
c: '6> c: LU
70
/
4 6 Strain x 0.001
2
8
180
1260 A l~
160
A
140
'"~
éií
80
40 20
1120
840 ro
700 ~
,¡;
560 (J) ~'"
I I
420 280
Ij
140
0.4
Ni.038 Inconel 718 nickel alloy sheet, stress-strain curves with effect of heat treatment conditions
980
/ /
100
60
B
e
If
120 '00 -'" ,¡;
¡...--
0.8
1.2 1.6 Strain, %
2.0
2.4
o
2.8
Sheet thicknesses = 17.78 and 2.54 mm (0.70 and 0.100 in.). Heat treatment: A: 954 oC (1750 °F), 0.5 h, air cooled, + 718 oC (1325 °F), 10 h, force cooled, to 621°C (1150 °F), + 621°C (1150 °F) for total age time 20 h, air cooled. Or 1010 oC (1850 °F), 0.5 h, air cooled, + 718 oC (1325 °F), 10 h, force cooled to 635 oC (1175 °F), + 635 oC (1175 °F) for total age time 20 h, air cooled. B: 1066 oC (1950 °F), 0.5 h, air cooled, + 760 oC (1400 °F), 10 h, force cooled to 649 oC (1200 °F), + 649 oC (1200 °F) for total age time of 20 h, air cooled. C: 1121 oC (2050 °F), 0.5 h, air cooled + 760 oC (1400 °F), 10 h, force cooled to 649 oC (1200 °F), + 649 oC (1200 °F) for total age time of 20 h, air cooled. Composition: Ni-19Cr-18Fe-5.1(Nb + Ta)-3Mo-0.9Ti0.5AI. UNS N07718 Source: "Effect of Heat Treatment and Snrface Oxidation on the LowCycle Fatigue Life of AIloy 718," Report MPR No. 9-176A-77, Rocketdyne, May 1969. As published in Aerospace Structural Metals Handbook, Vo14, Code 4103, CIl\TDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 42
654/Nickel (Ni)
Ni.039 Inconel 718 nickel alloy sheet, typical tensile and compressive stress-strain and compressive tangent modulus curves at room temperature
Compressive tangent modulus, GPa
200 or-:-----T=____....:7.;.o_ _1~0..:.5-~1~40=----.:..;17..:.5---=~-__=_;241400
a.
Test direction: longitudinal (L) and long transverse (LT). Sheet thickness =0.254-6.35 mm (0.010-0.250 in.). Solution treated and aged Inconel 718, heat-resistant alloy (AMS 5596). Ramberg-Osgood parameters: n(L, tension) = 21; n(LT, tension) = 22; n(L, compression) = 21; n(LT, compression) = 24. Composition: Ni-l9Cr18Fe-5.1(Nb + Ta)-3Mo-0.9Ti-0.5Al. UNS N07718
¡i
Source: MIL-HDBK-5H, Dec 1998, p 6-58
160 f-------I---_+--F-74---+---"'~=_'''''''_:_+--_I 1120 L and LT, tension
.¡¡; -'"
120 f-------I---~--4_--+--__I--:_++_-_I840 ro
:2:
'"
~
~
1ñ 80
f------+-#~_+--4_--+--__I--:_++_-_I5601ñ
40f----~L+---+--4---+----I--:-++---I280
0
0
2
6
4
8
10
12
o 14
25
30
35
Strain, 0.001 in./in.
o
10
5
I
I
15
20
Compressive tangent modulus, 106 psi
Ni.040 Inconel 718 nickel alloy sheet, tensile stressstrain curves at room and low temperatures
2 4 0 . - - - - , - - - - , - - - - , - - - - , - - - - , 1680 -423 °F (-253 OC)
Heat-resistant alloy, solution annealed and aged (conditioning not reported). Composition: Ni-19Cr-18Fe5.1(Nb + Ta)-3Mo-0.9Ti-0.5Al. UNS N07718
1400
1120 ro
a.
:2:
840
g'"
(J)
560
280
0.2
0.6
0.4 Strain, %
0.8
o 1.0
Source: E.H. Schmidt, "Fatigue Properties of Sheet, Bar, and Cast Metallic Materials for Cryogenic Applications," NASA CR-111396, 30 Aug 1968. As published in Aerospace Structural Metals Handbook, Vol 4, Code 4103, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 50
Nickel (Ni)/655
220
1540
200
75°F (24 OC) 1400
-
180
140
g¡
6do
Heat treatment: 1037 oc (1900 °F), 1 h, air cooled, + 760 oc (1400 °F), 10 h, force cooled to 649 oC (1200 °F) and held for total age time of 18 h, air cooled. Composition: Ni-19Cr-18Fe-5.1(Nb + Ta)-3Mo-0.9Ti0.5Al. UNS N07718
°F (316 OC) 1260 900°F (482 oC) 1200 °F (649 OC) 1120
"""" / l..--":: ~~
160
Ni.041 Inconel 718 nickel alloy plate, tensile stressstrain curves at room and elevated temperatures in hydrogen at 34.5 MPa (5.0 ksi)
980
r¡
840 ~
120
"'
700 ~
100 80
560
60
420
40
280
,J
20
Souree: J. Mueci and J.A. Harris, Sr., "Influenee of Gaseous Hydrogen on Meehanical Properties of High Temperature Alloys," FR-7746, Pratt & Whitney Aireraft Group, July 1976. As published in Aerospace Structural Metals Handbook, Vol 4, Code 4103, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 34
140 3
2
4
Strain, %
240
1680 70 oF(L OC)
200
(
í --
160 .¡¡; -'"
~"'
f--
120
I
C/l
--
1400
-
1200 °F (649 OC)
-----...
1120
&
:2
840
1400 °F (760 OC)
V
"
80
560
40
280
o
O
2
4
6
8 Strain, %
10
12
14
Ni.042 Inconel 718 nickel alloy bar, tensile stressstrain curves at room and elevated temperatures
"' ~
Heat-resistant alloy, solution treated and aged (conditioning not reported). Composition: Ni-19Cr-18Fe5.1(Nb + Ta)-3Mo-0.9Ti-0.5Al. UNS N07718 Souree: G.L. Heslington and S.D. Foster, "Stress-Strain Diagrams in tbe Elastie and Plastic Regions at Elevated Temperatures," Report MPR 8-176A-37, Roeketdyne, 17 Oet 1968. As published in Aerospace Structural Metals Handbook, Vol 4, Code 4103, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 39
656/Nickel (Ni)
Ni.043 Inconel 718 nickel alloy bar, typical tensile and compressive stress-strain and compressive tangent modulus curves
Compressive tangent modulus, GPa 200 o¡--_---,3;-5_ _-,7o_ _ _1,o_5_ _1,4_o_ _1T75_ _ _2,10_ _-,241400
Test direction: longitudinal (L) and short transverse (ST). Solution treated and aged (creep rupture application). AMS 5662 and 5663. Ramberg-Osgood parameters: n(L, tension) = 18; n(ST, tension) = 14; n(L and ST, compression) = 13. Composition: Ni-19Cr-18Fe-5.1 (Nb + Ta)-3Mo-O.9Ti-0.5Al. UNS N07718
160 1-----1f----l-"""'-.46-""'---__+--"'--_+--+----j1120
.¡¡;
840
120
ro
O-
""(f;
Source: MIL-HDBK-5H, Oec 1998, p 6-58
:2: uf (J)
(J)
~ (f)
~
560
80
401--~~----l---+--__+--_+--+r----j280
2
4
6 8 Strain, 0.001 in./in.
I
12
o 14
I
15 25 10 20 Compressive tangent modulus, 106 psi
5
O
10
30
35
Ni.044 Inconel 718 nickel alloy bar, tensile stressstrain curves at room and low temperatures
1680
240 -410F (-2J OC) 200
/
160 ~ uf (J) 120
/I
~
80
40
I
V
0.2
V
r....--
1
_1
~310 °F (-19k OC)
I
Heat-resistant aHoy, solution annealed and aged (conditioning not reported). Composition: Ni-19Cr-18Fe5.1(Nb + Ta)-3Mo-O.9Ti-O.5Al. UNS N07718
1400
I
70 °F (21 °C) ______ 1120 ro
O-
:2:
840 en (J) ~
é'ií 560
280
0.4
0.6 0.8 Strain, %
1.0
1.2
o
1.4
Source: E.H. Schmidt, "Fatigue Properties of Sheet, Bar, and Cast Metallic Materials for Cryogenic Applications," NASA CR-111396, 30 Aug 1968. As published in Aerospace Structural Metals Handbook, Vol 4, Code 4103, CINOASIUSAF CROA Handbooks Operation, Purdue University, 1995, p 50
Nickel (Ni)/657
Ni.045 Inconel 718 nickel alloy bar, isochronous stress-strain curves (actual and predicted) at various temperatures
1120
160
1h 10 h 100 h
840
1000 h tIl
.¡¡;
c..
-'"
:2
rñ
560 rñ
ro
ro
'"~
'"~
280
O 840
1h 10 h 100 h 1000 h .¡¡;
560
tIl
c..
-'" rñ
:2 rñ
'" ~
'"~
280
ro
o 120
840 1300 °F (704 ·C) 1h
.¡¡;
80
560
10 h
-'" rñ
100 h
ro
1000 h
'"~
40
rñ
'"~
280
L--------~--------~--------~--------~o
0.4
0.8 Total strain, %
1.2
tIl
c..
:2
1.6
ro
Data points: actual data. Line: predicted from log-log curve. Heat-resistant alloy conditioned 982 oc (1800 °P), 2 h, air cooled + 718 oC (1325 °P), 8 h, force cooled 56 °CIh (100 °PIh) to 621°C (1150 °P), held 8 h, air cooled. Composition: Ni-19Cr-18Pe-5.1(Nb + Ta)-3Mo0.9Ti-0.5Al. UNS N07718 Source: R.M. Goldhoff, Methods for Constructing Isochronous Creep Curves, The Generatíon of lsochronous Stress-Straín Curves, ASME Pamphlet, Nov 1972, p 67-85. As published in Aerospace Structural Metals Handbook, Vol 4, Code 4103, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 62
658/Nickel (Ni)
200
.,.... ~
175
I
150
I
125
1/
~
gf 100 ~
50
25
/ /
1225 _
/
1/ /
éií 75
Ni.046 Inconel 718 nickel alloy roll-formed sheet l and E shapes, tensile stress-strain curves at room and elevated temperatures
1400 75°F 24 OC)
~
1200 °F (649 OC)
V--
1050
875 __ ----1400°F(760°C) f-"
a..'"
:2 700
'"~
éií 525
Ij/
r
Conditioned 996 oc (1825 °F) in hydrogen, + 718 oC (1325 °F), 8 hin argon, force cooled to 621°C (1150 °F) at 639 °C/h (1150 °F/h), + 621°C (1150 °F), 8 h, force cooled to room temperature in argon. Heat-resistant alloy. Composition: Ni-19Cr-18Fe-5.1(Nb + Ta)-3Mo-0.9Ti0.5Al. UNS N07718 Source: G.N. Wassil et al., "Form Rolling Close Tolerance Shapes of Superalloys," A.F. Contract No. AF33(6l5)-3545. As published in Aerospace Structural Metals Handbook, Vol 4, Code 4103, CINDAS/ USAF CRDA Handbooks Operation, Purdue University, 1995, p 49
350
175
0.5
1.0
1.5
2.0
2.5
o
3.0
Slrain, %
140
120
Ni.047 Inconel 718 nickel alloy investment casting, typical tensile stress-strain curve at room temperature (full range)
1120
160
I
/'-
980
Heat-resistant aHoy, solution treated and aged Inconel 718 (AMS 5383). Composition: Ni-19Cr-18Fe-5.1 (Nb + Ta)-3Mo-0.9Ti-0.5Al. UNS N07718
840
Source: MIL-HDBK-5H, Dec 1998, p 6--60 700
100
a.. '"
:2 560
'" ~
60
420
40
280
20
140
0.02
0.04
0.06 Slrain, in.lin.
0.08
0.10
o
0.12
Nickel (Ni)/659
200
o
Compressive tangent modulus, GPa 70 105 140 175
35
Test direction: longitudinal. Sheet thickness = 12.7 mm (0.500 in.). Heat-resistant alloy, solution treated and aged (AMS 5383). Composition: Ni-19Cr-18Fe-5.1(Nb + Ta)3Mo-0.9Ti-0.5Al. UNS N07718
1120
160
""-k
120
compression~~ ...............
'c;;
-'"
/
en
~
80
40
Ni.048 Inconel 718 nickel alloy investment casting, typical tensile and compressive stress-strain and compressive tangent modulus curves at room temperature
210
<
V
Source: MIL-HDBK-5H, Dec 1998, p 6-59 840
Tension
r--- ~
::¡;
'"
/
o
E
.......
V
/
2
4
5
10
'"
11.
6
8 Strain, 0.001 in.lin.
I
I
15
20
en
560
~ 280
o
10
12
14
25
30
35
Compressiv,e tang~nt modulus, 10 psi 6
160
Ni.049 Inconel MA 754 oxide-dispersionstrengthened annealed nickel alloy sheet, engineering stress-strain curve
1120
140
~
120
/
/
---
980
840
'"
11.
700 ::¡;
!
560 ~ e
.~
al
420
e
'g> LU
. 40
280
20
140
0.05
0.1 Strain
0.15
o
0.2
Test direction: longitudinal. Sheet thickness = 1.448 mm (0.057 in.). 0.2% yield strength = 614 MPa (89.0 ksi); ultimate tensile strength = 932 MPa (135.2 ksi); elongation = 16.6%, strain-hardening exponent (n) = 0.2245. Composition: Ni-20.0Cr-1.0Fe-0.5Ti-0.3 AI-0.05C-0.6Y203' UNS N07754 Courtesy of Special Metals Corporation
660/Nickel (Ni)
Ni.050 Inconel MA 754 oxide-dispersionstrengthened nickel alloy bar, compressive true stress-strain curve at room and elevated temperatures
1120
160
752°F 400 oC)
v
120
~
gf ~ 80 ID
~
RTt
840
1112 °F (600°C)
v
lE
:2 yj
560 ~
11
1ií ID
~ 1472 °F (800°C)
40
I
~
280
Cylindrical specimens, 4.064 mm (0.16 in.) diam, 6.096 mm (0.24 in.) long. Strain rate ::: 1.5 x lO-4/s. Average grain intercept 3.2 mm (longitudinal), 0.113 mm (transverse), aspect ratio::: 28/1. Composition: Ni-20.0Cr-l.OFe-0.5Ti-0.3Al-0.05C-0.6Y203' UNS N07754 Source: B. Reppich, W. List!, and T. Meyer, Partic1e-Strengthening Mechanisms in ODS Superalloys, Con! High Temperature Alloys for Gas Turbines and Other Applications 1986 (Liege, Belgium), Part 2, 1986, P 1023-1035. As published in Aerospace Structural Metals Handbook, Vol 4, Code 4106, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 16
1562 °F (850°C)
I
1832 °F (1 OOO°C) 2192 °F (1 200°C)
40
20 30 True strain, %
10
100
~ 80 yj ID
~
g
60
.~
/
~
~
-----
/
lE
Test direction: longitudinal. Sheet thickness ::: 1.22 mm (0.048 in.). 0.2% yield strength::: 387 MPa (56.1 ksi); ultimate tensile strength ::: 824 MPa (119.5 ksi); elongation = 57.4%. Composition: 57Ni-20.75Cr8.25Mo-bal Fe. UNS N07725
:2
Courtesy of Special Metals Corporation
700
560
1
420 ~ e .~
ID
ID
e .c,
Ji
Ni.051 Inconel 725 annealed nickel alloy sheet, engineering stress-strain curve (full range)
840
120
40
e .c, e 280 W
20
140
0.05
0.10
0.15 Strain
0.20
0.25
o
0.30
Nickel (Ni)/661
Ni.052 Inconel 725 annealed nickel alloy sheet, engineering stress-strain curve (expanded range)
490
70
60
~--
50
I
----
10
:2
Courtesy of Special Metals Corporation
350
a.
:i ~
280
/ / /
20
os
Test direction: longitudinal. Sheet thickness = 1.22 mm (0.048 in.). 0.2% yield strength = 423 MPa (61.4 ksi); ultimate tensile strength = 825 MPa (119.6 ksi); elongation = 58.0%. Composition: 57Ni-20.75Cr8.25Mo-bal Fe. UNS N07725
420
el
c: 210 .~ c: 'c, c: W
140
70
1/ 4
2
8
6
o
Strain. 0.001
180
1260
160
1120
Ni.053 Waspaloy nickel alloy all products, typical tensile stress-strain curves at room and elevated temperatures
980
Heat-resistant aHoyo Composition: Ni-20Cr-14Co-4Mo3Ti-1Al. UNS N07001
80 'F (27 'c) 140
".---¡/
120
1
800 'F (427 'c)
/ 1000 'F (538 'c)
Source: MIL-HDBK-5H, Dec 1998, p 6-95 840
~~ ~ ;::::::-:: ¡-
~ 100 rñ
'"~
é'ií
V
./"
80
1400 'F (760 'c)
os
700 ~
\1200 'F (649 'C
gf 560
60
420
40
280
20
J
140
11 5
10
15 20 Strain, 0.001 in.lin.
25
30
g en
662/Nickel (Ni)
Solution annealed 0.5 h, 1200 oC (2192 °F), force cooled or heated to test temperature. Strain rate 5/min. Composition: Ni-20Cr-14Co-4Mo-3Ti-1Al. UNS N07001
560
80
r---
L I
-----
- r--
¡oel
"['""i
40
1832 °F (1000 OC)
{
20
Ni.054 Waspaloy nickel alloy, effect of temperature on compressive flow curves
700
100
420
&.
:2 ui m
l'!
Source: A.A. Guimaraes and J.J. Jonas, Recrystallization and Aging Effects Associated with the High Temperature Deformation of Waspaloy and Inconel 718, Metall. Trans., Vol12A (No. 9), 9 Sept 1981, p 1655-1666. As published in Aerospace Structural Metals Handbook, Vol 5, Code 4208, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 23
Ci) al
280 ~
19~2 °F (10150 OC)
-r".
-¡-
/ 2 102 °F Cf50 OC)
22 28 °F (1í20 OC) 1
1
0.1
0.2
140
"2012 °F (11r O OC)
0.3
0.4
0.5
0.6
0.7
o
0.8
True slrain
80
v-- ~
t
-
Strai~rate
"'-....
r---
V 40
Ni.055 Waspaloy nickel alloy, effect of strain rate on compressive flow curves at 950 oC (1742 °F)
700
100
lí
~
--- --
560
in ~:n
r---- r--
~min
420
l'!
Ci)
0.3 min
0.03 min
al
280 ~
140
20
0.2
0.3
0.4 True strain
0.5
0.6
&.
:2 ui m
~
-1"---
0.1
Solution annealed 0.5 h, 1200 oC (2192 °F), force cooled to test temperature. Composition: Ni-20Cr-14Co-4Mo3Ti-1Al. UNS N07001
0.7
o
0.8
Source: A.A. Guimaraes and J.1. Jonas, Recrystallization and Aging Effects Associated with the High Temperature Deformation of Waspaloy and Inconel 718, Metal!. Trans., Vol12A (No. 9), 9 Sept 1981, p 1655-1666. As published in Aerospace Structural Metals Handbook, Vol 5, Code 4208, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 23
Nickel (Ni)/663
240
200 .¡¡;
""'. 160
j
ID
~ 120
Ni.056 Waspaloy nickel alloy forging, true stressstrain curves at room temperature
1960
280
I
/
V
v
A~
~-
-::C-
1400
&.
1120 :2
840
80
560
40
280
0.05
Square: Bar cut fram turbine disk specimen 10.2 mm (0.4 in.) thick by 121.9 mm (4.8 in.) diam fully heat treated. Circle: Specimen fram disk after overspeed burst, corrected for straining. Composition: Ni-20Cr-14Co4Mo-3Ti-1Al. UNS N07001
1680
0.10
0.15 True slrain
0.20
0.25
o
0.30
f ID
~
Source: L. Islip, Component Design and Material Selection, Engineering in High Duty Materials, Bulleid Memorial Lectures, Vol IV, University of Nottingham, 1967. As published in Aerospace Structural Metals Handbook, Vol 5, Code 4208, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 17
664/Nickel (Ni)
200
.¡g 100
=ª a. E lO
~
50
Ni.057 Waspaloy nickel alloy forging, static and cyclic stress-strain curves at room temperature
1400
.y~
rI
-.
--
~
4
lO
o..
:2
1050 --"
'"'e~"
700
2'"
"C
ª
a.
Static
E lO
350
'"'"~
1i5
o (a)
o
~
100~~hL-~-----_+------_r----~
700
'"
"C
ª
a.
E
E
lO
lO
~
350
''""
~
1i5 O~(b~)----~-------L------~------~O
200 ,..:--'-------,--------r--------¡:=------, 1400
~
.¡g a.
100~-HL--~-----_+----_r----~
ª
700
E
lO
~ ~
'"
"C
=ª a.
E
lO
50~~--_4-----_+----_r-----~
350
1i5 OL----~----~4-----6L----~80
o (e)
2
Strain range, %
0
Source: lD. Morrow and ER. Tuler, Low Cyc1e Fatigue Evaluation of Inconel 713C and Waspaloy (Paper No. 64 MET-15), Trans. ASME, J. Basic Eng. As published in Aerospace Structural Metals Handbook, Vol 5, Code 4208, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 17
2oo,.-------,--------,------r---::::------, 1400
.¡g :E a.
Speeimens 12.7 mm (0.5 in.) bar e10xed from turbine whee1 forging, heat treated. Cyc1ie R = -1. Heat treatment: (a): 1079 oc (1975 °P), 4 h, air eooled, + 843 oC (1550 °P), 2-4 h, force eooled, + 760 oC (1400 P), 16 h, force eooled. (b): 996-1010 oC (1825-1850 °P), 4 h, oil quenehed, + 843 oC (1550 °P), 2-4 h, air eooled, + 760 oC (1400 °P), 16 h, air eooled. (e): Same as B from different vendor. Data points indieate ha1f-life value. Composition: Ni-20Cr-14Co-4Mo-3Ti1Al. UNS N07001
''"" ~
Nickel (Ni)/665
Ni.058 Nimonic 90 nickel alloy sheet, stress-strain curves at room temperature
300 ,-------,------,------,------,------,-----.2100
250 I------+------t- 50% CR + 677 oC (1 250°F), 16h, AC
I
I
Test direction: longitudinal. Sheet thickness = 1.575 mm (0.062 in.). Strain rate = O.003/min. Sheet milI annealed with varying amounts of cold rolling (CR) and aging (air cooled, AC). Composition: Ni-20Cr-18Co-2.5Ti-1.5Al. UNS N07090
1750
1
30% CR + 704 oC (1300 °F), 16h, AC 200 ~----~----+_~--+_~~~====4-----~1400 20% CR + 732 oC (1 350°F), 16h, AC
.¡¡;
"'ui"" en
~
I
I
'" ::;: [L
I
150 1------I-:...t"'=---t-10% CR al 732 oC (1350 °F), 16h, AC
1050 ~ (IJ
No CR, 760 oC (1400 °F), 16h, AC
100 ~~~·~------~----~------~----~----~700
Source: J.R. Kattus, "Tensile and Creep Properties of Struetural Alloys under Conditions of Rapid Heating, Rapid Loading, and Short Times at Temperatures," Southem Researeh Institute, for The Intemational Niekel Co., Ine., April 1959; J.R. Kattus, "Tensile and Creep Properties of Struetural Alloys under Conditions of Rapid Heating, Rapid Loading and Short Times at Temperature," Supplementary Report by Southem Researeh Institute, for The Intemational Nickel Co., Ine., 5 June 1959. As published in Aerospace Structural Metals Handbook, Vol 5, Code 4210, CINOAS/USAF CROA Handbooks Operation, Purdue University, 1995, p 5
~~--~------~----~------~----~----_4350
°0L-----·-5L------1~0--·--~1~5------2~0----~2~5----~3~ Slrain, 0.001 in.lin.
140r------r------,--------,------,,------,------,980
Ni.059 Nimonic 90 nickel alloy sheet, tensile stressstrain curves at room and elevated temperatures
120L------r-----J~~~~~==~==~~~~~~~0 I 1110 °F (599 oC)
Test direction: longitudinal. Sheet thickness = 1.778 mm (0.070 in.). Heat treatment: 954 oC (1750 °P), 0.25 h, air cooled, + 732 oC (1350 °P), 4.5 h, air cooled. Composition: Ni-20Cr-18Co-2.5Ti-1.5Al. UNS N07090
750°F (399 oC) 1001-------+---f~~~---~1__----~------+_----~700
~ 80~-----+~hh~+_------~------4-------~----~560 ~
ui" en
::;: ui"
e
~
é'ií 60
420 é'ií
401----flW4-----~------+_----_+------+_----~280
201--~---+------+--------+------+-------~----~140
2
4
6 Slrain, 0.001 in.lin.
8
10
Souree: O.C. Hayward, "The Meehanieal Properties of Nimonic 80, 90 and 100 Sheet at Room and Elevated Temperatures," Teehnieal Note No. Met. 266, Royal Aireraft Establishment, 1957. As published in Aerospace Structural Metals Handbook, Vol 5, Code 4210, CINOAS/ USAF CROA Handbooks Operation, Purdue University, 1995, p 6
666/Nickel (Ni)
140
--
TransJers:.- _ 120
100
~ 80
'" ~ CI)
I
60
40
20
o
I
O
/
/
/
!
r
~
J- -
Longitudinal
Test direction: longitudinal and transverse. Sheet thickness = 1.778 mm (0.070 in.). Heat treatment: 954 oC (1750 °F), 0.25 h, air cooled, + 732 oC (1350 °F), 4.5 h, air cooled. Compressive yield strength: longitudinal, 896 MPa (130 ksi); transverse, 903 MPa (131 ksi). Composition: Ni-20Cr-18Co-2.5Ti-1.5Al. UNS N07090
840
700
560 ~ :2
gf !!:!
420
/
280
140
2
Ni.060 Nimonic 90 nickel alloy sheet, compressive stress-strain curves at room temperature
980
6 4 Strain, 0.001 in.lin.
8
é'ií
Source: D.C. Hayward, "The Mechanical Properties of Nimonic 80, 90 and 100 Sheet at Room and Elevated Temperatures," Technical Note No. Met. 266, Royal Aircraft Establishment, 1957. As published ín Aerospace Structural Metals Handbook, Vol 5, Code 4210, CINDASI USAF CRDA Handbooks Operatíon, Purdue University, 1995, p 6
Nickel (Ni)/667
1400
200
1400
200 10%CR
O%CR
75°F (24 OC) 1120
160
.¡¡;
---¡;
120
r----
~
U)
!!! Ci5 80
40
ji
If
1120
160 1400 °F (760 OC)
75°F (24 OC) 840 1400 °F (760 OC)
560
a.'"
.¡¡;
::¡;
~
U)
~
840
120
'"
a.
1600 °F (871°C)
::¡;
!!! Ci5
U)
80
560
!!! Ci5
1800 °F (982 oC) 1800 °F (982 OC)
5
10
280
280
~--------~5--------~10~------~15--------~2~
o
15
20
Slrain, 0.001 in.lin.
Slrain, 0.001 in.lin.
(a)
(b) 200.---------,---------,---------,---------,1400 75°F (24 OC) 20%CR
~------~~--------+_--------~--------~1120
1800 °F (982 OC)
~-If¡'-I-----+_--------+_--------_+_--------~
280
______~_________JO 10 15 20 Strain, 0.001 in.lin.
L---------L-------~--
5
Ni.061 Nimonic 90 nickell altoy sheet, stress-strain curves at various temperatures showing effects of cold working
Test direction: longitudinal. Sheet thickness = 1.575 mm (0.062 in.). Sheet exposed to rapid heating, 10 s heat time, and rapid strain rate of O.1/s. Treatment: mill annealed, varying amounts of cold rolling (CR); aging: 0% CR, 760 oC (1400 °F), 16 h, air cool; 10 and 20% CR, 732 ce (1350 °F), 16 h, air cooled. Composition: Ni-20Cr-18Co-2.5Ti-1.5Al. UNS N07090 Souree: J.R. Kattus, "Tensile and Creep Properties of Struetural Alloys under Conditions of Rapid Heating, Rapid Loading, and Short Times at Temperatures," Southem Researeh Institute, for The IntemationaI Nickel Co., Ine., April 1959; J.R. Kattus, "Tensile and Creep Properties of StrueturaI Alloys under Conditions of Rapid Heating, Rapid Loading and Short Times at Temperature," Supplementary Report by Southem Researeh Institute, for The Intemational Nickel Co., Ine., 5 June 1959. As published in Aerospace Structural Metals Handbook, Vol 5, Code 4210, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 7
668/Nickel (Ni)
Ni.062 Nimonic 90 nickel alloy sheet, stress-strain curves at various temperatures showing effecls of cold working
1960
280 30%CR
1680
240 70 'F (21 'c) 200
"¡¡; ~
I
160
~ tñ
120
///
r
1120
rf 2 !Ji
I
1600 'F (871 ,C)
/iV -
80
40
1400 'F (760 'C)
/1 V--
!Ji
1400
V--
In
840
~
560 1800 'F (982 'C) 280
5
10 Strain, 0.001 in./in.
15
o
20
(a)
1960
280 50%CR 70 'F (21 'C)
240
.¡¡;
1680
200
1400
160
1120
~
~ (f)
rf 2
!Ji (J)
!Ji (J)
120
840
80
560 1800 'F (982 'C) 280
40
00
(b)
5
10 Strain, 0.001 in./in.
15
O 20
~
Test direction: longitudinal. Sheet thickness = 1.575 mm (0.062 in.). Sheet exposed to rapid heating, 10 s heat time, and rapid strain rate of O.1/s. Treatment: mill annealed, varying amounts of cold rolling (CR); aging: 30% CR, 704 oC (1300 °P), 16 h, air cool; 50% CR, 677 oC (1250 °P), 16 h, air cooled. Composition: Ni-20Cr-18Co-2.5Ti-1.5Al. UNS N07090 Souree: J.R. Kattus, "Tensile and Creep Properties of Struetural Alloys under Conditions of Rapid Heating, Rapid Loading and Short Times at Temperature," Supp1ementary Report by Southem Researeh Institute, for The Intemational Niekel Co., Ine., 5 June 1959. As published in Aerospace Structural Metals Handbook, Vol 5, Code 4210, CINDAS/ USAF CRDA Handbooks Operation, Purdue University, 1995, p 7
Nickel (Ni)/669
gj 80 ui
/
'" jg
'"g>
60
ID
c: '6> c:
V-
.,..
100
.~
j
V
/
./
v
:2
:z
c:
"$
c: '6> c:
280 w
140
0.10
0.15 Strain
0.20
0.25
60
420
50
350
ui
'"~
1ií
g> 30
"$ c: '6> c:
w 20
10
Courtesy of Special Metals Corporation
420 ~
0.05
gj 40
Test direction: longitudinal. Sheet thickness =0.990 mm (0.039 in.). 0.2% yield strength = 345 MPa (50.0 ksi); ultimate tensile strength = 851 MPa (123.4 ksi); elongation = 54.3%. Composition: Ni-20Cr-20Co-2.15Ti . UNS N07263
jg
20
I
700
560 ~
w 40
t
Ni.063 Nimonic 263 annealed nickel alloy sheet, engineering stress-strain curve (full range)
840
120
I
V
Ni.064 Nimonic 263 annealed nickel alloy sheet, engineering stress-strain curve (expanded range)
280 ~
/ / /
:2
:z jg
210 ~ c:
.~
ID
c: '6> c:
140 w
70
1/ 2
4 Strain x 0.001
6
Test direction: longitudinal. Sheet thickness = 0.990 mm (0.039 in.). 0.2% yield strength = 345 MPa (50.0 ksi); ultimate tensile strength = 851 MPa (123.4 ksi); elongation = 54.3%. Composition: Ni-20Cr-20Co-2.15Ti. UNS N07263 Courtesy of Special Metals Corporation
670/Nickel (Ni)
140
Ni.065 Inconel 625 annealed nickel alloy sheet, engineering stress-strain curve (full range)
980
120
V
100
/
/
/'
f-""
.....- ~
/""
840
700
c..'"
:2 560
Test direction: longitudinal. Sheet thickness = 0.940 mm (0.037 in.). 0.2% yield strength = 488 MPa (70.8 ksi); ultimate tensile strength = 963 MPa (139.6 ksi); elongation = 47.1 %. Composition: 58Ni-21.5Cr-9Mo3.65Nb-5Fe-1Co. UNS N06625 Courtesy of Special Metals Corporation
gf
~
el
r:
420
'g¡ r:
'0,
r: UJ
40
280
20
140
o
O
0.05
0.10
0.15 Strain
0.25
0.20
80
"-
70
1/
60
~
50
f
g> 40
.~
al
r:
'g>
30
UJ
20
10
o
0.30
560
Ni.066 Inconel 625 annealed nickel alloy sheet, engineering stress-strain curve (expanded range)
490
Test direction: longitudinal. Sheet thickness = 0.940 mm (0.037 in.). 0.2% yield strength = 473 MPa (68.6 ksi); ultimate tensile strength = 927 MPa (134.5 ksi); elongation = 46.2%. Composition: 58Ni-21.5Cr-9Mo3.65Nb-5Fe-1Co. UNS N06625
420
I
350
/ / / /
g¡'" uf
'" ~
280 ~ r:
.~
al
210
140
70
1/ 2
4 Strain, 0.001
6
8
r:
'0,
r: UJ
Courtesy of Special Metals Corporation
Nickel (Ni)/671
.¡¡; -"
100
700
80
560
i~
60
420
40
20
l If
280
V--
Source: MIL-HDBK-5H, Dec 1998, p 6-39
ca
::!:
800 °F (4~7 OC) 1200 °F (649 OC)
~
en
a..
Test direction: longitudinal and long transverse. Sheet thickness = 1.27-6.35 mm (0.050-0.250 in.). 0.5 h exposure to temperature. Ramberg-Osgood parameters: n(room temperature) = 23; n(800 °F) = 24; n(1200 °F) = 30; n(1600 °F) = 12. Composition: 58Ni-21.5Cr-9Mo3.65Nb-5Fe-lCo. UNS N06625
1-- Room temperature
t---
t-
~
Ni.067 Inconel 625 annealed nickel alloy sheet, tensile stress-strain curves at room and elevated temperatures
j
___ 1600 °F (871°C)
140
2
4
6
8
o
10
12
Strain, 0.001 in.lin.
35
Compressive tangent modulus, GPa 70 105 140
80
1"- ...---
-
----
If
60
~
/
'" ~
40
175
Ni.068 Inconel 625 annealed nickel alloy sheet, compressive stress-strain and compressive tangent modulus curves at room temperature
560
Test direction: longitudinal and long transverse. Sheet thickness = 1.27-6.35 mm (0.050-0.250 in.). 0.5 h exposure to temperature. Ramberg-Osgood parameter: n(room temperature) = 32. Composition: 58Ni-21.5Cr9Mo-3.65Nb-5Fe-lCo. UNS N06625
420
a..
140
1/
2
4
6
8
10
Strain, 0.001 in.lin.
o
5
10
15
20
25 6
Compressive tangent modulus, 10 psi
Source: MIL-HDBK-5H, Dec 1998, p 6-39 ca
::!:
280
/
20
\
210 700
30
1
672/Nickel (Ni)
Ni.069 IN 625 nickel alloy sheet, tensile stress-strain curves at room and elevated temperatures
80r---------,---------,----------,--------, 560
Sheet thickness = 1.575 mm (0.062 in.). Heat-resistant alloy annealed at 1038 oC (1900 °F), 5 mino Strain rate = 0.005/min to yield. Composition: 58Ni-21.5Cr-9Mo3.65Nb-5Fe-1Co. UNS N06625
Room temperature
60
f----------+---~"""'---+-~---1000
°F (538 oC)
420
1400 °F (760 oC)
ro
a.
~
i
:::¡;
40
f------fhI'+------:=....¡.-~==..1600 °F
rñ
en
(871 oC)
280 ~
.!!1 ·iii e
Source: J. Huebner, "Elevated Temperature Tensile Properties of Inconel 625 Nickel-Chromium Alloy," AF33(657)-7749 and BPSN: 2 (8-7381), McDonnell, 10 Jan 1963. As published in Aerospace Structural Metals Handbook, Vol 4, Code 4117, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 31
.!!1 ·iii e
~
~
20f---H.h~-~----_+-----+_----~140
L---------~--------J---------~6---:------~80
Strain, 0.001 in./in.
~ 60 rñ
en ~
.!!1 ·iii
&40 20
Test direction: longitudinal and transverse. Sheet thickness = 3.175 mm (0.125 in.). Heat-resistant alloy annealed at 1149 oC (2100 °F), 1 h. Composition: 58Ni21.5Cr-9Mo-3.65Nb-5Fe-1Co. UNS N06625
560
80
tí
Ni.070 IN 625 nickel alloy sheet, tensile stress-strain curves at room and elevated temperatures
700
100
I
-
V P'"
ro
420 ~
rñ
en ~
---
f .--VI 2
Room temperature
tí
800°F (427 OC) I
.!!1
I
1200 °F (649 °C) ______ 280 .~ ~
-
I
I
1600 °F (871°C) 140
4
6 Strain, 0.001 in./in.
8
10
Source: "Preliminary Data Inconel Alloy 625," International Nickel Co., 1962; "Data Sheet, InconeI625," International Nickel Co., Huntington Alloy Products Division, 1964
Nickel (Ni)/673
Ni.071 IN 625 nickel alloy plate, tensile stress-strain curves at room and elevated temperatures tested in pressurized helium
1oo,-------,-------,-------,--------r-------,7oo
Heat treatment: annealed at 982 oC (1800 °F), 2 h, air cooled. Tested in 34.5 MPa (5000 psig) He. Composition: 58Ni-21.5Cr-9Mo-3.65Nb-5Fe-1Co. UNS N06625 ~
60 HIH"'------+------+-------__t_-------+------_j 420
gf
ro ~
Source: "Data Sheet, Inconel 625," International Nickel Co., Huntington AlIay Praducts Division, 1964
rñ
~
~
~
~
j~
~~
~
~
20H-------+------~-------t--------+----_j140
°OL------~--------.2'--------3L-------4L-----~50
Strain, %
100
Ni.072 Inconel 625 nickel alloy bar, typical tensile stress-strain curves at room temperature
700
80
Test direction: longitudinal and short transverse. Bar thickness = 12.7-101.6 mm (0.500-4.000 in.). RambergOsgood parameters: n(longitudinal, tension) = 27; n(short transverse, tension) = 25. Composition: 58Ni-21.5Cr9Mo-3.65Nb-5Fe-lCo. UNS N06625
560 Longludina,
I~
60 '00 -'"
~
20
Short transverse
420
:2
~
280
/
140
1/ 2
ro
11.
/
ui (f)
40
¡...
+-
4
6 Strain,
0.001 in.lin.
8
10
O
12
Cií
Source: MIL-HDBK-5H, Dec 1998, p 6--40
674/Nickel (Ni)
Compressive tangent modulus, GPa
35
70
105
140
80
"
60 "¡¡;
'\
/
-'"
ui
~"'
en
40
"/
,;,
Long/tu !na
Souree: MIL-HDBK-5H, Dec 1998, p 6-40
420
I
"'
a.
~
:;e ui
~"'
en
280
/
20
Test direction: longitudinal and short transverse. Bar thickness = 12.7-101.6 mm (0.500-4.000 in.). RambergOsgood parameters: n(longitudinal, compression) = 26; n(short transverse, compression) = 27. Composition: 58Ni-21.5Cr-9Mo-3.65Nb-5Fe-1Co. UNS N06625
560
Short transverse ~
Ni.073 Inconel 625 nickel alloy bar, typical compressive stress-strain and compressive tangent modulus curves at room temperature
21~00
175
140
1/ 4
2
o
8
10
12
20
25
30
6 Strain, 0,001 inJin,
o
10
5
15
Compressive tangent modulus, 106 psi
400
300
2800
Ni.074 IN 625 nickel alloy rod, true stress-strain curves
2100
Solid line for rod, cold drawn, annealed 982 oC (1800 °F), 1 h. Dashed line for rod hot roUed, annealed 1149 oC (2100 °F), 1 h. Composition: 58Ni-21.5Cr9Mo-3.65Nb-5Fe-lCo. UNS N06625
,....1-"
V /'
200
,/'
~
V
ui
"'~
u;
/~
ID
~
100
V
80
60
V
1400
1,/ ,,'/
"'
,/
a.
,/
:;e ui
,/
"' ~
,/
,/ ,/
700 ~
¡!:
,/ ,/ ,/
560
;
V
/
/
/'
,/
420
,/
50
350
,/ ,/ ,/
0,04
0,06
0,10
0,20
True strain, inJin,
0,40
0,60
280 1,0
Souree: "Ineonel Alloy 625," International Nickel Co., Huntington AlJoy Produets Div., 1970. As published in Aerospace Structural Metals Handbook, Vol 4, Code 4117, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 25
Nickel (Ni)/675
Ni.075 IN 625 cast nickel alloy, tensile stress-strain curves at room and elevated temperatures tested in pressurized helium
8o.-------,-------,-------,--------,-------,56o
Heat treatment: annealed at 1149 oC (2100 °F), 2 h, force cooled. Tested in 34.5 MPa (5000 psi gage) He. Composition: 58Ni-21.5Cr-9Mo-3.65Nb-5Fe-l Co. UNS N06625
75°F 24 OC) 60~------+-------~---~
__~~----_r------~420 600°F (316 OC)
~
~'"
900°F (482 OC)
rñ
uf
gj 2~ 40
I1--::7--::j::::::::=-L====+==~~)7f7s:;:Cl1280 1200 °F (649 OC)
'"
2~
"00
"0
~
~
e
Souree: J. Mueci and J.A. Harris, Jr., "Influenee of Gaseous Hydrogen on the Meehanieal Properties of High Temperature Alloys," NASA CR149962, United Teehnologies Corp., 1976, p II-3. As published in Aerospace Structural Metals Handbook, Vo14, Code 4117, CINDAS/ USAF CRDA Handbooks Operation, Purdue University, 1995, p 32
e
20~------+-------~-------~------_r------~140
r,
4
3
<.
Strain, %
120
100
~ 80 ID
~
g> 60
.~
ID
e .c, e llJ
Ni.076 Incoloy 800 annealed nickel alloy sheet, engineering stress-strain curve (full range)
840
/
/
/
~
J-.---- +-
-
700
560
~
:;¡;
1
420 ~ e
"$ e
.¡;'
40
280
20
140
0.05
0.10
0.15 Strain
0.20
0.25
o
0.30
e llJ
Test direction: longitudinal. Sheet thickness = 1.193 mm (0.047 in.). 0.2% yield strength = 330 MPa (47.8 ksi); ultimate tensile strength = 665 MPa (96.5 ksi); elongation = 36.1 %. Composition: 33Ni-21Cr-OATi-OAAl-bal Fe. UNS N08800 Courtesy of Special Meta1s Corporation
676/Nickel (Ni)
60
420
50
350
._ 40
g;¡
~
ig' 30 .~ (])
c:
"g> UJ
20
10
.....
(
280
/ / /
Ni.077 Incoloy 800 annealed nickel alloy sheet, engineering stress-strain curve (expanded range)
~
Test direction: longitudinal. Sheet thickness = 1.193 mm (0.047 in.). 0.2% yield strength = 327 MPa (47.4 ksi); ultimate tensile strength = 649 MPa (94.1 ksi); elongation = 36.7%. Composition: 33Ni-21Cr-0.4Ti-0.4Al-balFe. UNS N08800
:2
Courtesy of Special Metals Corporation
~ ~
210 ~ c:
"$ c:
'0,
140
c:
UJ
70
1/ 4
2
8
6
Strain x 0.001
Ni.078 Incoloy 800H nickel alloy bar, isochronous stress-strain curves at 649 oC (1200 °F)
210
30
-----
Monotonic curve from Case 1592. Other curves constructed from monotonic curve and creep data relations from M.K. Booker, v,E. Baylor, and B.L.P. Booker, "Survey of Availab1e Creep and Tensile Data for Alloy 800H," ORNLITM-6029, 1978. Composition: 32Ni-21Cr-0.75Mn-0.05C-bal Fe. UNS N08810
Monoto~
25
20 ~ tñ
'"~
15
ii5
10
175
¡--
~
~/
tV
l.---""
V-
~
1dh
140 ro
a..
:2
105 ",-
'"
5
~
10 h
~
ii5
¡--
70
35
5
0.4
0.8
1.2 Strain, %
1.6
2.0
o
2.4
Source: ASME Boiler and Pressure Vessel Code Case 1592, Section VIII, 1977, 1, P 63. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1615, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 11
Nickel (Ni)/677
25
~
20
V--
(
.¡¡;
"",,; '" ~
Ni.079 Incoloy 800H nickel alloy bar, isochronous stress-strain curves at 704 oC (1300 °F)
210
30
---
Monotonic
140 C\l
a..
-
15
10
I?-
5
Monotonic curve from Case 1592. Other curves constructed from monotonic curve and creep data re1ations from M.K. Booker, V.B. Bay1or, and B.L.P. Booker, "Survey of Avai1ab1e Creep and Tensile Data for Alloy 800H," ORNLITM-6029, 1978. Composition: 32Ni-21Cr-O.75Mn-O.05C-bal Fe. UNS N08810
175
¡--
V--
~
~
::2
10"h
105 ,,;
~
Source: ASME Boiler and Pressure Vessel Code Case 1592, Section VIII, 1977, 1, P 63. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1615, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 11
70 10" h
f--
35
0.4
0.8
1.2
1.6
O
2.0
2.4
Strain, %
30
25
20
(
.¡¡;
"",,;
'" ~
Ni.080 Incoloy 800H nickel alloy bar, isochronous stress-strain curves at 760 oC (1400 °F)
210
15
V
V--
~
140 C\l
a..
::2
105
10
~
5
.........
~
70
-
3
10 h
10" h
35
Vo
O
Monotonic curve from Case 1592. Other curves constructed from monotonic curve and creep data re1ations from M.K. Booker, V.B. Bay1br, and B.L.P. Booker, "Survey of Avai1ab1e Creep and Tensile Data for Alloy 800H," ORNLITM-6029, 1978. Composition: 32Ni-21Cr-O.75Mn-O.05C-ba1 Fe. UNS N08810
175
0.4
0.8
1.2 Strain, %
1.6
2.0
O
2.4
ui
~
Source: ASME Boiler and Pressure Vessel Code Case 1592, Section VIII, 1977, 1, P 63. As published in Aerospace Structural Metals Handbook, Vol 2, Code 1615, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 11
678/Nickel (Ni)
140
980
120
840
100
~ Vi ~ 80
/'
1ií Cl
e
.~ 60
e .0, e
V
~
----
:2
Courtesy of Special Metals Corporation
700
a.
560
li ~
Cl
e
420 .~ e e
.0, llJ
40
280
20
140
o
0.05
O
0.10
0.15 Slrain
0.20
0.25
o
0.30
70
490
60
420
I /
50
~ Vi
~ 40 1ií Cl
e "ij5
:g
ro
Test direction: longitudinal. Sheet thickness = 0.965 mm (0.038 in.). 0.2% yield strength = 419 MPa (60.8 ksi); ultimate tensile strength = 878 MPa (127.4 ksi); elongation = 56.5%. Composition: Ni-21Cr-16Mo-5 max Fe-3.7W. UNS N06686
~
llJ
.0,
Ni.081 Inconel 686 annealed nickel alloy sheet, engineering stress-strain curve (full range)
30
e
llJ
20
10
ro
Test direction: longitudinal. Sheet thickness = 0.965 mm (0.038 in.). 0.2% yield strength = 411 MPa (59.6 ksi); ultimate tensile strength = 848 MPa (123.0 ksi); elongation = 56.1%. Composition: Ni-21Cr-16Mo-5 max Fe-3.7W. UNS N06686
:2
Courtesy of Special Metals Corporation
350
a.
280
/ / /
V
Ni.082 Inconel 686 annealed nickel alloy sheet, engineering stress-strain curve (expanded range)
li ~
1ií Cl
e
210 .~ e
.0,
e
llJ
140
70
2
4 6 Strain x 0.001
8
o
10
Nickel (Ni)/679
70~------,--------,--------~------,---------,490
Ni.083 IN 617 nickel alloy sheet, tensile stress-strain curves at room and elevated temperatures
60 1-____-l-_ _ _-+ ___==-..¡..._~~75 °F (24 OC)
Sheet thickness = 1.194 mm (0.047 in.). Cold roUed and solution treated. Solid lines, longitudinal direction; dashed lines, transverse direction. Composition: Ni-22Cr12.5Co-9Mo-l.5Fe-l.2Al. UNS N06617
420
50~-----~~----4------~----4--------1350
'iii ~
-<
--- 800 °F (427 OC)
40 ~----_t+~~..;::J;:;::;:;;;:t;.;::;;;~1200 °F (649 OC)
-
--
I
280
/f ~ u)
(/l-
E
en 30
210
~ ro
Source: O.L. Deel, "Engineering Data on New Aerospace Structural Materials," AFML-TR-75-97, Battelle-Columbus Laboratories, June 1975. As published in Aerospace Structural Metals Handbook, Vol 5, Code 4215, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 18
1_-J~~~--~~~:-======i=~1:60:0~O~F¡(8~71~O~C~)--~ 140
20~
2
O
______
8
6
~
_ _ _ _ _ _ _ _ _L __ _ _ _ _ _
4
~
______
~
L -_ _ _ _ _ _
~
10~~--+_----4-----~---~----~70
10
Sll-ain, 0.001 in./in.
N i.084 IN 617 nickel alloy sheet, compressive stressstrain curves at room and elevated temperatures
80r-------~--------r--------r_------,_--------560
70~------~--------e--------~~
__--4_------_1490
60~-----+_--~~~~----~----~----~420
'iii
__
/f
800 °F (427 oC)
~- 50 1--------'.+-----:c::rI"c....::.-------~------4_------_1 350 ~
m
w
~
~
-___--1"-=--:::. 1200 °F (649 OC)
~ 40
280 ~ ~
1 ~
(/)
c.
__ __
-- -
~
1600 °F (871 OC)
15 30
210 E
8
ü 20~~~~-4_-------~------~~------+_------~140
10~~----+_----~~----~-----~---_470
2
4 6 Slrain, 0.001 in./in.
8
Sheet thickness = 1.194 mm (0.047 in.). Cold roUed and solution treated. Solid lines, longitudinal direction; dashed lines, transverse direction. Composition: Ni-22Cr12.5Co-9Mo-1.5Fe-1.2Al. UNS N06617 Source: O.L. Deel, "Engineering Data on New Aerospace Structural Materials," AFML-TR-75-97, Battelle-Columbus Laboratories, June 1975. As published in Aerospace Structural Metals Handbook, Vol 5, Code 4215, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 20
680/Nickel (Ni)
120
Ni.085 Inconel 617 annealed nickel alloy sheet, engineering stress-strain curve (full range)
840
V-
~
100
~ 80
:i
~ 1;)
g> 60 "fE al
e '¡¡' e W
v
/ /
/
700
/
560
~
2 ui
Test direction: longitudinal. Sheet thickness = 1.524 mm (0.060 in.). 0.2% yield strength = 361 MPa (52.3 ksi); ultimate tensile strength = 857 MPa (124.3 ksi); elongation =52.8%. Composition: 44.5Ni-22Cr-13Co9Mo-3Fe. UNS N06617 Courtesy .of Special Metals Corporation
~
420 ~ e
.~
al
e e
'¡¡'
40
280 W
20
140
0.10
0.05
0.15 Slrain
60
.-------
50
(
~ 40 ~ 1;)
g> 30
al
e e
'¡¡'
W
20
10
0.25
---
o
0.30
Ni.086 Inconel 617 annealed nickel alloy sheet, engineering stress-strain curve (expanded range)
420
350
ro
280~
/
ui en
.~
0.20
ui
~
Cl
210.§
/ /
al al
e e
'¡¡' W
140
70
l
2
4 6 Slrain x 0.001
8
Test direction: longitudinal. Sheet thickness = 1.524 mm (0.060 in.). 0.2% yield strength = 361 MPa (52.3 ksi); ultimate tensile strength = 847 MPa (122.8 ksi); elongation = 52.8%. Composition: 44.5Ni-22Cr-13Co9Mo-3Fe. UNS N06617 Courtesy of Special Metals Corporation
Nickel (Ni)/681
120
840
100
700
v
._ 80 en -'"
/ /'
en ~
1ií Cl
<:
60
.,
"55
<:
'0> <:
W 40
,/
~
./
'" 560 a. ::2:
E
/
<: <:
'0>
280
30
~
1ií Cl
<:
.,
"55
.§¡
20
<: W
10
<:
w
140
0.10
0.15 Strain
0.20
0.25
o
0.30
350
50
¡:f
Courtesy of Special Metals Corporation
"5i.,
0.05
~
Test direction: longitudinal. Sheet thickness = 0.965 mm (0.038 in.). 0.2% yield strength = 312 MPa (45.3 ksi); ultimate tensile strength = 748 MPa (108.5 ksi); elongation = 49.8%. Composition: 47.5Ni-21.75Cr18.5Fe-0.6W. UNS N06002
420 ~
20
40
Ni.087 Inconel HX annealed nickel alloy sheet, engineering stress-strain curve (full range)
I
V280
I I I
Ni.088 Inconel HX annealed nickel alloy sheet, engineering stress-strain curve (expanded range)
Test direction: longitudinal. Sheet thickness = 0.965 mm (0.038 in.). 0.2% yield strength = 316 MPa (45.8 ksi); ultimate tensile strength = 738 MPa (107.0 ksi); elongation = 51.0%. Composition: 47.5Ni-21.75Cr18.5Fe-0.6W. UNS N06002 Courtesy of Special Metals Corporation
70
I
2
4
6 Strain x 0.001
8
o
10
682/Nickel (Ni)
Ni.089 Hastelloy X nickel alloy sheet, typical tensile stress-strain curves at room and elevated temperatures
6o,-----,------,-----,------,-----,------,42o Room temperature
I
50 1-----_f_--7"'-'-+---::±..__400 'F (204 'C)--t----; 350
I
~_-r---
800 'F (427 'C) 1000 °F (538 'C)
40~-~~~~~__~~~~12~0;0~'F~(;64;9~';C~)--~280 1400 °F (760 'C)
&
~ gf 30 I------/j'fl--+---+--___+---;-=~+.::::-:_:_::::--_+_--____i 210 ~--r
Q)
~
1600 'F 871 'C)
:2
ui UJ
~
Test direction: longitudinal and long transverse. 0.5 h exposure to temperature. Ramberg-Osgood parameters: n(room temperature) = 10; n(400 °F) = 13; n(800 °F) = 15; n(lOOO °F) = 18; n(1200 °F) = 19; n(400 °F) = 15; n(1600 °F) = 12; n(1800 °F) = 7.7; n(2000 °F) = 3.8. Composition: Ni-22Cr-18Fe-9Mo-1.5Co-0.5W. UNS N06002 Source: MIL-HDBK-5H, Dec 1998, p 6-25
201--~--f---+-----f---r----+---~140
~i----
1800 'F (982 'C)
I
I
10 ,,'----i-=::j:;;;=---2000 'F (1093 °C)----f------j 70
°0L---~2---4L---~6----L8--~10---~1f
Strain, 0.001 in.lin.
35
Compressive tangent modulus, GPa 70 105 140
Ni.090 Hastelloy X nickel alloy bar, typical compressive stress-strain and compressive tangent modulus curves at room and elevated temperature
175
Specimens were exposed to temperature 0.5 h. RT, room temperature. Ramberg-Osgood parameters: n(RT) = 6.9; n(700 °F) = 6.7; n(900 °F) = 5.6. Heat-resistant aHoyo Composition: Ni-22Cr-18Fe-9Mo-1.5Co-0.5W. UNS N06002 Source: MIL-HDBK-5H, Dec 1998, p 6-26
~
~
gf 30 I---f++_f_-"""""-+-"""";::-I---r--~O+__--~ 210 gf ~
~
ro
ro 20~~--+----+--___+--~~-~~--~140
10~--+----r--_+---r_---f-~-~70
o
2
4
5
10
6 8 Strain, 0.001 in.lin. 15
20 6
Compressive tangent modulus, 10 psi
10
0 12
25
30
Nickel (Ni)/683
Ni.091 Hastelloy X solution treated nickel alloy bar, tensile stress-strain curves at room and elevated temperatures
6or------r-----,------,-----~------~----_,420
70°F (21°C) 50~----~----~~----~~~~------+_----_1350
40
~----~---/'~'--
1200 °F (649 OC) 280
...-t-::::::::~:::::::f:....---r
~
Bar thickness: 19.05 mm (0.75 in.). Composition: Ni-22Cr-18Fe-9Mo-1.5Co-0.5W. UNS N06002
~
1400 °F (760 OC) ::¡; ~ 30 f-------hl'W------7'~------+__----_+------+_----____j 210 ~
E
~
Source: C.E. laske et al., "Low-Cycle Fatigue of Type 347 Stainless Steel and Hastelloy Alloy X in Hydrogen Gas and in Air at Elevated Temperatures," NASA-CR-135022, May 1976. As published in Aerospace Structural Metals Handbook, Vol 4, Code 4112, CINDAS/ USAF CRDA Handbooks Operation, Purdue University, 1995, p 14
ro
(/J
20~---m~~----~~----~----_+------+_----_1140
f-~---~----~f-----+__----_+------+_----____j70
L-----~----~2----~3------~4------5~--~60
Strain, 0.001 in./in.
100
~
80
V
L~/
~ ~
60
~
;¡; Ol
c:
.~
ID
.§,
40
c:
w
Ni.092 Inconel 601 annealed nickel alloy sheet, engineering stress-strain curve (full range)
700
/ /
560
c.. '"
420
V
~
I
g>
.~
280 ~
.~
w
20
140
0.05
0.10
0.15 Strain
0.20
0.25
o
0.30
Test direction: longitudinal. Sheet thickness = 1.27 mm (0.050 in.). 0.2% yield strength = 239 MPa (34.6 ksi); ultimate tensile strength = 657 MPa (95.3 ksi); elongation =48.2%. Composition: 60.5Ni-23 Cr-bal Fe. UNS N06601 Courtesy of Special Metals Corporation
684/Nickel (Ni)
Ni.093 Inconel 601 annealed nickel alloy sheet, engineering stress-strain curve (expanded range)
280
40
í
30
ro
Test direction: longitudinal. Sheet thickness = 1.27 mm (0.050 in.). 0.2% yield strength = 243 MPa (35.2 ksi); ultimate tensile strength = 652 MPa (94.6 ksi); elongation = 47.7%. Composition: 60.5Ni-23 Cr-bal Fe. UNS N06601
:2:
Courtesy of Special Metals Corporation
~~ 210
I
a..
ui
'"~
140
I
~ e
.~ Q)
e c:
'c, llJ
70
10
11 4
2
8
6
Strain. 0.001
140
v---
120
100
80
700 ro
a..
:2:
560 gf
~
/
tí el
e
'$e
840
/
~ ui ~
Ni.094 Monel K-500 age-hardened nickel alloy 36 mm (1.4 in.) diam rod, engineering stress-strain curve
980
60
el
e
420
/ /
'c, e
llJ
40
20
o
O
'$e
'c, e
llJ
280
140
/
5
10 Strain xO.001
15
Test direction: longitudinal. 0.2% yield strength = 740 MPa (107.3 ksi), ultimate tensile strength = 1118 MPa (162.2 ksi); elongation = 25.6%; reduction in area = 46%; modulus of elasticity = 179 GPa (26.0 X 106 psi). Composition: 66Ni-29Cu-3AI-0.5Ti. UNS N05500 Courtesy of Special Metals Corporation
Nickel (Ni)/685
140
-423 °F (-253 oC)
v:=
120
J
100
]l 80
J
E en 60 40
20
I
/
J
Y
~
Ni.095 Monel K-500 annealed and aged nickel alloy sheet, tensile stress-strain curves at room and low temperatures
980
840
Sheet thickness = 1.27 mm (0.050 in.). Composition: 66Ni-29Cu-3AI-0.5Ti. UNS N05500
I-::;;;""°F (-196 oC)
~
'1 Room temperature
700
560 ~ ~
Source: E.H. Schmidt, "Fatigue Properties of Sheet, Bar and Cast Metallic Materials for Cryogenic App1ications," Report No. R-7564, Rocketdyne, 30 Aug 1968, p K-9; See Also NASA Tech. Brief 7010199. As pub1ished in Aerospace Structural Metals Handbook, Vo14, Code 4116, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 17
C/)
~
ro
420
~
280
140
V
o
2
O
4
3
5
6
Strain, 0.001 in.lin.
200
1400
160
1120
120
840
'00
"'
Ni.096 Monel K-500 age-hardened nickel alloy, coldrolled product, tensile stress-strain curves at room and low temperature
Composition: 66Ni-29Cu-3AI-0.5Ti. UNS N05500
o..'" ~
C/)
~
C/)
~
ro
560
80
40r---r,r~------+------~------~------r-----~280
2
4
6 Strain, 0.001 in.lin.
8
10
ro
Source: D.N. Gideon, RJ. Favor, A. Koppenhafer, HJ. Grovem, and G.M. McC1ure, "Investigation of Notch Fatigue Behavior of Certain Alloys in the Temperature Range of Room Temperature to -423F)," ASD-TDR-62-351, Aug 1962, p 13. As pub1ished in Aerospace Structural Metals Handbook, Vo14, Code 4116, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 17
686/Nickel (Ni)
200
160 .¡¡;
""ui
E!
120
Ni.097 Monel K-500 nickel alloy bar, tensile stressstrain curves at room and low temperatures
1680
240
.....-
--
¡..--~~ ..---::
~
-42rF (-253 oC)
Bar specimen (3.658 mm, or 0.144 in., diam) taken from 19.05 mm (0.75 in.) diam bar aged at 593 oC (1100 °F), 21 h, + 538 oC (1000 °F), 8 h, air cooled. Composition: 66Ni-29Cu-3AI-0.5Ti. UNS N05500
1400 - \ -320 ¡)(-196 oC)
v---
\
-110 °F (-79 oC)
1120 ro
a.
80 °F (27 OC)
:2
840
Uí
ui
~
Source: K.A. Warren and R.P. Reed, Tensile and Impact Properties oi Selected Materials from 20 to 300K, Monograph 63, National Bureau of Standards, 28 June 1963. As published in Aerospace Structural Metals Handbook, Vol 4, Code 4116, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 18
Uí 80
560
40
280
0.08
0.16
0.24
0.32
o
0.40
Strain in.lin.
Ni.098 Monel K-500 cold drawn and aged nickel alloy bar, true stress-strain curves at various temperatures
400 .------¡----,-------¡----,-------¡-------, 2800
3601-----+---t-----+--~
2520
Bar diameter = 6.35 mm (0.25 in.). Specimen gage length = 31.75 mm (1.25 in.). Composition: 66Ni-29Cu-3Al0.5Ti. UNS N05500
320 I----_+---t__--_+--?~t__----t-:==---'-I 2240
~
ro
2801----_+---t__--7"'----b"L---t__---+'=..-_'__j 1960
~-
~ cñ
~
~ 00 1680 ~
~
~ 240
~
~
2001---~~~~-~~-_+---t__--_+--_'__j1400
160 hf:H'--7Lt----t__--_+---t----+--_'__j 1120
1200L----OL.1---0L.2------0L.3------0L.4----~OL.5----~0.~40 True strain, in.lin.
Source: E.B. Kula and T.S. DeSisto, "Plastic Behavior of Metals at Cryogenic Temperatures," Technical ReportAMRA TR 65-32, Materials Engineering Division, U.S. Army Materials Research Agency, p 3. As published in Aerospace Structural Metals Handbook, Vol 4, Code 4116, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 18
Nickel (Ni)/687
260
240
/"
220
g¡
V--
(;
200
......
-------*'"
-
---
1820
Ni.099 Monel K-500 nickel alloy wire, stress-slrain curves al -196 oC (-321°F) for hydrogen-free and hydrogenated wire
1680
Wire diameter =0.711 mm (0.028 in.). Treatment: 527 oC (980°F), 8 h, + slow coo1ed (8.3-13.9 °C/h, or 15-25 F/h) to 482 oC (900°F), ultimate strength = -1275 MPa (-185 ksi), cathodically charged for 96 h at 0.16 amps/cm2 (1 amp/in. 2) in 80 oC (176 °F) e1ectro1yte of 4% su1furic acid poisoned with sodium arsenate to saturation and baked 488 oC (910 °F), 4 min, water quenched. Strain rate = 2.2 x lO--4/s. Composition: 66Ni29Cu-3A1-0.5Ti. UNS N05500
I
-
300 ppm H2 1
H2 Free
-- --- --
1540
1400
I
gf
I
~
1260
160
1120
140
980
O
'" en
en 180
120
fE ~
I
20
40
60 80 Strain, 0.001
120
100
480
~
Source: W.M. Cain, C.C. Koch, J.L. Mihelich, and A.R. Troiano, "Solute Induced Embrittlement in Steel and Severa! Face-Centered Cubic Alloys," Report ARL 64-101, Aerospace Research Laboratories, June 1964, p 40. As published in Aerospace Structural Metals Handbook, Vol 4, Code 4116, CINOASfUSAF CROA Handbooks Operation, Purdue University, 1995, p 18
840 140
Ni.100 Monel K-500 nickel alloy plate, cyclic stressslrain curve
3360
/0
/'
400
°V
/o
320 ~ al Ol c: ~
240
en en
!!!
/
iñ
160
/
80
o
/
O
/
//
2240
Vo
fE
~
.;
1680
'"~ en en
!!!
iñ 1120
~ 0.4
2800
560
0.8
1.2 1.6 Strain range, %
2.0
O
2.4
P1ate thickness = 25.4 mm (1 in.). Specimen heat treated to ultimate strength, 1172 MPa (170 ksi); yie1d strength, 862 MPa (125 ksi); e1ongation in 2 in., 24%; reduction in area, 36%. Data points from 10w-cycle fatigue (LCF) tests. Curve generated from LCF and modu1us of e1asticity (E = 1796 GPa, or 26 x 106 psi). Composition: 66Ni-29Cu-3A1-0.5Ti. UNS N05500 Source: M.R. Gross, "Low-Cycle Fatigue of Materials for Submarine Construction," NAVENGRXSTA Report 91 1970,14 Feb 1963, p A-7. As published in Aerospace Structural Metals Handbook, Vol 4, Code 4116, CINDASfUSAF CROA Handbooks Operation, Purdue University, 1995, p 27
688/Nickel (Ni)
70
./"
60
V'
30
20
10
B
420
-C D
E
350
-F
/'
/~
CIl
en
-~
J~ - - - -
40
"'
~
/~ tr-::
50
.¡¡;
Ni.101 ID nickel alloy sheet, tensile stress-strain curves at room temperature
490 A
! /
V
--
280
& ::¡;
G
~ 210 1'ií
1--- 3.75 ---..¡
~ %R
o~IF6-
140
70 - - Longitudinal - - Tr¡nSVerse 2
4 6 Strain, 0.001 in./in.
8
o
10
Ni.102 ID nickel alloy sheet, tensile stress-strain curves at room and elevated temperatures
350
Sheet was stress relieved and tested in longitudinal (L) and transverse (T) directions. Composition: Ni-2Th0 2
70 'F (21 'C) 40
280
30
210
ro
o-
::¡;
"'
'" ~
1600 'F (871 'C), L, T
en
Source: C.R. Manning, Jr. et aL, "An Investigation of a New Nickel Alloy Strengthened by Dispersed Thoria," NASA Technical Note D1944, 1963. Calorized data from R.M. Bums and w,w, Bradley, Protective Coatingsfor Metals, Rhinehold Publishing, 1955. As published in Aerospace Structural Metals Handbook, Vol 4, Code 4115, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 9
~
50
.¡¡;
Sheet thickness = 0.635-1.27 mm (0.025-0.050 in.). Specimen tested in longitudinal or transverse directions after various conditioning: A and B, as received; C and D, preoxidized, 1316 oC (2400 °F), 24 h; E, F, G calorized; E, unexposed; F, 1204 oC (2200 °F), 192 h; G, 1316 oC (2400 °F), 88 h. Composition: Ni-2Th0 2 . Dimensions in inset given in inches (1 in. =25.4 mm)
140
20 1800 'F (982 'C), L, T
70
10
°0L---------0~.-2---------0~.4~------~0~.6~------~0.~
Strain, %
en
Source: O.L. Deel and W.S. Hyler. "Engineering Data on Newly Developed Structural Materials," AFML-TR-67-418, Apri11968, P 54. As published in Aerospace Structural Metals Handbook, Vol 4, Code 4115, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, P 11
Nickel (Ni)/689
Ni.l03 ID nickel alloy sheet, tensile stress-extension curves at elevated temperatures
140
20 1700 °F (927 OC)
Sheet thickness =0.635-1.27 mm (0.025-0.050 in.). Composition: Ni-2Th02 • Dimensions in inset given in inches (1 in. =25.4 mm)
112
16
84
12 '00
r--- ---1 ~ 0~}.6
..><
~
1ñ 8
%R
~
rñ
Vl
56
I
2400 °F (1316 OC) 4
2500 °F (1371 OC)
28
°O~--------~--------~---------L---------JO
4
8
12
Motíon betweEm crossheads, 0.001 ín.lín.
a.'" ~
3 .75
rñ
Vl
16
~
Source: C.R. Manning. Jr. el al., "An Investigation of a New Nickel Alloy Strengthened by Dispersed Thoria," NASA Technical Note D-1944, 1963. As published in Aerospace Structural Metals Handbook, Vol 4, Code 4115, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 11
690/Nickel (Ni)
70
490
Ni.104 TD nickel alloy bar (a) and sheet (b), stressstrain curves at room and elevated temperatures
420
Bar 12.7 mm (0.5 in.) diam, as received. Recrystallized sheet 0.508 mm (0.020 in.) thick, 1300 oC (2372 °P), 3 h. Tested at strain rate of 0.000167/s. Composition: Ni-2Th0 2
77 'F (25 'C)
60 '00
ro
o..
256 'F (124 'C)
-'" ui
::¡; ui
'" ~
'"~
50
40
ro 350
482 'F (250 'C)
280 (a)
60
350
40
210
ro
o..
'00
::¡;
-'" ",-
ui
~'" (/)
'"~
140
30
932 'F (500 'C) 1112 'F (600 'c) 1292 'F (700 'C) 70
20 1472 'F (800 'C)
10
0 (b)
3 Elongation, %
2
4
5
O
ro
Source: B.A Wilcox and AH, Clauer, "High Temperature Deformation of Dispersion Strengthened Nickel Alloys," NASA CR-72367, 29 Feb 1968, P 11. As published in Aerospace Structural Metals Handbook, Vol 4, Code 4115, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p II
Nickel (Ni)/691
Ni.l05 TD nickel alloy sheet, compressive stressstrain curves at room and elevated temperatures
350
50
280
Stress relieved and tested in longitudinal (L) and transverse (T) directions. Composition: Ni-2ThO z
210
Source: O.L. Deel and W.S. Hyler, "Engineering Data on Newly Developed Structural Materials," AFML-TR-67-418, Apri11968, P 54. As published in Aerospace Structural Metals Handbook, Vol 4, Code 4115, CINDAS/USAF CROA Handbooks Operation, Purdue University, 1995, P 17
L 40
.¡¡;
30
ro
c..
"'vi"
~
vi
U)
U)
~ C/)
~ C/)
1600 °F (871°C), L, T
20
140
1800 °F (982 OC), L, T
I
2000 °F (1093 OC), L, T 70
10
ooL---------o~.2------·---0J.4----------0.L6---------J0.~
Strain, %
Ni.l06 TD nickel alloy sheet and bar, stress-plastic strain curves in bending with effect of vacuum annealing at various temperatures
70 ,-------,-------,-------,--------,-------,490 2000 °F (1093 OC) 60
r-------~------~·----~~~------~-------4420
50
r-------~~--~~·--------~=_~~4_-------4350
ro
.¡¡;
"'vi" U)
~
c.. ~
40 r-----"A---~L-~·--------r-------~~~----1280
~
1ií
ID .c
¡¡::
2
~
1ií
Bar 30 r---t+--A---~~~·--------r-------~--------1210
~
~
.l!l :::1
:::1
O
O
20
r- f---
r-~~~~------~·--~----r-------4--------4140
0.025-1
O1
10
1.375
---1
Loaded in bending
11
75
70
L-----~~----~· __-----J------~------~O
00
0.004
0.008 Plastic strain, %
0.020
0.635 mm (0.025 in.) sheet (solid curve) and machined bar (dashed curve) vacuum annealed at temperature indicated for 1 h. Composition: Ni-2ThOz' Dimensions in inset given in inches (1 in. = 25.4 mm) Source: J.E. White and R.D. Carnaban, A Microplasticity Study of Dispersion Strengthening in TD Nickel, AIME Trans., Vol 230, Oct 1964, p 1300. As published in Aerospace Structural Metals Handbook, Vol 4, Code 4115, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 10
692/Nickel (Ni)
Ni.107 ID nickel alloy bar, stress-plastic strain curves in bending with effect of cold rolling followed by vacuum annealing
6o.-------,-------,-------.-------,---=---~420
~
40 1-----------f#'------o7""f---':c.::c.---t-------+--------1 280 ro
~
~
m
~lB
ª
.2)
o~
~
30 l------h'---r-------b..--""=-t------+--------121 o 1/) 50% (Recrystallized during 1500 °F (816 OC) anneal) ::
2
Bar extruded at 1204 oC (2200 °F). Reduced by rolling at percentage indicated then vacuum annealed 816 oC (1500 °F), 1 h. Composition: Ni-2Th0 2 • Dimensions in inset given in inches (1 in. = 25.4 mm) Source: J.E. White and R.D. Carnahan, A Microplasticity Study of Dispersion Strengthening in TD Nickel, AIME Trans., Vol 230, Oct 1964, p 1302. As published in Aerospace Structural Metals Handbook, Vol 4, Code 4115, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 10
.2) ~
201----~----+-------+------+-------+---------11400
-1 10~------+-------+-
¡'-0.025-0.040
OIr---
Ir -------1
75
1.375
70
Loaded in bending
0.004
0.008 Plastic strain, %
80
~
~
60
1ií Ol
e "55
(J)
.§, 40 e
UJ
Ni.108 Monel400 annealed nickel alloy sheet, engineering stress-strain curve (full range)
700
100
I
/
/
----
560
ro
o.. 420
~ 1/) 1/)
~
1ií Ol
e
"53
280 ~
'5l e
UJ
140
20
0.05
0.10
0.15 Strain
0.20
0.25
o
0.30
Test direction: longitudinal. Sheet thickness =0.432 mm (0.017 in.). 0.2% yield strength = 281 MPa (40.8 ksi); ultimate tensile strength = 612 MPa (88.7 ksi); elongation = 38.0%; strength coefficient (K) = 196.4; strainhardening exponent (n) =0.385. Composition: 63Ni-30Cu-2.5Fe. UNS N04400 Courtesy of Special Metals Corporation
Nickel (Ni)/693
,....
40
gf 30
Test direction: longitudinal. Sheet thickness =0.432 mm (0.017 in.). 0.2% yield strength = 268 MPa (38.9 ksi); ultimate tensile strength = 563 MPa (81.7 ksi); elongation = 38.0%. Composition: 63Ni-30Cu-2.5Fe. UNS N04400
280
/
~
'"
O-
'"e
Courtesy of Special Metals Corporation
210 :2_ UJ
1/
~
~
Ol
e "55
/
.~
al
.§,
Ni.109 Monel 400 annealed nickel alloy sheet, engineering stress-strain curve (expanded range)
350
50
20
140 ~
'0,
/
e
LU
10
e
LU
70
1/
3
2
4
5
7
6
8
o
Strain, 0.001
160
140
/
120
I
100
I/
""
----
---¡---
75 'F (24 'C) 980
Composition: Ni-35Fe-13Cr-6Mo-2.5Ti. UNS N09901
--
840
700
'"
O-
:2
560 rñ
~
420
~
40
280
D
140
11 0.5
Source: DMIC Data Sheet 6803-005, March 1968. As published in Aerospace Structural Metals Handbook, Vol 4, Code 4107, CINDAS! USAF CRDA Handbooks Operation, Purdue University, 1995, p 5
1200 'F (649 'C)
1/
60
20
V
Ni.110 Incoloy 901 solution treated and aged nickel alloy bar, stress-strain curves at room and elevated temperature
1120
1.0
1.5
2.0 Strain, %
2.5
3.0
o
3.5
694/Nickel (Ni)
150
Heat-resistant alloy at room temperature (creep rupture heat treatment). Composition: Ni-37Pe-16Cr-2.9Nb1.8Ti. UNS N09706
1400
200
~
Ni.111 Inconel 706 nickel alloy bar and sheet, typical tensile stress-strain curve (full range)
1750
250
~ ,../'"
¡...---
-'" IX
Source: MIL-HDBK·5H, Dec 1998, p 6-50 1050
l'
'"
c.. ::¡;
rñ CJ)
rñ
CJ)
~
~ (J)
(J)
100
700
50
350
0.05
0.10
0.15
0.20
0.25
o
0.30
Strain, in./in.
Ni.112 Inconel 706 solution treated and aged nickel alloy forged bar, typical tensile stress-strain curves at room and elevated temperature
1400
200
Room temperature
160
1120
120
840
'"
c.. ::¡;
~ <ñ CJ)
u;
'"~
~
560
80
40~--~~-----r----~------r-----~-----i280
ooL-----~2------4L-----~6------8~----~10~--~1~ Strain, 0.001 in./in.
Uí
Test direction: longitudinal and long transverse. Bar thickness = 50.8 mm (2.000 in.). Creep rupture heat treatment and 0.5 h exposure to elevated temperatures. Ramberg-Osgood parameters: n(room temperature) = 6.7; n(800 °P) = 7.0; n(lOOO °P) = 13; n(l200 °P) = 13. Composition: Ni-37Pe-16Cr-2.9Nb-1.8Ti. UNS N09706 Source: MIL-HDBK-5H, Dec 1998, p 6-49
Nickel (Ni)/695
Ni.113 Inconel 706 nickel alloy bar, tensile stressstrain curves at room and elevated temperatures
160 r - - - - - - , - - - - , - - - - - , - - - - - , - - - = - - - - - - - - , 1120
100~--4_---.A~~L-1_--_+---+_--~
Test direction: longitudinal. 152,4 mm (6 in.) square bar pressed into 50.8 x 152,4 mm (2 x 6 in.) bar, treated at 982 oC (1800 °F), 2 h, air cooled, + 843 oC (1550 °F), 3 h, air cooled, + 718 oC (1325 °F), force cooled to 621°C (1150 °F), 18 h, air cooled. Composition: Ni37Fe-16Cr-2.9Nb-l,8Ti. UNS N09706
700 ro
a.
~
g
:2 80~---~~~LA----1_---_+---+_--~ 560 <ñ !/)
U5
U5
~
~
60~---~~~~----~--_+---+_--~
420
40~-~~--~----1_--_+---+_--~
280
20~~--~--~----1_--_+---+_--~
140
2
4
6
8
10
Source: OL. Deel and H. Mindlin, "Engineering Data on New Aerospace Structural Materials," Technical ReportAFM6-TR-72-196, Vol n, Sept 1972, p 113, 125. As pub1ished in Aerospace Structural Metals Handbook, Vo14, Code 4110, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 10
O
12
Strain, 0.001 inJin.
160r----r-------¡----,----,--~,---_,1120
Ni.114 Inconel 706 nickel alloy bar, tensile stressstrain curves at room and elevated temperatures
140~---~--~----1_~-_+--~~~-~980
Test direction: transverse. 152,4 mm (6 in.) square bar pressed into 50.8 x 152,4 mm (2 x 6 in.) bar, treated at 982 oC (1800 °F), 2 h, air cooled, + 843 oC (1550 °F), 3 h, air cooled, + 718 oC (1325 °F), force cooled to 621°C (1150 °F), 18 h, air cooled. Composition: Ni-37Fe-16Cr-2.9Nb-l,8Ti. UNS N09706
100~---r--,~~7~~~--_+---+_--~700
~
&.
:2
g
80 ~---r_+---/-___H.'-------+_--_+---+_--~ 560 <ñ
U5
U5
~
~
60~---r~~~----1_--_+---+_--~420
40~-~~--~----1_--_+---+_--~280
20r-~-_r--~----+_--_+---+_--~140
L---~--~----~--~---~---"O
2
4
6
Strain, 0.001 inJin.
8
10
12
Source: OL. Dee1 and H. Mindlin, "Engineering Data on New Aerospace Structural Materials," Technical Report AFM6-TR-72-196, Vol n, Sept 1972, p 113, 126. As published in Aerospace Structural Metals Handbook, Vo14, Code 4110, ClNDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 10
696/Nickel (Ni)
Ni.115 Inconel 706 solution treated and aged nickel alloy forged bar, typical compressive stress-strain and compressive tangent modulus curves at room and elevated temperatures
Compressive tangent modulus, GPa
o 35 70 105 140 175 210 245 200 r - - - " T - - - , - - - - , - - - - - . , - - - - r - - - . , - - - - , 1400
Test direction: longitudinal and long transverse. Bar thickness = 50.8 mm (2.000 in.). Creep rupture heat treatment and 0.5 h exposure to elevated temperatures. RT, room temperature. Ramberg-Osgood parameters: n(RT) = 11; n(800 °P) = 10; n(lOOO °P) = 9.7; n(1200 °P) = 9.2. Composition: Ni-37Pe-l6Cr-2.9Nb-1.8Ti. UNS N09706
RT
160 r---->,~--__+--__+---+_=__=t---_+--_j 1120 800 °F (427 OC)
I
120 r-_ _~~~~-~~~~~~-+~10~0~0-OF~(~5-38-0-C~) 840
'w
o.:. ui
'"~
Source: MIL-HDBK-5H. Dec 1998, p 6--49
é7í
80
40r--.~r--_4--__+--__+-r+_r+---H--~280
00
2
O
5
6 8 Strain, 0.001 in./in.
4
I
10
O
12
14
30
35
I
10 15 20 25 Compressive tangent modulus, 106 psi
Ni.116 Inconel 706 nickel alloy bar, compressive stress-strain curves at room and elevated temperature
160 ...-----,------,-----,-------,---::::;0<-,-----, 1120
140r---~--_4--~~--_+---~
__~_j980
100r---~-~__+~~-+_--_+---r---_j700
~
:i ~
& ::;¡ 80 r---~_+~~---+_--_+---r---_j 560
é7í 60r---~~--4---+----+---r----j420
40~-~~--~---+_---+---r_--~280
20r-~-~--_4---+_--_+---r_--_j140
2
4
6
Strain, 0.001 in./in.
8
10
ui
~ w
Test direction: longitudinal. 152.4 mm (6 in.) square bar pressed into 50.8 x 152.4 mm (2 x 6 in.) bar, treated at 982 oC (1800 °P), 2 h, air cooled, + 843 oC (1550 °P), 3 h, air cooled, + 718 oC (1325 °P), force cooled to 621°C (1150 °P), 18 h, air cooled. Composition: Ni37Pe-16Cr-2.9Nb-1.8Ti. UNS N09706 Source: G.L. Deel and H. Mindlin, "Engineering Data on New Aerospace Structural Materials," Technical Report AFM6-TR-72-196, Vol n, Sept 1972, p 113, 127. As published in Aerospace Structural Metals Handbook. Vol 4, Code 4110, CINDAS/USAF CRDA Handbooks Gperation, Purdue University, 1995, p 12
Nickel (Ni)/697
Ni.117 Inconel 706 nickel alloy bar, compressive stress-strain curves at room and elevated temperature
16o.------,-----,------,------.--~~~----_,1120
140~----~----_1----~~----_+----~~=---~980
100~----~--_7~~~--+_----_+------+_----~700
~
~
::2:
gf 80 ~----+-_+--¡'A------+_----_+------+_----~ 560 gf ~ e
1i5
(f)
60~-----~~--_1------+_----_+------+_----~420
Test direction: transverse. 152.4 mm (6 in.) square bar pressed into 50.8 x 152.4 mm (2 x 6 in.) bar, treated at 982 oC (1800 °F), 2 h, air cooled, + 843 oC (1550 °F), 3 h, air cooled, + 718 oC (1325 °F), force cooled to 621°C (1150 °F), 18 h, air cooled. Composition: Ni-37Fe-16Cr-2.9Nb-1.8Ti. UNS N09706 Source: OL. Deel and H. Mindlin, "Engineering Data on New Aerospace Structural Materials," Technical Report AFM6-TR-72-196, Vol n, Sept 1972, p 113, 128. As published in Aerospace Structural Metals Handbook, Vol 4, Code 4110, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 12
40~--~~----_1------+_----_+------+_----~280
20~~---~-----1------+------+------+-----~140
Strain,
-------
50
40
·00 30 -"
~"' 25 en
(])
::l
¡!: 20
15
(
I I
Ni.118 Inconel 706 annealed nickel alloy 51 mm (2 in.) diam rod, hot rolled, engineering stress-strain curve
350
~
45
35
0.001 inJin.
3150 280 245 210
rf. ::2:
175 ~
1
(])
140 ~
I
105
10
70
5
35 2.5
5.0
7.5
10.0 True strain, x 0.001
12.5
o
15.0
Test direction: longitudinal. 0.2% yield strength = 280 MPa (40.6 ksi); ultimate tensile strength =722 MPa (104.7 ksi); elongation = 51.3%; reduction in area = 71.5%. Composition: Ni-37Fe-16Cr-2.9Nb-1.8Ti. UNS N09706 Courtesy of Special Metals Corporation
698/Nickel (Ni)
200
Ni.119 Incoloy 909 nickel alloy bar, tensile stressstrain curves at room temperature with effect of various heat treatments
1400
180
1260
_A
160
/'
f
~
v /' j ..----: VI ~ / / / V / / V / / / / / / / V / / / /
140 120
Test direction: longitudinal. Bar diameter = 123.825 mm (4.875 in.). Reat treatment: A: 982 oC (1800 °P), 1 h, air cooled, + 718 oC (1325 °P), 8 h, force cooled to 621°C (1150 °P), held 8 h, air cooled. B: 982 oC (1800 °P), 1 h, air cooled, + 718 oC (1325 °P), 4 h, force cooled to 621°C (1150 °P, held 4 h, air cooled. C: 1038 oC (1900 °P), 1 h, air cooled, + 774 oC (1425 °P), 8 h, force cooled to 621°C (1150 °P), held 8 h, air cooled. D: 1038 oC (1900 °P), 1 h, air cooled, + 774 oC (1425 °P), 8 h, force cooled to 621°C (1150 °P), held 4 h, air cooled. Composition: Ni-42Pe-13Co-4.7Nb-1.5Ti. UNS N19909
1120
B
e ....... D
980 840
./
J
80 60 40 20
o
I V
'( r-
0 .2
-1
/
120
100
/
/
40
/
/
v ---
140
1120
Ni.120 Incoloy 909 nickel alloy bar, tensile stressstrain curve at 538 oC (1000 °F)
980
Test direction: longitudinal. Bar diameter = 123.825 mm (4.875 in.). Reat treatment: 982 oC (1800 °P), 1 h, air cooled, + 718 oC (1325 °P), 8 h, force cooled to 621°C (1150 °P), held 8 h, air cooled. Composition: Ni-42Pe13Co-4.7Nb-1.5Ti. UNS N19909
840
700
o..'"
/
::;;
560
~
ro 420
I
280
140
0.2
Source: Private communication fmm D.R. Yates, INCa Alloys International, 19 Oct 1989. As published in Aerospace Structural Metals Handbook, Vol 5, Code 4219, CINDASfUSAF CRDA Randbooks Operation, Purdue University, 1995, p 8
o
y
60
20
/
280
Strain, %
160
140
420
0.4
0.6 Strain, %
0.8
1.0
o
1.2
Source: Private cornmunication fmm D.R. Yates, INCa Alloys International, 19 Oct 1989. As pub1ished in Aerospace Structural Metals Handbook, Vol 5, Code 4219, CINDASfUSAF CRDA Randbooks Operation, Purdue University, 1995, p 9
Nickel (Ni)/699
Ni.121 Incoloy 909 nickel alloy bar, tensile stressstrain curves at 649 oC (1200 °F) with effect of various heat treatments
140,----,----,-----,----,-----,----,----, 980 A
~
B
120~---+----~----r---~--_.~~~~~~
840
100~--_+----~----r_~~~~_r----+_--~
700
80~---+----~--~-r__7~--~~~~~--~
560 ~ :::i:
~~
ui
'"
~ W 60~--_+----~---~~--~--+__r----+---~ 420 W
40~--_+,r--~r---+.r--~-----r----+---~
280
20~_7_+--~~-.~-r_~~----_r----+---~
140
OL-__
~
____
~
____
L __ _
~
_ _ _ __ L_ _ _ _
~
__
~
O
Test direction: longitudinal. Bar diameter = 123.825 mm (4.875 in.). Reat treatment: A: 982 oC (1800 °P), 1 h, air cooled, + 718 oC (1325 °P), 8 h, force cooled to 621°C (1150 °P), held 8 h, air cooled. B: 982 oC (1800 °P), 1 h, air cooled, + 718 oC (1325 °P), 4 h, force cooled to 621°C (1150 °P, held 4 h, air cooled. C: 1038 oC (1900 0 P), 1 h, air cooled, + 774 oC (1425 °P), 8 h, force cooled to 621°C (1150 °P), held 8 h, air cooled. D: 1038 oC (1900 °P), 1 h, air cooled, + 774 oC (1425 °P), 8 h, force cooled to 621°C (1150 °P), held 4 h, air cooled. A: yield strength = 823 MPa (119.3 ksi); ultimate tensile strength = 1028 MPa (149.1 ksi); elongation (in 4D) = 19%; reduction in area = 38%. B: yield strength = 778 MPa (112.9 ksi); ultimate tensile strength = 990 MPa (143.6 ksi); elongation (in 4D) = 18%; reduction in area = 37%. C: yield strength = 594 MPa (86.1 ksi); ultimate tensile strength = 871 MPa (126.3 ksi); elongation (in 4D) = 23%; reduction in area = 44%. D: yield strength = 607 MPa (88.0 ksi); ultimate tensile strength = 916 MPa (132.9 ksi); elongation (in 4D) = 19%; reduction in area = 30%. Composition: Ni-42Pe-13Co-4.7Nb-l.5Ti. UNS N19909 Source: Private cornmunication fram D.H. Yates, INCO Alloys IntemationaI, 19 Oct 1989. As published in Aerospace Structural Metals Handbook, Vo15, Code 4219, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 9
700/Nickel (Ni)
800r------,------,-----~------._----_,------~
3%
Ni.122 Nickel-molybdenum alloy, true compressive stress-strain curves for various alloys and temperatures
Strain rate = -3 x lO-4/s, d = -75 X 10-6 m. (a) Temperature =-295 K, composition as indicated; curves diverge monotonically. (b) Ni-3% Mo at various temperatures, curves coincide at low strains but diverge in the dynamic recovery range. Source: George Krauss, Ed., Deformation, Processing, and Structure, papers presented at ASM Materials Science Seminar (St. Louis, MO), 23 Oct 1982, American Society for Metals, 1984, p 100-101
o
(a)
800 295 K 700
600
ro
O-
:2
!Il
~
400
300
200
100
o o
0.1
(b)
0.2
0.3 Strain
0.4
0.5
0.6
Nickel (Ni)/701
100
._ 80
1!
"' tí Ul
~
g> 60
.~ Q)
e 'c,
e W 40
/
V
,,- ./
~
----
560
al
o..
i"'
Test direction: longitudinal. Sheet thickness = 1.168 mm (0.046 in.). 0.2% yield strength = 294 MPa (42.7 ksi); ultimate tensile strength =703 MPa (101.9 ksi); elongation = 39.4%. Composition: 42Ni-21.5Cr-bal Fe . UNS N08825 Courtesy of Special Metals Corporation
420 ~ c:
"$
e '0 e 280 W
140
0.05
0.15 Strain
0.10
0.20
0.25
o
0.30
Ni.124 Incoloy 825 annealed nickel alloy sheet, engineering stress-strain curve (expanded range)
350
50
10
700
;:¡¡:
20
40
Ni.123 Incoloy 825 annealed nickel alloy sheet, engineering stress-strain curve (full range)
840
120
I-
280
I I I1/
al
o.. 210
~Ul
~
01
e
.~
140 ~
'0 e
W
70
2
4
6
Strain x 0.001
8
o
10
Test direction: longitudinal. Sheet thickness = 1.168 mm (0.046 in.). 0.2% yield strength = 289 MPa (41.9 ksi); ultimate tensile strength =687 MPa (99.6 ksi); elongation = 37.7%. Composition: 42Ni-21.5Cr-bal Fe. UNS N08825 Courtesy of Special Metals Corporation
702lNickel (Ni)
80
~ 60
ui
~
el
o:
.~ Q)
.§,
40
o:
UJ
Ni.125 Incoloy 330 annealed nickel alloy sheet, engineering stress-strain curve (full range)
700
100
/
/
'/
/
/
V--
--
560
'"
a..
420 :2.
g¡
Test direction: longitudinal. Sheet thickness = 2.946 mm (0.116 in.). 0.2% yield strength = 247 MPa (35.8 ksi); ultimate tensile strength = 587 MPa (85.2 ksi); elongation = 43.5%. Composition: 44Fe-35.5Ni-18.5Cr. UNS N08330 Courtesy of Special Metals Corporation
~
tí el
o:
.~
280 .0, ~ o:
UJ
140
20
0.05
0.10
0.15
0.20
0.25
o
0.30
Strain
100
._ 80
g¡
ui
~g> 60
(
/
V
v--
~ 700
560 a.. '" :2 ui
~
420
.~
!o: .~
Q)
Q)
o: o:
.0, UJ
Ni.126 Incoloy 25-6 annealed nickel alloy sheet, engineering stress-strain curve (full range)
840
120
o: o:
.0,
40
280
20
140
0.05
0.10
0.15 Strain
0.20
0.25
o
0.30
UJ
Test direction: longitudinal. Sheet thickness = 0.889 mm (0.035 in.). 0.2% yield strength = 413 MPa (59.9 ksi); ultimate tensile strength = 785 MPa (113.9 ksi); elongation = 41.5%. Composition: 45.5Fe-25Ni-20Cr6.5Mo. UNS N08926 Courtesy of Special Metals Corporation
Nickel (Ni)/703
70
490
60
420
/
50
&.
:2
/
cñ
g¡ 40
280 gf
/ 'J
ti el
e
.~ 30
e .c,
e
W
10
350
V
~
20
~
/
Ni.127 Incoloy 25-6 annealed nickel alloy sheet, engineering stress-strain curve (expanded range)
~
el
e
210 .~ e .c, e
W
/
140
70
/
2
3
4 Strain x 0.001
5
6
7
8
o
Test direction: longitudinal. Sheet thickness = 0.889 mm (0.035 in.). 0.2% yield strength = 413 MPa (59.9 ksi); ultimate tensile strength =785 MPa (1l3.9 ksi); elongation = 41.5%. Composition: 45.5Fe-25Ni-20Cr6.5Mo. UNS N08926 Courtesy of Special Metals Corporation
Reactive and Refractory Metals (RM)/705
Reactive and Refractory Metals (RM) RM.OOl Be-2%BeO beryllium all forms, effect of temperature on physical properties
Temperature, oc
260
-18 0.9
1093
826
538
137 1 10 LL
0.8
~ e
"~ ~ .a
~0.7
~ 120
ro
o: 1ií
.g" 0.6
.c
80
·0
g
"o-
C/l
~
ti::l
."
e o
Source: MIL-HDBK-5H. Dec 1998, p 7-5
!;t
""".c
::l
6
.,eox "
The coefficient of thermal expansion, ex, is between 21°C (70 °F) and the indicated temperature. The thermal conductivity, K, is at the indicated temperature. The specific heat, e, is at the indicated temperature.
40
ro"
E
"
.c f-
004
O
0
500
1000
1500
2000
2500
Temperature, °F
80
70
[
60
! I
50
30
20
10
1
e =0.02
2
e
560
RM.002 Various grades of beryllium, various forms, tensile stress-strain curves
490
(1) 1400 hot-pressed block. Ultimate tensile strength: longitudinal (L), 450 MPa (66 ksi); transverse (T), 550 MPa (80 ksi). Typical compressive and tensile yield strength: L, 430 MPa (62 ksi); T, 450 MPa (65 ksi). (2) SR200 sheet. Ultimate tensile strength (L and T), 540 MPa (79 ksi). Tensile and compressive yield strength (L and T), 400 MPa (58 ksi). (3) S200E hot-pressed block. Ultimate tensile strength: L, 340 MPa (50 ksi); T, 390 MPa (56 ksi). Tensile and compressive yield strength: L, 260 MPa (38 ksi); T, 270 MPa (39 ksi). (4) no brake grade. Ultimate tensile strength: L, 340 MPa (50 ksi); T, 360 MPa (53 ksi). Tensile and compressive yield strength (L and T), 220 MPa (32 ksi). (5) BG 170 brake grade at 371°C (700 °F). (6) BG 170 brake grade at 649 oC (1200 °F). The elongation, e, is listed for each by the material curve. AH values are typical. Guaranteed values are lower.
=0.20 420
--e
350
'"
=0.03
a.
::¡:; 280 ui
~ ~ --;; =0.04 :::::::--
Ir -
[ [ Ir
5
e =0045
6
e
~
UJ
210
140
=0.20 70
2
4
6
Strain, 0.001 in.lin.
8
Source: Brush Wellman unpublished data and specification data. As published in Vol 5, Code 5101, Aerospace Structural Metals Handbook, CINDAS/USAF CRDA Handbook Operation, Purdue University, 1995, p 9 and 12
706/Reactive and Refractory Metals (RM)
70
490
60
420
50
.¡¡; 40 -'"
~ ~ C!J
30
72°F (22jC). f. = 0.0~2
/'
r
~
300°F (149
350
Í)' f. = 0.003 5 ~
I
280
¡...--
700°F b71
OC),
f.
=0.03 5~1 210
20
140
10
70
0.12
0.08
0.16
&
:2
'/
0.04
Tested at various temperatures and strain rates, f.. Hotpressed block with 20 !lm grain size. Tested in the transverse direction. X indicates fracture.
1 5-
~~O °F (260 OC), f. =0.006 5- 1
V/
RM.003 S200E beryllium block, tensile stress-strain curves
Souree: F.L. Sehierloh and S.G. Babeoek, "Tensile Properties of Beryllium at High Strain Rates and Temperatures," AFML-TR-69-273, General Motors Teeh Center, Oet 1969. As published in Aerospace Structural Metals Handbook, Vol 5, Code 5101, CINDASfUSAF CRDA Handbook Operation, Purdue University, 1995, p 12
~
U5
o
0.20
0.24
Strain, in.lin.
90 80
.,....-
70 60 .¡¡; -'"
50
/
r
V
~
---
¡..--
RM.004 SR200 beryllium sheet, tensile stress-strain curves
560
Tested at various temperatures and a strain rate of 0.005 S-1 for 1.5 mm (0.060 in.) sheet with 13 !lm grain size. X indicates fracture.
72 °F (2 oC)
1
490
l
420
iK 300 °F (149 oC)
-
500 °F
(~60 oC)
ro
700 °F
~
U5 40
630
(~71
V-
350 ~ oC)
280 ~
C!J
30
210
20
140
10
70
0.04
0.08
0.12
0.16
Strain, in./in.
0.20
0.24
o
0.28
Souree: F.L. Sehierloh and S.G. Babeoek, "Tensile Properties of Beryllium at High Strain Rates and Temperatures," AFML-TR-69-273, General Motors Teeh Center, 1969. As published in Aerospace Structural Metals Handbook, Vol 5, Code 5101, CINDASfUSAF CRDA Handbook Operation, Purdue University, 1995, p 12
Reactive and Refractory Metals (RM)/707
80
560
RM.005 S200E beryllium sheet, tensile stress-strain curves
490
Tested at various temperatures for cross-rolled sheet. At room temperature for 0.5-6.35 mm (0.021-0.25 in.) sheet: ultimate tensile strength (min), 483 MPa (70.0 ksi); 0.2% offset yield strength (min), 345 MPa (50.0 ksi)
Room telperature
70 60
/ /V V
50
'/
20 j
~
420 ~
500 OF (260 oC) 350
1
ro
~
~
30
10
V" V"
f,.--
o..
750°F (399 oC)
~
280
Source: "Designing with Beryllium," Brush Wellman, Inc., Cleveland, OH. As published in Aerospace Structural Metals Handbook, Vol 5, Code 5101, CINDASIUSAF CRDA Handbook Operation, Purdue University, 1995, p 8, 9
~
210 1000 °F (538 oC)
/'
140
V
70
3
2
4
5
6
6
Strain, 10- in./in.
55
J--=
50 45
V-f/
40
gj 30 25 20 15 10 5
500°F (260 oC)
I I V / f¡ I
245 ro
175
/'
Tested at various temperatures for hot-pressed block. At room temperature: typical minimum ultimate tensile strength, 280 MPa (40 ksi); typical minimum tensile yield strength, 210 MPa (30 ksi)
315
210 ~
f¡
gf
350
280
/ Iy
35
¡¡¡
~emper~ture ~ !---
RM.006 S200E beryllium block, tensile stress-strain curves
385
-
140 1100 °F (593 oC) 105 70 35
2
3
4 5 6 6 Strain, 10- in./in.
7
8
~ ~
Cñ
Source: "Designing with Beryllium," Brush Wellman, Inc., Cleveland, OH. As published in Aerospace Structural Metals Handbook, Vol 5, Code 5101, CINDASIUSAF CRDA Handbook Operation, Purdue University, 1995, p 8, 9
70B/Reactive and Refractory Metals (RM)
RM.007 Be-38AI, Lockalloy beryllium sheet, tensile stress-strain curves
7o,-------,--------,-------,--------,-------,49o
Sheet thickness: 1.47-2.47 mm (0.058-0.108 in.) sheet. Young's modulus, 193 GPa (28 x 106 psi). Curve 1 is for sheet in as-roUed condition with longitudinal, L, specimen. Curve 2 is for as-roUed condition with transverse, T, specimen. Curve 3 is annealed, and applies to both L and T.
50¡------t1l~~---¡----==:j::::::==t===~~1350 '00
40 1-----..,ff-+:;~----_+-----__t--------+__------__1 280
~
&: ~
~
00 w
~
1i5 30
210
~
Souree: R.W. Fenn, Jr., 0.0. Crooks, W.c. Coons, and E.E. Underwood, "Properties and Behavior of Beryllium-Aluminum Alloys," Loekheed Missiles & Spaee Company, Oet 1964. As published in Aerospace Structural Metals Handbook, Vo15, Code 5102, CINOAS/USAF CROA Handbook Operation, Purdue University, 1995, p 4
20~~---+--------r-----~--------+-------~140
10~-----+------_+------__t--------+__------__170
L -_ _ _ _ _ _L -_ _ _ _
0.2
~
______
~
0.4
______
0.6
~
______
~O
0.8
1.0
Strain, %
60
420
50
350
Room temperature
40
,/
/
~
r-----
-
10
¡
/
ro
a.
400 °F (204 oC)
~
210 rñ w
~
140 800 °F 427 oC)
~
0.1
70
0.2
Tested at various temperatures and at a strain rate of -0.13 mm/min (-0.005 in./rnin) for 1.5 mm (0.060 in.) annealed sheet, in both longitudinal and transverse directions
280
¡...---
20
RM.008 Be-38AI, Lockalloy beryllium sheet, compression stress-strain curves
0.3
0.4
Strain, %
0.5
0.6
o
0.7
Souree: R.W. Fenn, Jr., 0.0. Crooks, O.E. Watts, and A.S. Neiman, A Meehaniea1 Property Evaluation of Be-38% Al Alloy from -320 to 800 F, Met. Eng. Q., Nov 1965. As pub1ished in Aerospace Structural Metals Handbook, Vo15, Code 5102, CINOAS/USAF CRDA Handbook Operation, Purdue University, 1995, p 7
Reactive and Refractory Metals (RM)/709
60
420
50
350
40
280
(J)
~
Tested at various temperatures and at a strain rate of approximately 0.13 mm/rnin (0.005 in./rnin) for annealed extrusion. Solid line is longitudinal, broken line is transverse direction. ro
a.
'00
"'rñ"
RM.009 Be-38AI, Lockalloy beryllium extrusion, compression stress-strain curves
::¡;
210 rñ (J)
30
Source: R.W. Fenn, Jr., D.D. Crooks, G.E. Watts, and A.S. Neiman, A Mechanical Property Evaluation of Be-38% Al Alloy from -320 10 800 F, Met. Eng. Q., Nov 1965. As published in Aerospace Structural Metals Handbook, Vol 5, Code 5102, CINDASfUSAF CRDA Handbook Operation, Purdue University, 1995, p 7
~
é'i5
é'i5 20
140 800°F 427 'C) 70
10
o0L-----L---~-----~----~----~----~----~0
0.1
0.2
0.3
0.4
0.5
0.6
0.7
Strain, %
60
RM.Ol0 N50 beryllium block, tensile stress-strain curves
420
"L, V<. 72 "
50
;;~-
Tested at various temperatures and strain rate of 0.002 S-l. Hot-pressed block with 40 !lm grain size. Tested in the transverse direction. X indicates fracture.
350
30
40 '00
"'rñ" (J)
~
500 'F (260 oC)
r!!/ V----
700 'F (371°C)
280 ro
a.
¡--"'"
::¡;
30
210 rñ (J)
~
é'i5 20
140
10
70
0.02
0.04
0.06 Strain, in.lin.
0.08
0.10
o
0.12
Source: EL. Schierloh and S.G. Babcock, "Tensile Properties of Beryllium at High Strain Rates and Temperalures," General Motors Tech Center, Oct 1969. As published in Aerospace Structural Metals Handbook, Vol 5, Code 5101, CINDASfUSAF CRDA Handbook Operation, Purdue University, 1995, p 12
71 O/Reactive and Refractory Metals (RM)
50
--.
serratio1
30 'üi
-'"
Tested at 340 oc. The chromium displayed an average rate of work hardening of 27.6 MPa (4000 psi)/percent strain between O and 3% strain, compared with arate of 3.5 MPa (500 psi) between 3 and 20% strain.
No seJations
~
40
RM.Oll Worked chromium rod, quenched mediumgrain size chromium, stress-strain curve
350
.......
I
280
\
\
210
\
.,;
'~"
iií
20
Source: A Gilbert, C.N. Reid, and G.T. Hahn, Tensile Properties of Chromium and Chromium-Rhenium Alloys, High Temperature Refractory Metals, R.W. Fountain, J. Malt, and L.S. Richardson, Ed., based on a symposium, 16-20 Feb 1964, sponsored by the High Temperature Metals Committee Extractive Metallurgy Division) and the Refractory Metals Committee (Institute of Metals Division) of the Metallurgical Society of the American Institute of Mining, Metallurgical, and Petroleum Engineers, Gordon and Breach Science Publishers, 1966, p 200
ro
Il.
:2
~ ~
140 iií
\
10
70
5
10
15
20
25
o
30
35
Elongation, %
50
50r-----------------------------------------,350
350
Ouenched
Lo.,Ji. uppe) yield stress 1 Lower yield stress
40
318 oC 280
379 oC
40~~-T----------------_7~----------------1280
Ji.
30 'iji
/1 1
-'"
.,;
" '1-
-1- _Vi '-...1"
Ouenched
210 ro
VJ
~
iií 20
Lo.
Lo.
Lo.
1-....
'iji
:2: .,;
.,;
VJ
Lo.
Lo.
~
Lo. Lo.
~ 140
-'" VJ
ro :2:
Il.
310 oc
.,;
378 oc
~
en
VJ
~
140
20
1 ..!~~.::.c:'~~-1-(..1:-1-1 'k1-
iií
Furnace cooled
.~
10
210
30
Il.
70
70
10 2%
'---'
320
340
360
380
o
O~--------------~----------------------~O
400
Test temperature, oC (a)
(b)
RM.012 Worked chromium rod, quenched and furnace cooled medium-grain size chromium, effect of quenching on yield properties
(a) Yield stress versus temperature. (b) Effect of cooling rate on the shape of stress-strain curves. The quenched specimens were all strained 8% in the strain-aging range and, compared with the fumace-cooled samples, had higher upper and lower yield stress values and markedly different stress-strain curves that showed an unusually high rate of work hardening. After about 3% strain, the rate of work hardening decreased substantially. Source: A Gilbert, C.N. Reid, and G.T. Hahn, Tensile Properties of Chromium and Chromium-Rhenium Alloys, High Temperature Refractory Meta/s, R.W. Fountain, J. Malt, and L.S. Richardson, Ed., based on a symposium, 16-20 Feb 1964, sponsored by the High Temperature Metals Committee Extractive Metallurgy Division) and lhe Refractory Metals Cornmittee (Institute of Metals Division) of the Metallurgical Society of the American Institute of Mining, Metallurgical, and Petroleum Engineers, Gordon and Breach Science Publishers, 1966, p 199
Reactive and Refractory Metals (RM)/711
80 60 ·00 -'"
gf 40
~
en
~ ,vr
440 oC 420
_
Test stopped at 8%strain
20
r
Test stopped at ....- 8%strain
::¡;
280
140
-~
-
420 oC ·00
'" ~
V
20
5% plastic strain '----'
'"
280 ~
u)
'"
140 ~
"
en
O
-"\ V -
420
469°C
·00 -'" 40 u)
'"~
1ií
20
~ 1ií
420
O 60
u)
O
60
u)
'"
Il.
O
-'" 40
RM.013 Chromium-rhenium alloy worked rod, stress-strain curves at various temperatures
560 330 oC
5% plastic strain
'"
280 ~
u)
'"
140 ~
\
en
'----'
O
O 60
420 690 oC
Small-amplitude serrations
'"
~ 40 u)
'" ~
20
O
--.....
/'
1/
5% plastic strain '----'
280 ~
u)
\
'"
140 ~
en
O
Cr-l at.% Rh alloy specimens Source: A Gilbert, C.N. Reid, and G.T. Habn, Tensi1e Properties of Chromium and Chromium-Rhenium Alloys, High Temperature Refractory Meta/s, R.W. Fountain, J. Malt, and L.S. Richardson, Ed., based on a symposium, 16-20 Feb 1964, sponsored by the High Temperature Metals Committee Extractive Metallurgy Division) and the Refractory Metals Committee (lnstitute of Metals Division) of the Metallurgical Society of tbe American Institute of Mining, Metallurgical, and Petroleum Engineers, Gordon and Breach Science Publishers, 1966, p 203
712/Reactive and Refractory Metals (RM)
80 0.1 09
thick ./
70
60
/
I
.,;
420
/
400°F (204 oC)
/'
~
J~ ~ ~
30
490
,;
J/
50
ROOJ tempeJture
V....
/
350
o~
'"
600 (316 oC; ;;... 800 °F¡ (427 0C)¡
a.
:2 280 In '"
1000 °F (538 °Cl 1200 °F (649 °Cl 1600 °F (871°C
~
210
U~
20
140
~ 'f
10
RM.014 L-605 (UNS R30605) cobalt sheet, tensile stress-strain curves for thicknesses as indicated at room and elevated temperatures and various strain rafes
560
i~. (2. 77 ~m)
70
If
o
o 70
490 0.040 ir· (1.0 mr) thick
60
I
----
50
g¡ ¡i al c\5
_._.-
420
Strain rate 60 in./in. miñ' 0.003 in./in. miñ' average of 10 s and 1/2 h holding time 0.0025 in./in. miñ'
350
280
40
30
~
20
-- ---
V
r-
1---
I
--~ --
O
(j)
2000 °F (1093 °C).I I
I
2250 °F (1 232 oC) 140
J
o
¡i 210 ~
V
10
r---
1--
2
&
:2 1600 °F (871 °C)I
-- f ------
4 3 5 Strain, 0.001 in./in.
70 2000 °F (1093 oC) 2250 °F (1 232 oC)
I
I
6
7
The 2.77 mm (0.109 in.) sheet was solution treated at 1200 oC (2200 °P) and rapid air cooled. The 1.0 mm (0.040 in.) sheet was solution treated at 1200 oC (2200 °P) and air cooled. Composition: Co-20Cr-15WlONi Source: For 0.109 in. sheet, Haynes Stellite Company, "Haynes AlIoy No. 25," March 1959; for 0.040 in., sheet, w.P. Roe and J.R. Kattus, "Tensile Properties of Aircraft Structural Metals at Various Rate of Loading after Rapid Heating," TR·55-199, Part III, Wright Air Development Center, Sept 1957. As published in Aerospace Structural Metals Handbook, Vol 5, Code 4302, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 22
Reactive and Refractory Metals (RM)/713
RM.015 L-605 (UNS R30605) cobalt sheet, compressive stress-strain curves at room and elevated temperatures and strain rates
80 ,-------,-------,-------,-------,-------.560 RT
0.18' 60
~------~--~~r-------+-------+-----~420
'00
"'" :1 ~
Sheet thickness: 1.6 mm (0.063 in_). Solution heat treated at 1232 oC (2250 °P) and rapid air cooled. RT, room temperature. Other test specimens were resistance heated to the indicated temperatures. Composition: Co-20Cr15W-lONi
1200 °F (649 oC) 40
éií
Source: P.R. Dioguardo and R.D. Lloyd, "Investigation of lhe Effects of Rapid Properties of Compressive and Column Members," ASD-TR 61-499, The Marquardt Corp., Jan 1962. As published in Aerospace Structural Metals Handbook, Vol 5, Code 4302, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 21
20
o
~
_____
~
_______ L _______ L_ _ _ _ _ __ L_ _ _ _
~O
80 ,-------,-------,-------,-------,-------,560 3
10 8' 60
f------r----r-----RT::!:::==:::j::::::==1 420
I
RT
al
'00
"'" :1
~
[L
:2
40
Foc:)~1~2~00~O~Ft(6~4~9~OC~)=~ 280 ~
_ -t:z:!::8:00:o:F:(4:2:7
éií
1600 °F (871°C) 20
1800 °F (982 oC)
140
2000 °F (1093 oC) OL-------L-------·~------~------~----~O
80
560 5
10 8 ' 60
420 RT
20
t
rf.
...---'
,
:2 8000F (427 oC) '1200 °F (649 oC) - 280 ui
~
V-
~
1800 °f (982 oC) 2000 °F (1093 oC) 2
éií
1600 lF (87l oC)
4
6
Strain, 0.001 in.lin.
2200 °F (1 204°C) _ 8
140
714/Reactive and Refractory Metals (RM)
RM.016 X-40 cobalt investment casting, as cast, total strain curves
4o.--------------------,--------------------.28o
--1%} ____ 2% Total strain
Tested at 816 and 871°C (1500 and 1600 °F). Total strain of 1 and 2% as indicated. Composition: Co-25CrlONi-7.5W
30~------------------_r--------------------1210
--- - - -
~
ro
--~
~ ----g 20 ~-------'=-""""--------_r------------------=-''''''__I140
Source: Haynes Stellite Company, "Haynes Stellite Alloy No. 31," April 1958. As published in Aerospace Structural Metals Handbook, Vol 5, Code 4305, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 26
..:::.
ui
~
~
1500°F(816°C)
00
00
--- - - -1600°F (871 oC)
10 '-0--------------------1oL---------------------'00TP o 1 1 Time, h
RM.017 WI-52 cobalt stress-strain curves
40.----------,----------~---------,-------,280
To
Fiy 37.6 ksi (259 MPa) \ ..,.,.~"I-
Tested at 927 and 1093 oC (1700 and 2000 °F). Pratt Whitney Aircraft 653 coated with PWA 45, chromized at 1052 oC (1925 °F), time unspecified. Individual tests are plotted. F ty , tensile yield strength. Composition: Co-21CrllW-2Fe-1.75(Ta + Nb)
-'
. ' ;.'. -:.:.
-: ;: . ., .
210
30~--------~------~~~--
ro
~
~
g 20 1---------~'------------+__---------t------__I140 g ~
~
w
00
.- .- .- •-
10
-'-'-'1-'·
~~~e tests
~----P.--~"'+~"-'-------+-2000
.
°F (1093 oC)
70
--------j
O~--------~--------~----------L-----~O
O
0.1
0.2 Strain, %
0.3
Source: Personal communication from Pratt & Whitney Aircraft. As published in Aerospace Structural Metals Handbook, Vol 5, Code 4308, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 10
Reactive and Refractory Metals (RM)/715
50 Strain 0.009 ...
H
~~
RM.018 Haynes Alloy No. 188 (UNS R30188) stressstrain curve
350
rate/~in
0.036
...--
40
Tested at 871°C (1600 °P). Note the change in strain rate over the range of strain. Composition: Co-22Cr-22Ni14W-0.08La-Iow C
¡.280
1--
1/
30
210
/ /
~ cñ
1/)
~ 20
10
cñ
1/)
~
140
5
80
/ 1/
60
10 15 Strain, 0.001 in.lin.
20
25
~om te~perature
o
560
RM.019 Haynes Alloy No. 188 (UNS R30188) cobalt sheet, mili annealed, stress-strain curves
490
Tested in longitudinal direction. Typical for sheet thickness: l.73 mm (0.068 in.). Temperature effects on the stress-strain properties are indicated. Strain rate in the elastic region was 0.005 min-l. After yielding to fracture, the strain rate was 0.1 min- l head speed. Composition: Co-22Cr-22Ni-14W-0.08La-Iow C
420
!V -
50
600 °F 1(316 oC) 1000°F (538 oC)
~~ V
350
1400 °F (760 oC)
a.
:2 280 1/) cñ
V
~
30
210
20
140
10
J
70
~
2
é'ñ
70
1/
70
~
:2
Source: W.T. Ebíhara and R.B. Herchenroeder, "Mechanical and Physical Properties of Haynes Developmental Alloy No. 188," Report No. 7626, Kokomo Laboratory, Union Carbide Corp., 16 July 1969. As published in Aerospace Structural Metals Handbook, Vol 5, Code 4310, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 24
4
6 8 Strain, 0.001 in.lin.
10
Source: O.L. Deel and H. Mindlin, "Engineering Data on New Aerospace Structural Materials," Technical Report AFML-TR -71-249, Battelle Columbus Laboratories, Air Force Materials Laboratory, Contract No. F33615-70-C-1070, Dec 1971. As published in Aerospace Structural Metals Handbook, Vol 5, Code 4310, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 24
716/Reactive and Refractory Metals (RM)
80
70
/ /
60
I
50
/
RM.020 Haynes Alloy No. 188 (UNS R30188) cobalt sheet, mili annealed, stress-strain curves
490
Tested in transverse direction. Typical for sheet thickness: 2.0 mm (0.078 in.). Temperature effects on the stressstrain properties are indicated. In the elastic region the strain rate was 0.005 min-l. After yielding to fracture, the strain rate was 0.1 min- l head speed. Composition: Co22Cr-22Ni-14W-0.08La-Iow C
420
V--
~
600°F [316 oC)
1- 1000 °F (538 oC) 1400 °h760 oC)
350
'"
[L
2
280 U>
fI
~
UJ
210
'/
20
560
Room temperature
f-b::==== lA ~
30
10
I
¡....-
Souree: O.L. Deel and H. Mindlin, "Engineering Data on New Aerospaee Structural Materials," Technical Report AFML-TR-71-249, Battelle Columbus Laboratories, Air Force Materials Laboratory, Contraet No. F33615-70-C-1070, Dec 1971. As published in Aerospace Structural Metals Handbook, Vol 5, Code 4310, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 25
140
l
70
f
2
4
6
10
8
Strain, 0.001 in./in.
RM.021 Haynes Alloy No. 188 (UNS R30188) cobalt sheet, mili annealed, compressive stress-strain and tangent modulus curves
Tangent modulus, GPa
60
O
42
84
126
210
168
252 420
Tested in the longitudinal direction. Typical for sheet thickness: 2.0 mm (0.078 in.). Temperature effects on the mechanical properties are indicated. The strain rate was 0.005 min-l. RT, room temperature. Composition: Co22Cr-22Ni-14W-0.08La-low C
Room te1mperature
600°F (316 oC) 1000°,F (538 oC) 1400°F (760 oC)
50
350
Room temperature
280
40
:i ~
'" 2
600°F (316 oC)
.¡¡; -'"
[L
30
~
Ci5 1000°F (538 "e) 140
20 1400°F 760 oC)
70
I O
2
4
I 6
I 12
6 8 Strain, 0.001 in./in. I 18
I 24
Tangent modulus, 10 6 psi
O
10
12
I 30
I 36
Source: O.L. Deel and H. Mindlin, "Engineering Data on New Aerospace Structural Materials," Technical Report AFML-TR-71-249, Battelle Columbus Laboratories, Air Force Materials Laboratory, Contraet No. F33615-70-C-1070, Dec 1971. As published ín Aerospace Structural Metals Handbook, Vol 5, Code 4310, CINDASfUSAF CRDA Handbooks Operatíon, Purdue University, 1995, p 29
Reactive and Refractory Metals (RM)/717
RM.022 Haynes Alloy No. 188 (UNS R30188) cobalt sheet, mili annealed, compressive stress-strain and tangent modulus curves
Tangent modulus, GPa
84
42
~
70
60
./
f!
~
j<- r--
~ / "'-..'b ~ =---
50
126
¡.....-
~
~
20
420
~~ ~
350
-1400°F (760 oC)
'"
D..
600°F (316 oC)
1---
:::E 280 Ul rñ
~
'1400°F 1(760 oC) .-
Source: O.L. Deel and H. Mindlin, "Engineering Data on New Aerospace Structural Materials," Technical Report AFML-TR-71-249, Battelle Columbus Laboratories, Air Force Materials Laboratory, Contract No. F33615-70-C-1070, Dec 1971. As published in Aerospace Structural Metals Handbook, Vol 5, Code 4310, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 29
210
V--
100rF (538 oC) -
I
10
Tested in the transverse direetion. Typieal for sheet thiekness: 2.0 mm (0.078 in.). Temperature effeets on the meehanieal properties are indieated. The strain rate was 0.005 min-l. RT, room temperature. Composition: Co22Cr-22Ni-14W-0.08La-Iow C
600°F (316 oC)
30
j
252 560
490
------
V--
210
168
140
v
70
1/
2
4
8
6
10
Strain, 0.001 in.lin.
o
I
I
I
I
I
6
12
18
24
30
36
Tangent modulus, 10 6 psi
J
RM.023 Commercially pure molybdenum sheet, tensile stress-strain curves
1120
160 _ _
-
-
1
Transvele
Curves given for are east sheet, 0.76-1.0 mm (0.030-0.040 in.) thick, warm worked and stress relieved. Stress relieved 982 oC (1800 °P) for 2 h. Tested in longitudinal and transverse direetion at a strain rate of 0.025/min
Longitudinal
- .... " " ~ -- -- !-_-~ " Warmworked
120
........
/
r
840
1---
~
Stress relieved
gi 80
~
~
\
en
'"
D..
:::E
"\
560 Ul rñ ~
iñ
40
280
4
8
12
16
Strain, 0.001 in.lin.
20
24
Source: "Molybdenum Metal," Climax Molybdenum Co., 1960. As published in Aerospace Structural Metals Handbook, Vol 5, Code 5301, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 6
718/Reactive and Refractory Metals (RM)
120
100
/
80
/
"'Room
te~pera;;;;-
/
f13-t~s r- ~oo °F (982 OC)
2400 °F (1316 oC)
2
100
4
6 8 Strain, 0.001 in./in.
I
V
/
/'"
10
~
--~
-
Y V
1800 °F
(~2
2
RM.025 TZM molybdenum alloy rolled rounds, tensile stress-strain curves at room and elevated temperatures
700
Round diam: 16-17.5 mm (5/8-11/16 in.). Stress relief unspecified. Tested at a strain rate of 0.005/min. Composition: Mo-O.5Ti-0.08Zr
OC)
560 tIl
[l.
2000 °F (1b93 OC) 2400 °F
(1~16 OC)
....-
::¡; 420 rñ
~
é'ií 280
!/
~
840
Room tem erature
V
20
~
2000 °F (1093 0C)-= 280
120
40
::¡; 420 rñ
Source: R.Q. Barr and M. Semchyshen, "Stress Strain Curves for Wrought Molybdenum and Three Molybdenum Base Alloys," Climax Molybdenum Co., Dec 1959. As published in Aerospace Structural Metals Handbook, Vol 5, Code 5301, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 8
140
l--
80
16 mm (5/8 in.) thick bar stress relieved at 982 oC (1800 °F) for 1 h. Tested at a strain rate of 0.005/min
tIl
~
r
700
r---
[l.
.......
20
RM.024 Commercially pure-O.03 C molybdenum bar, tensile stress-strain curves at room and elevated temperatures
560
{, -- - -
40
840
140
4
8 6 Strain, 0.001 in./in.
10
Source: J.A. Houck, "Physical and Mechanical Properties of Commercial Molybdenum Base Alloys," DMIC Rep. 140, 1960. As published in Aerospace Structural Metals Handbook, Vol 5, Code 5303, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 9
Reactive and Refractory Metals (RM)/719
RM.026 MP35N multiphase alloy bar, tensile stressstrain curves at room and elevated temperatures
300 r - - - , . . - - - - - , - - - . . , - - - - - - ¡ - - - - ¡ - - - - - , 2100
250 f----+---+---+_------,""I---:::;j,o.-="--___l1750
200
f-----+---+---~'-7C-._+__---+---___l1400
ro
~
~
~
~
~ 150f-----+---~Y7~+_--_+__---+---___l10500
Typical curves for specimen (UNS R30035) cold worked and aged 538-649 oc (1000-1200 °F) for 4-4.5 h and air cooled. Test direction: longitudinal. Exposed to elevated temperatures for 0.5 h. Ultimate tensile strength, S basis for diam up to 44.45 mm (1.750 in.), 1793 MPa (260 ksi). RT, room temperature. Ramberg-Osgood parameters: n(RT) = 13, n(400 F ) = 14, n(700 F) = 15. Composition: Co-35Ni-20Cr-9.75Mo Source: MIL·HDBK-5H, Dec 1998, p 7-25
100 I----+__~~+_--+_--+_---t-----j 700
501--~+__--+_~-+_--+_---t-----j350
~--L2--~4---~6--~8--~1~0--~1P
Strain, 0.001 in./in.
2100
300
250
LOngitu~
200
~ 1750
1400
/
~ ~ 150
~
/
100
50
/
/
/
Typical curves for specimen (UNS R30159) cold worked and aged 649 to 677 ± 14 oC (1200 to 1250 ± 25°F) for 4-4.5 h and air cooled. Bar thickness: :$;13.462 mm (:$;0.530 in.). Test direction: longitudinal. Ultimate tensile strength, S basis for 20.3-44.45 mm (0.801-1.750 in.) diam, 1793 MPa (260 ksi). Ramberg-Osgood parameters: n(room temperature) = 13. Composition: 36Co-19Cr-9Fe7Mo-Ni(bal) Source: MIL-HDBK·5H, Dec 1998, p 7-30
700
V
350
2
RM.027 MP159 multiphase alloy bar, tensile stressstrain curve at room temperature
4
6 8 Strain, 0.001 in./in.
10
720/Reactive and Refractory Metals (RM)
240
1680
200
1400
r
160 'iñ -'"
tñ U) ~
rf-
ii5 80
40
O
r
ej= ¡.----- 0.02 ~
J
t-_I.. -11
1120 ro o..
,.......
120
~-423'F(-253'C)
::¡; 840 tñ U)
-
1..-
RM.028 Commercially pure niobium bar, tensile stress-strain curves at room and low temperatures
Solid line curves for wrought bar stress relieved at 750 oC (1382 °F) for 1 h. Dashed line curves for bar recrystallized at 1100 oC (2012 °F) for 15 min Source: A.G. Imgram, Ee. Holden, H.R. Ogden, and R.I. Jaffee, "Notch Sensitivity of Refractory Metals," WADD Tech. Rep. 60-278, Sept 1960. As published in Aerospace Structural Metals Handbook, Vol 5, Code 5201, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 5
~
-320 'F (-196 'C)
(f)
560 -103 'F (-75 'C) 280 Rooi t.mp'ffi'rn - -- - - - - - - -
I
o
...
Straln, Jn.lJn.
RM.029 Nb752 niobium alloy sheet, tensile stress-strain curves at room temperature for several thicknesses
80,----,------,------,------,------,-----,560
0.030 in. (0.762 mm)
~
:i
~
Sheet milI annealed. Sheet thickness: 0.30-0.76 mm (0.012-0.030 in.). Composition: Nb-lOW-2.5Zr
ro
~
40 1-------_+--------If#,~--_+-----t_----_+--____I280 tñ
~
201------~L-----t_---_+------t_----_+----____I140
~----~----~2------L-----~----~----~60
Strain, 0.001 in.lin.
Source: J.P. O'Connor, "Evaluation of Cb-IOW-2.5Zr (Cb-752) Columbium Alloy," Rep. A-742, Ser. No. 1, McDonnell Aircraft Corp., June 1964. As published in Aerospace Structural Metals Handbook, Vol 5, Code 5209, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p !O
Reactive and Refractory Metals (RM)/721
28.----------,----------,---------,----------,
24~--------~------~~~~----+_------~
20~---------1_~~~-~~--------~--------__1
-~ 16~------7S~~-------+--------~--------~
-"
'" ~
w
12~--------1_---------+~~--~~--------__1
8~--------1_--~--
__~__~----~--------__1
4~--------~~~~~+_~~~--+_------~
8.01
0.1 Creep. %
RM.030 Nb752 niobium alloy, isochronous stressstrain curves for several temperatures
Composition: Nb-lOW-2.5Zr Source: E.J. Beck and ER. Schwartzberg, "Determination of Mechanical and Thermophysical Properties of Refractory Metals," AFML-TR-65-247, July 1965. As published in Aerospace Structural Metals Handbook, Vol 5, Code 5209, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 13
722/Reactive and Refractory Metals (RM)
RM.031 E8ZR niobium alloy rod, zone-refined, resolved shear stress-strain after one pass (top) and three passes (boUom)
350
50
¡Ir
40
280
~195°C
.¡¡; -"
cñ
'"
~
30
ro
o-
:2
210
ro
'" '" o>'" '"'" "O
20
~
10
~
I
.!::
.!::
'" "O
140 ~
t
o
LJ
-
-80 oc
1/
&
~ -+
25 oc
~
-"
cñ
'" ~
30
o 350
50
.¡¡;
70
92.5%
o
40
"
\
280 ro
o-
:2
210
-195 oc
g ~
tí
ro
~
ro
'" '"
''""
.!::
.!::
"O
o'>"
g ~
"O
140 ~
20
'"'"
~
-80°C
~
10
25 oC
v10
20
Strain, %
LJ \ 1\
o
'"'"
~
70
\
30
40
o
The resolved shear stress as a function of engineering strain for the one- and three-pass electron bearn zonerefined niobium is shown. Their orientations are shown in the unit triangles with each curve. Source: M.K. Thomas, E.S. Jenkins, imd J.F. Erthal, Mechanical Properties of Zone Refined Columbium and Tantalum, High Temperature Refractory Metals, 16-20, Feb 1964, Metallurgical Society of American Institute of Mining, Metallurgical, and Petroleum Engineers, Gordon and Breach Science Publishers, 1966, p 460
Reactive and Refractory Metals (RM)/723
2800
400
200
~
~ 1ií al
2
f-
100
1/ 60 40
/
0.01
V
V
/
/
/
V l/
/ 1400 ro
11.
:2 cii
~
1ií al
700~
RM.032 Rhenium sheet, wire, and rod, average true stress-strain curve Room-temperature properties for 0.254 mm (0.01 in.) sheet (S), 12.7 mm (0.5 in.) wire (W), and 3.175 mm (0.125 in.) rod (R), all in annealed condition. Yield strength (0.2%): S, 930 MPa (135 ksi); R, 317 MPa (46 ksi). Ultimate tensile strength: S, 1160 MPa (168 ksi); W, 1170 MPa (170 ksi); R, 1130 MPa (164 ksi) Source: B.W. Gonser, Ed., papers presented at symposium on rhenium, 3-4 May 1960 (Chicago, IL), Electrothennics and Metallurgical Division of the ElectrochemÍcal Society, Elsevier Publishing Co., 1962, p 34
420
0.02
0.04 0.06
0.1
0.2
0.4 0.6
1.0
280 2.0
True strain, in./in.
RM.033 Commercially pure tantalum wrought bar, stress-strain curves at room and low temperatures
1400
200
RT, room temperature. Solid lines for wrought bar stress relieved at 750 oC (1382 °P) for 1 h. Dashed lines for wrought bar, recrystallized at 1200 oC (2192 °P) for 3 h
1120
160 " " " , -320 °F (-196 OC)
120 '00
/
""cii
/ I r---.
(J)
~ 80
.--
-103°F (-75 OC)
gi
I 560
I
í
{- I
RT
----f::
103 °F(-75
~;
----
I I ---RT r- ~- ~-----1-----
o ~ 0.02 ----.¡
ro
11.
:2
I 40
840
-423 °F (-253 OC)
280
o Straln, In./ln.
~
Source: A.G. Imgram, F.e. Holden, H.R. Ogden, and R.1. Jaffee, "Notch Sensitivity of Refractory Metals," WADD Tech. Rep. 60-278, 1960. As published in Aerospace Structural Metals Handbook, Vol 5, Code 5401, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 4
724/Reactive and Refractory Metals (RM)
60
420
50
350
RM.034 Commercially pure recrystallized tantalum foil, tensile stress-strain curve
íii'
W40 ¡¡; e:
280 ~ ¡¡; e: "5
o c: 30
210 ~
C\l
:g
"§
~
C\l
-'"
'"
Source: R.P. Jewett and E.D. Weisert, Dislocation Morphology of Tantalum deformed in Tension, High Temperature Refractory Metals, based on a symposium, 16-20 Feb 1964, Metallurgical Society of American Institute of Mining, Metallurgical, and Petroleum Engineers, Gordon and Breach Science Publishers, 1966, p 163
c..
'c;;
:E
(J)
~
Foil thickness: 0.076 mm (0.0003 in.). Curve is similar to other body-centered cubic metals, showing the typical yield point. Yield drop observed in aU specimens, with average being 21 MPa (3 ksi).
U)
20
140 ~
10
70
¡¡¡
5
10
15
20
25
30
35
Elongation, %
RM.035 Ta-10W tantalum alloy sheet, arc cast, as-rolled, tensile stress-strain curves at room and elevated temperatures
1400
200
Room temperature
1 mm (0.040 in.) sheet, as-roUed, 96% reduction, tested in argon at a strain rate of O.OO1/s
1120
160
840
120
C\l
c..
'c;;
-'"
:E
'"
'"
(J)
(J)
~
560
80 2000 °F (1093 OC)
2500 °F (1371 OC) 280
40
3000 °F (1649 OC) 00
2
4
6
Strain, 0.001 in.lin.
8
O
10
~
Source: A.S. Rabensteine, "Tensile and Creep Rupture Properties of Tantalum-lO% Tungsten Alloy Sheet," PR 281-1Q-2, AF 33(657)-8706, The Marquardt Corp., Sept 1963. As published in Aerospace Structural Metals Handbook, Vol 5, Code 5402, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 6
Reactive and Refractory Metals (RM)/725
56
8
6
l'
2
~~.
-
42
RM.036 Ta-10W tantalum alloy, tensile stress-strain curve at 1704 oC (3100 °F)
Forrn and condition of material not given for curve. At 1704 oC (3100 °F): ultimate tensile strength, 109.3 MPa (15.85 ksi); tensile yield strength, 74.81 MPa (10.85 ksi), elongation, 22% Source: P.E. Moorhead, "Tensile and Creep Properties of Columbium, Tantalum and Titanium Alloys at Elevated Temperatures," BLR-62-26, Bell Aerosystems Co., Dec 1962. As published in Aerospace Structural Metals Handbook, Vol S, Code 5402, CINDAS/USAF CROA Handbooks Operation, Purdue University, 1995, p 6
I
14
V
6
4
2
Strain, 0.001 in./in.
1000r------r-----,------,------.------.-----~
RM.037 Thorium-carbon alloy, tensile stress-strain curves for various alloys
Alloys with grain size approximately 18 ¡.tm, tested at 78 K, at a strain rate of 0.0007/s Source: G. Krauss, Ed., Deformation, Processing, and Structure, papers presented at ASM Materials Science Seminar, 23 Oct 1982 (St. Louis, MO), American Society for Metals, 1984, p 95
5
10
15
Strain
20
25
30
726/Reactive and Refractory Melals (RM)
RM.038 Commercially pure tungsten rod, true tensile stress-strain curves at elevated temperatures
1oo.-------,-------,--------,-------,-------.7oo
Recrystallized swaged rods Souree: J.W. Pugh, "Tensile and Creep Properties ofTungsten at Elevated Temperatures," ASTM Preprint No. 71, 1957. As published in Aerospace Structural Metals Handbook, Vol 5, Code 5501, CINOASI USAF CROA Handbooks Operation, Purdue University, 1995
80~------+_------~------_+------~------~560
798 "F (426 OC)
I
999.8"F (537.7 OC) 1203.1 "F (650.6 OC)
~
60 f-----r-+-7""-------+--:::;;7~-:::;;7""'f'----___::::;;;oo___t-'-----_'_I 420 ~ 1395.5 "F (757.5 OC) :2 ~ {161o'"F (876.7 OC) gf tí 1790"F (976.7 OC) ~ ~
al
~~
-~
~~----+-------~------_+------~------~140
°0L-------O~.-1-------0L.2-------0~.3------~0.-4-------J0.~ True plastic strain, in./in.
RM.039 W-Hf-C tungsten alloy rod, tensile stress elongation curve
60.---------,----------,---------,,---------.420
50f---------r---------+_~
40~--------+---~
Rod recrystallized at 2200 oC (4000 °P) 1 h and tested at 1370 oC (2500 °P). Composition: W-0.35Hf-0.025C
----------1 350
=---------+_--___1f----j280 ro
~ ~ gf 30 ~------_++---------_+--------___if___--_+--___j 210 gf
~
~ en 20f---~L---r---------+_--------+---___1--~140
10f-~------r---------+_--------+---___1--~70
L -________L -________L -______
---:~
__
~==~O
0.4 Elongation, in.
Source: L.S. Rubenstein, "Effeet of Composition and Heat Treatment on High Temperature Strength of Are Melted Tungsten-Hafnium-Carbon Alloys," TN 0-4379, NASA Lewis Research Center, 1963. As published in Aerospace Structural Metals Handbook, Vol 5, Code 5502, CINOASI USAF CROA Handbooks Operation, Purdue University, 1995, p 4
Reactive and Refractory Metals (RM)/727
140
~oom temp~rature
p
,,/
120 /
100 .¡¡; -'"
..
/
...
Q)
,L
2 60
'" '" '"
-
~ ........ ~'"
40
~
....• --
¡... ........
/
/
/
//
t '" .~
1-
-'
/
/
~
302°F (150"1)
/
I.L· 80
'" ~
1.52 mm (0.060 in.) thick sheet hot roUed at 843 oC (1550 °F). Zircaloy 2 composition: Zr-1.5Sn. Nominal ultimate tensile strengths are indicated on curves by arrows.
840
/
! /
/
I
////,1)
/
RM.040 Zr-l.5Sn zirconium alloy, true tensile stressstrain curves at room and elevated temperatures
980
'"
... ......
'" 482
o~ (250 OC) ·1
... f.o.() 662 O~ (350 OC) ... .........
'" '"
'"
'" '"
",'"
-
932
700
'" 560 :;: D..
:Z
i
420 !!5
t=
oJ (500 OC)
.... - -- -- ---- 1-----
20
280
140
o o
0.2
0.4
0.6 True strain
1.0
0.8
140
RM.041 Zr-l.5Sn zirconium alloy, true tensile stressstrain curves for various conditions
980
o
Maximum load • Fracture
/ ... /. ... r/,.,..-
120
100
~
.¡¡; -'"
80
'" ~ Q)
~
Source: F. Forscher, "Effects of Cold Work on the Mechanical Properties of Zircaloy-2;' Westinghouse Atomic Power Division, 1957. As published in Aerospace Structural Metals Handbook, Vol 5, Code 5701, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 5
.......:..
60
~t """ .... a:
ü
ü
o~
o
~
20
'"
LO N
~
D..
560 :;:
f
-
N
280
~
!e.. -
o
"
0.02
'" o o
!e..
a:
t=
P" o
O
'"
"""HR
1ií
o o
ü
o
700
:.....f"
P" o N
a:
"""
"",,-
420 !!5
¡fF
40
/~:¿..
/ ......;~ r~/" ~~"",,"""
Sheet thickness: 1.52 mm (0.060 in.). Test direction: longitudinal. Tested at 250 oC (482°F). HR, sheet hot roUed at 843 oC (1550 °F). Other curves for cold roUed (CR) conditions as indicated. Zircaloy 2 Composition: Zr-1.5Sn
840
0.04
a:
140
ü
o~
o
ID
0.06 True strain
0.08
0.10
Source: F. Forscher, "Effects of Cold Work on the Mechanical Properties of Zircaloy-2," Westinghouse Atomic Power Division, 1957. As published in Aerospace Structural Metals Handbook, Vol 5, Code 5701, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 5
1 1 1 1 1 1 1
1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1
1
Titanium (Ti)/729
Titanium (Ti) Ti.OOl Commercially pure titanium (CP-Ti) sheet, typical tensile stress-strain curves (full range) at room temperature
800
700
600
(
500
'" :::;
Il.
~
V
V
400
¡..---
V
¡--
V
Ti-70
-
'-t-_
100
Yield strength = 275 and 480 MPa (40 and 70 ksi). Ti-40 is UNS R50400; Ti-70 is UNS R50700.
-
Ti-40
-
Source: Data consistent with MIL-HDBK 5H, 1998 P 5-13, 5-14. As published in R. Boyer, G. Welsch, and E. Collings, Ed., ASM Material Properties Handbook: Titanium Alloys, ASM International, 1994, p 239
80
t--_
-
11
en 300
- 40
200
-
20
100
0.02
0.04
0.06
0.08 0.10 0.12 Strain, mm/mm
0.14
0.16
0.18
o
0.20
Ti.002 Commercially pure Ti-55 and Ti-70 titanium sheet, stress-strain curves at room and elevated temperatures
600 - - - Ti-55 Ti-70
80
500
Ti-55 (UNS R50550): 1.6 mm (0.064 in.) thick, 7j-100 h exposure. Ti-70 (UNS R50700): 0.6 mm (0.025 in.) thick
70
400 ~
__~__~__~_/~~~__+-__+-~~__+-~60
'"
Il.
50
:::;
~
300
gf 40
200
~
I
-hr¡;k~~~;::f~~~ 482 oC (900°F) 30 I
316 oC (600 °F) 427 oC (800°F)
20
100 10
2
3
4 5 6 Sllrain, 0.001 mm/mm
7
8
9
~
iñ
Source: Ti-70 data from E.J. King and H.M. Lundstrom, "Short-Time High-Temperature Data of Titanium Sheet RC-70," Bell Aircraft Corp., 1955. Ti-55 data from D.D. Doerr, "Determination ofPhysical Properties of Nonferrous Structural Sheet Materials at Elevated Temperatures," AFI'R 6517 Part 1, Supplement 1, Feb 1953. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3701, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p5
730/Titanium (Ti)
Ti.003 Commercially pure titanium (CP-Ti) sheet, effect of crosshead speed on tensile stress-strain curves
500r------,------,------,------,------,------, 70
50 ~ 300r-----~~----~-----r------~-----r----~
:2
:i
~ 40 oo'
~ o;
-oo~
Curve Crosshead speed 1 6 mm/min ~ 2 0.6 mm/min ~ 200 r------r------~-----r---3 60 mm/min 4 6mm/min 0.6 mm/min 5
Sheet thickness = 0.81 mm. Test direction: longitudinal. Tests for 1-3 conducted in air at 20 ± 1°C; tests for 4 and 5 conducted in water at 20 ± 0.5 oC. Composition analysis: 0.009 C, 0.055-0.058 0z, 0.002 H 2, 0.002Fe, 0.007 N Source: P. Kvist, Material Properties of Cornmercially Pure Titanium Sheet, Titanium '80 Science and Technology, TMS, 1980, P 1124
Q)
30 ~
20 100r------r------~-----r------~-----r----~
10
ooL-~--~----~~----~----~----~~--~·O
0.05
0.10 0.15 0.20 Natural strain, mm/mm
0.25
0.30
500.---------,---------,---------,---------, 0°
400r-----~~~~~~---+----------~--------~
Ti.004 Commercially pure titanium (CP-Ti) sheet, effect of orientation to rolling direction on tensile stress-strain curves
Sheet thickness =0.81 mm. Curves from series 4 tests. 6 mmlmin conducted in water at 20 ± 0.5 oC. Composition analysis: 0.009 C, 0.055-0.058 Oz, 0.002 Hz, 0.002 Fe, 0.007 N Source: P. Kvist, Material Properties ofCommercially Pure Titanium Sheet, Titanium '80 Science and Technology, TMS, 1980, P 1124
~
al
~ 200~--------~---------+----------t_--------~
100~--------~--------+---------~--------~
0.1
0.2 Natural strain
0.3
0.4
Titanium (Ti)/731
Ti.005 Commercially pure titanium (CP-Ti) sheet, effect of orientation to rolling direction on log tensile stress-strain curves
2.70 2.68 2.66
Sheet thickness = 0.81 mm. Curves from series 4 tests. 6 mm1min conducted in water at 20 ± 0.5 oC. Log curves yield strain hardening n values for strains greater than and less than 0.15: n(O°, where strain is <0.15) = 0.14, n(O°, where strain is >0.15) = 0.17; n(45°, where strain is <0.15) = 0.11, n(45°, where strain is >0.15) =; n(90 0, where strain is <0.15) = 0.11, n(90°, where strain is >0.15) =0.18. Composition anaIysis: 0.009 C, 0.055-0.058 02' 0.002 H2 , 0.002 Fe, 0.007 N
45°
• ./ ./ ....90° 0°
2.64
~
/
~ ~ 2.62
? /;/
Q)
2 -;;, 2.60
h/ ~
o
-'
2.58
Source: P. K vist, Material Properties of Commercially Pure Titanium Sheet. Titanium '80 Science and Technology, TMS, 1980, P 1124
.~.... ~
2.56
2.54 2.52 -1.4
-1.2
-1.0
-0.8
-0.6
-0.4
Lag natural strain
Ti.006 Commercially pure grade 2 titanium textured sheet, true and engineering stress-strain curves
1200
- 160
Test direction: longitudinal. UNS R50400 1000
800 ca
Il..
:; rñ 600
'"~
en
400
L/
Y
- 120 - 100
./
rI
Source: L. Murugesh et al., J. Mater. Shap. Technol., Vol 7 (No. 2), 1989, P 86. As published in R. Boyer, G. Welsch, and E. Collings, Ed., Materials Properties Handbook: Titanium Alloys, ASM International, 1994, p 240
- 140
Árue
~ rñ
~
- 80 ~ .r.
en
Engineering ""-(
- 60 - 40
200
- 20
0.25
0.50
0.75 Strain, mm/mm
1.00
1.25
o
1.50
732/Titanium (Ti)
Ti.007 Cornrnercially pure grade 2 titaniurn textured sheet, true and engineering stress-strain curves
1200
- 160
Test direction: transverse. UNS R50400 (")
1000
- 140
800 ro
el
o.. :2 rñ (/J
600
ir
~
1ií 400
~ ......
V
~
Source: L. Murugesh et al., J. Mater. Shap. Technol., Vol 7 (No. 2), 1989, P 86. As published in R. Boyer, G. Welsch, and E. Collings, Ed., Materials Properties Handbook: Titanium Alloys, ASM International, 1994, p 240
Kue
- 120
r-- '----
~ineering
,.
-
100
-
80
-
60
-
40
-
20
~ rñ (/J ~
1ií
200
0.25
0.50
0.75 1.00 1.25 Strain, mm/mm
1.50
1.75
o
2.00
Ti.OOS Cornrnercially pure grade 2 titaniurn sheet, engineering stress-strain curves
600
- 80 500
&.
"1
400
I~ l?'
,-v
f
:2
......,
~
'\
""'-'---
\
Transverse
Test direction: longitudinal and transverse. UNS R50400
\
- 60 ~
Longitudinal
rñ
rñ (/J
- 50 ~
~ ~ 300
el
e
-
'55
40
e
.:¡¡e Q)
Q)
e
e e
'c,
'c, UJ
Source: L. Murugesh et al., J. Mater. Shap. Technol., Vol 7 (No. 2), 1989, P 86. As published in R. Boyer, G. Welsch, and E. Collings, Ed., Materials Properties Handbook: Titanium Alloys, ASM International, 1994, p 240
- 70
200
-
30
-
20
-
10
100
o
O
0.05
0.10
0.15 0.20 0.25 0.30 Engineering strain, mm/mm
0.35
O
0.40
UJ
Titanium (Ti)/733
Ti.o09 Grade 2 equivalent titanium, true stress-strain curves at elevated temperatures
270 240 210 180
'"
a.
~ 150
'"'"~
1ií CI)
~
120 90 60 30
/
V
/
v
/ " 600 K
Strain rate: 0.033/s. Composition: commercially pure with 0.49 at.% Oeq - 30
¡.......... 700K
1/ Ji/; V {/
~
V.OOK 906K
.;
- 20
i
CI)
--
~
r-
~
-
1150 K 0.16
0.24
-
-1000 K 1050 K
.-
0.08
Source: Metal!. Trans. A, Vol 14, Dec 1983, p 2810. As published in R. Boyer, G. We1sch, and E. Collings, Ed., Materials Properties Handbook: TitaniumAlloys, ASM Internationa1, 1994, p 241
0.32
10
1100 K
--..::
0.40
True, plastic strain, mm/mm
Ti.Ol0 Grade 2 equivalent titanium, true stress-strain curves at various temperatures
14oo,----,----,----r----,----,----,----,----,2oo
Strain rate: 0.00036/s. Composition: commercially pure with 0.5 at.% Oeq. Grain size: 22 11m Source: Metal!. Trans. A, Vo114, Dec 1983, p 2546. As published in R. Boyer, G. Welsch, and E. Collings, Ed., Materials Properties Handbook: Titanium Alloys, ASM International, 1994, p 241
r-___r____~~~r---_+~~+_--~----~--__1150 ~
208 K
.;
'"
100 ~
CI)
~ 420 K 50
°0~---~0.~0~5--~0~.1~0---0~.1~5~~0.~20~--0~.2-5---0~.3-0---0-.L35--~0.48 True strain, mm/mm
734/Titanium (Ti)
Ti.Oll Commercially pure grade 3 annealed titanium sheet, typical compressive stress-strain curves at room and elevated temperatures
500r---------.---------~------~~--------~
70 Room temperature 400~--------4----------+----~~~--------~
Annealed at 705 oC (1300 °P), air cooled. UNS R50550. Chemical composition: Ti-0.02C-0.20Pe-0.005H-0.OIN0.200
60
50
.,
300
40 ~
c..
:;¡;
rñ (/)
rñ (/) ~
iñ
Source: Crucible Data Sheet, Crucible Specialty Metals. As published in R. Boyer, G. Welsch, and E. Collings, Ed., Materials Properties Handbook: Tttanium Alloys, ASM International, 1994, p 241
200
~______~~____~~-+________~________~30
~
20
10
4 Strain, 0.001 mm/mm
2
6
Ti.012 Commercially pure grade 4 titanium, effect of grain size on true stress-strain curves at various temperatures
1600
I
1.5 ¡tm
4.2 K
1400
11 11 1200 1\
n
.,1000 V c..
:;¡;
rñ (/) ~
tí ID
:::J
t=
800
.....
.....
--
~ 600
--~
~ L--
t.------ ~ po-
V
--
200 K
---.::
-
1----::: ~ 200
200
- 150
1.5 ¡tm
1---
~~ ~
400
-
77K 16 ¡tm
16¡tm 1.5¡tm
I
300 K 16¡tm
-
1.5¡tm 16 500K¡tm I - 50 1.5 ¡tm 650 K 16 ¡tm
V
o
O
4
8
12 True strain, %
16
20
o
24
Strain rate: 0.00033/s. UNS R50700. Composition: -1 at. % 0eq Source: Acta Metal!., Vol 21, Aug 1973, P 1117-1129. As published in R. Boyer, G. Welsch, and E. Collings, Ed., Matenals Properties Handbook: Titanium Alloys, ASM International, 1994, p 241
Titanium (Ti)/735
1ooo,---------,---------,---------,---------,
900~---------~----------+_
140
Ti.013 Commercially pure grade 4 titanium, effect of grain size on true stress-strain curves at room temperature
130
Strain rate: -0.0003/s. UNS R50700
120
110
lJ..
:;;
ui
ui
~ 700J-------~~~~-------+_--------_4-----------
~
~'"
~
Source: H. Conrad and R. Jones, The Science, Technologyand Application ofTitanium, R.I. Jaffe and N.E. Promisel, Ed., Pergamon Press, p 489-501. As published in R. Boyer, G. Welsch, and E. Collings, Ed., Materials Properties Handbook: Titanium Alloys, ASM Intemational, 1994, p 239
100
'"
~
t='" ~
90 80 500~--------+_--------+_--------+_------~
70
scatter between specimens 1 Typical 400L_______
o
~I________~________ 0_04
0_08 True strain, mm/mm
_ L_ _ _ _ _ _
0.16
60 r---------,.---------,----~___,----_¡ 420
Ti.014 Commercially pure titanium (Ti-55) sheet, compressive stress-strain curves for room and elevated temperatures
50 I------------l------~"----I-----___=_+__---__I 350
Solid line: 100 h exposure. Dashed line: Y:!-100 h exposure. UNS R50550
40
1----------+_~~,L---+_--------+_------~280
----::: --
.¡¡;
""ui '"~
~ 60
0.12
30
1ñ
20
10
r-~~~--~~~.~-----_+--------10-0-0-0F+(-5-38-0-C-)--~70
2
4
Strain, 0.001 in./in.
6
Source: Data for 0.5-100 h exposure from D.E. Miller, "Determination of the Tensile, Compressive and Bearing Properties of Ferrous and Nonferrous StructuraI Sheet MateriaIs at Elevated Temperatures," AFTR Part 5, 1957. Data for 100 h exposure from TML Memo, 1958. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3701, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 7
736/Titanium (Ti)
175
1225
150
1050
125
875
Test direction: longitudinal. 152 mm (6 in.) square billet solution heat treated for 15 min at 815 oC (1500 °F), air cooled, 12 h, 565 oC (1050 °F), air cooled. UNS R58640
700 o..ro
]l 100
::i<
ui
ui
'"~
éñ
Ti.015 Ti-3AI-8V-6Cr-4Mo-4Zr titanium alloy billet, tensile stress-strain curves for room and elevated temperatures
700°F (371°C) 75
525
50
350
25
175
~
__-L____
00
~
4
2
__
~
____J -__
6
~
____-L__
10
8
'" ~
Source: O.L. Deel and H. Mindlin, "Engineering Data on New and Emerging Structural Materials," AFML-TR-70-252, Batelle-Columbus Laboratories. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3723, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 10
~o
12
14
Strain, 0.001 in.lin.
.¡¡;
"'ui" '" ~
175
1225
150
1050
125
875
Ti.016 Ti-3AI-8V-6Cr-4Mo-4Zr titanium alloy billet, tensile stress-strain curves for room and elevated temperatures
Test direction: transverse. 152 mm (6 in.) square billet solution heat treated for 15 min at 815 oC (1500 °F), air cooled, 12 h, 565 oC (l050 °F), air cooled. UNS R58640
700 o..ro
100
::i< ui
700°F (371°C) 75
'" ~ 525 en
50
350
25 ~--~~---4-----+-----+----~----~----~175
~
00
__
~
____- L____
2
4
~
6
____L -__
8
Strain, 0.001 in.lin.
~
____- l____
10
12
~o
14
Source: O.L. Deel and H. Mindlin, "Engineering Data on New and Emerging Structural Materials," AFML-TR-70-252, Batelle-Columbus Laboratories. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3723, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 11
Titanium (Ti)/737
Ti.017 Ti-3AI-8V-6Cr-4Mo-4Zr titanium alloy billet, compressive stress-strain curves for room and elevated temperatures
175r-----,-----,------r----~----_,------r__,1225
150~----+-----~-----_r----_t----_4~----r_~1050
Test direction: longitudinal. 152 mm (6 in.) square billet solution heat treated for 15 min at 815 oC (1500 °F), air cooled, 12 h, 565 oC (1050 °F), air cooled. UNS R58640
125~----+-----~-----~----_+~~~--~~~~
'w
Source: O.L. Deel and H. Mindlin, "Engineering Data on New and Emerging Structural Materials," AFML-1R-70-252, Batelle-Columbus Laboratories. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3723, CINDAS/USAF CROA Handbooks Operation, Purdue University, 1995, p 12
100r_----·+-----~---~~~~~L-~~----~--~
""gf ~
00
75~----+-----4-~~~~~-+-----+----~--~
50~----·+_--~~~---~----_+----_+----~--~350
25r_--,&~~--1_-----~----_+----_+----~--~175
2
4
6
8
10
12
Slrain, 0.001 in./in.
175
1225
150
1050
125
875
Ti.0l8 Ti-3AI-8V-6Cr-4Mo-4Zr titanium alloy billet, compressive stress-strain curves for room and elevated temperatures
Test direction: transverse. 152 mm (6 in.) square billet solution heat treated for 15 min at 815 oC (1500 °F), air cooled, 12 h, 565 oC (1050 °F), air cooled. UNS R58640
'w 100
700 o.. ::;;:
75
525 00
""
'"
'"~
700°F (371°C) 50
350
25
175
00
2
4
6
8
Strain, 0.001 in.lin.
10
12
O
Source: O.L. Deel and H. Mindlin, "Engineering Data on New and Emerging Structural Materials," AFML-TR-70-252, Batelle-Columbus Laboratories. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3723, CINDAS/USAF CROA Handbooks Operation, Purdue University, 1995, p 12
738/Titanium (Ti)
Ti.019 Ti-5AI-2.5Sn annealed titanium alloy sheet, bar, and forging, tensile stress-strain curves at room and elevated temperatures
12or------,-------r------,-------r------,--~840
100~----~-------4-------+~L----+------~--~700
560
80 .¡¡;
'"!Ji ti)
~
90% probability tension. UNS R54520/R54521.
500°F (260 OC) 60 700 ~F (371°C) 900°F (482 OC)
ro
o..
:::¡; 420 !Ji ti) ~
Cií
40
280
20
140
00
2
6 Strain, 0.001 in.lin.
4
8
10
O
Ti.020 Ti-5AI-2.5Sn annealed titanium alloy sheet, bar, and forging, compressive stress-strain at room and elevated temperatures
140r-----.-----~------,_----_r------r_----~980
120~-----r------+-----_+----~~----_i------~840
90% probability compression. UNS R54520/R54521
100 ~--+_--+---~~..-~=:::::=t==~~ 700 500°F (260 OC)
gj 80 1-------+-------I-----o~---t=_--+...:;,,;;.;-:'--'=t=-..:::..!'----1 560
~
~
w
~
~M
_-+-----
700°F (371 OC) 900°F (482 OC)
~
~Cií
401-------r~~~------~----_+------+_----~280
201----~~----~------~----_+------+_----~140
~-----L2------~4------~6------~8------~1LO----~1f
Strain, 0.001 in.lin.
Source: "Compilation of Available Information on Ti-5AI-2.5Sn Alloy," TML Memo, Batelle Memorial Institute, 1957. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3706, CINOAS/USAF CROA Handbooks Operation, Purdue University, 1995, p 5
Source: "Compilation of Available Information on Ti-5AI-2.5Sn Alloy," TML Memo, Batelle Memorial Institute, 1957. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3706, CINOAS/USAF CROA Handbooks Operation, Purdue University, 1995, p 8
Titanium (Ti)/739
6o,-------,-------,-------,-------,-------.42o
Ti.021 Ti-5AI-2.5Sn annealed titanium alloy sheet, effect of test temperature, holding time, and strain rate on tensile properties
50~------r-~---=+-------+_------+_----~350
Holding time: salid line, 10 s; dashed line, 30 mino Strain rates at temperature: curve 1,649 oC (1200 °P), 60 in.lin.lrnin; curve 2, 649 oC (1200 °P), 0.003 in.lin.lrnin; curve 3, 871°C (1600 °P), 60 in.lin.lrnin; curve 4, 871°C (1600 °P), 0.003 in.lin.lmin; curve 5, 1288 oC (2350 °P), 60 in.lin.lmin; curve 6, 1521 oC (2770 °P), 60 in.lin.lrnin. UNS R545201R54521
40~----·~~------+-------+_------+_----~280
~
~ ~
gf 30 ~--____J'--~------h~O:=:::::+___------+_----___l210 gf
({)~
~ Cií
20~_,~L-~----T_-r_------+_------+_~----;140
Source: 1.0. Morrison and R.J. Kattus, "Tensile Properties of AircraftStructural Metals at Various Rates of Loading after Rapid Heating," WADC TR 55-199, 1956. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3706, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 6
10~~-----~_f----+-~r-~+_------+_------;70
Slrain, 0.001 in./in.
Ti.022 Ti-5AI-2.5Sn annealed titanium alloy sheet, tensile stress-strain curves for room and low temperatures
280,-------_,-------r---------r---------r--------, 1960
240 1---------1-------f------__+--~'----_+------_l1680
UNS R545201R54521
200 1--------I-------f-------B-------+-------l1400
.¡¡;
160 ¡--------I-------f--u..---=9'f=------+------l1120
~
8'. ~
'~" 00- 1201---------1----~~------__+------_+------_l~0 801--------I~~--~·------__+------_+-------l560
401----~---I------~·------__+------_+------_l280
L----·~
______
4
~
______
8
~
_______ L_ _ _ _ _ _
12
Slrain, 0.001 in./in.
16
~O
20
~
~
Source: R.L. McOee, 1.E. Campbell, R.L. Carlson, and O.K. Manning, "The Mechanical Properties of Certain Aircraft Structural Metals at Very Low Temperatures," WADC TR 58-386, lune 1958. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3706, CINDASIUSAF CROA Handbooks Operation, Purdue University, 1995, p 6
740/Titanium (Ti)
7o,-------,-------,--------,-------,--------,49o
Ti.023 Ti-5AI-2.5Sn annealed titanium alloy sheet, isochronous tensile stress-strain curves at 427 oC (800°F)
Test direction: longitudinal. Sheet thickness = 1.6 mm (0.064 in.). Results are the average of two heats. UNS R545201R54521
~
ro
~
rñ
50 1-----jf--I--H'~'-----_+___7'-----_+_::;;;...=--_+-----___l 350 rñ
en
~
E
m
Source: J.O. Hatchet and E.L. Home, "Tensile and Creep Properties of A11O-AT Titanium Sheet Material at Elevated Temperatures," ASD TDR 62-524, July 1962. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3706, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 12
40~~+-f_~'---~---+--------+-------+------~280
0.2
0.4
0.6
0.8
Total strain, %
Ti.024 Ti-5AI-2.5Sn annealed titanium alloy sheet, isochronous stress-strain curves at 538 oC (1000 °F)
40,-------,-------,--------,-------,--------,280 1h
Test direction: longitudinal. Sheet thickness = 1.6 mm (0.064 in.). Results are the average of two heats. UNS R545201R54521
10 h 30~--f_--+--------+--------+~,-~-+------~210
~
ro ::;;
a.
50 h
gi 20
~
100 h
140 rñ rn
~
OL-------L-------L-------L-------L-----~O
O
0.2
0.4
0.6
Total strain, %
0.8
1.0
Source: J.O. Hatchet and E.L. Home, "Tensile and Creep Properties of A11O-AT Titanium Sheet Material at E1evated Temperatures," ASD TDR 62-524, 1962. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3706, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 12
Titanium (Ti)/7 41
Ti.025 Ti-6AI-2Sn-2Zr-2Mo-2Cr-O.25Si titanium alloy billet, tensile stress-strain curves at room and elevated temperatures
16o,-------,------,------r------,------,------.112o
140~-----~------r_-----_r------+_--~~~--~980
120~----~------t_-----_+----~+_---
Test direction: longitudinal. a-~ finished forged and duplex annealed billet 102 X 152 mm (4 X 6 in.). Billet treated at 952 oc (1745 °P), 1 h, air cooled + 900 oc (1650 °P), water quenched, 538 oC (1000 °P), 8 h
840
Source: O.L. Deel, P.E. Ruff, and H. Mindlin, "Engineering Data on New Aerospace Materials," AFML-TR-75-97, Batelle-Columbus Laboratories, lune 1975. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3717, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 23
~-----~~~--r_----_r------+_----_+----~280
~--~_r------r_-----_r------+_----_+----~140
Strain, 0.001 in.lin.
Ti.026 Ti-6AI-2Sn-2Zr-2Mo-2Cr-O.25Si titanium alloy billet, tensile stress-strain curves at room and elevated temperatures
,------r------,-------,------,------r------.1120
140~----_+------+_-----_+------+---__~----~980
120~----_r------+_----_+----~~
840
~-----~----~------+,~~~~~~~~~700& :2
"'
'" ~-----~------t_---~~~----+_----_+----__4560 ~
'"
~
·00 e r------r----~~~--_+------+_----_+----__4420~
40~-----r.6~--r_-----_r------+_----_+----~280
20~--~~------t_-----_+------+_----_+----__4140
2
4
6 Strain, 0.001 in.lin.
8
10
Test direction: transverse. o:-~ finished forged and duplex annealed billet 102 X 152 mm (4 X 6 in.). Billet treated at 952 oC (1745 °P), 1 h, air cooled + 900 oC (1650 °P), water quenched, 538 oC (1000 °P), 8 h Source: O.L. Deel, P.E. Ruff, and H. Mindlin, "Engineering Data on New Aerospace Materials," AFML-TR-75-97, Batelle-Columbus Laboratories, lune 1975. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3717, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 23
742/Titanium (Ti)
Ti.027 Ti-6AI-2Sn-2Zr-2Mo-2Cr-O.25Si titanium alloy plate, tensile stress-strain curves at room and elevated temperatures
1225
1050
Test direction: longitudinal. Plate thickness = 38 mm (1 y, in.). Conventionally processed plate: 949 oC (1740 °F), 1 h, air cooled + 538 oC (1000 °F), 8 h
875
'"
D..
700
:::E
(/)
2!
iií ~
Source: O.L. Deel, P.E. Ruff, and H. Mindlin, "Engineering Data on New Aerospace Materials," AFML-TR-75-97, Batelle-Columbus Laboratories, June 1975. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3717, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 23
525 ·iii e ~
350
5or------r~~~------~----_+------+_----_1
25r---~~----~------~----_+------+_----_1175
L-----~----~------~----~------~-----"O
2
4
6
8
10
12
Strain, 0.001 in.lin.
i
175.-----.------,------.-----~------~----_,
1225
150r------r----~------+_----_+--~~+_----_1
1050
125r------r----~------+_~~~
875
~
~
.~
Ti.028 Ti-6AI-2Sn-2Zr-2Mo-2Cr-O.25Si titanium alloy plate, tensile stress-strain curves at room and elevated temperatures
Test direction: transverse. Plate thickness = 38 mm (1Y, in.). Conventionally processed plate: 949 oC (1740 °F), 1 h, air cooled + 538 oC (1000 °F), 8 h
'" :::E D..
700
100
(/)
2!
iií 75r------r----~~~L-+------+------+------1
~ 525 ·iii
50r------r~~~------+------+------+------1
350
25r---~~----~------+_----_+------+_----_1
175
e ~
~
O
12 Strain, 0.001 in.lin.
Source: O.L. Deel, P.E. Ruff, and H. Mindlin, "Engineering Data on New Aerospace Materials," AFML-TR-75-97, Batelle-Columbus Laboratories, June 1975. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3717, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 23
Titanium (Ti)/7 43
Ti.029 Ti-6AI-2Sn-2Zr-2Mo-2Cr-O.25Si solution treated annealed titanium alloy plate, compressive stress-strain curves at room and elevated temperatures
14oor------r------.-----~------~-----,------,200
1200~----~----_4------+_----~----~----~
Test direction: longitudinal
1000~----·~-----4-------+_----_Y~--~----__4150
~ 800~-----~------+_----_+~~~+_~~~----~
:::i!
~
100 ~
-
Source: O.L. Deel, P.E. Ruff, and H. Mindlin, "Engineering Data on New Aerospace Materials," AFML-TR-73-114, Batelle-Columbus Laboratories, June 1973. As published in R. Boyer, G. Welsch, and E. Collings, Ed., Materials Properties Handbook: Titanium Alloys, ASM International, 1994, p 727
j 600~-----~------+_~~~~~----+_----_+----~ ~ 400~-----~--~~~----_+------+_----_+----~
50 200~--~~----1_----_+------r_----~----~
2
4
6 8 Strain, 0.001 mm/mm
10
200~----~------~----_,------,_----_,----__,1400
Ti.030 Ti-6AI-2Sn-2Zr-2Mo-2Cr-O.25Si titanium alloy plate, compressive stress-strain curves at room and elevated temperatures
175~-----+------+_----_+------+_----_+~~~1225
150~-----~----_4------+_----_Y~----~--__4
Test direction: transverse. Plate thickness = 38 mm (IYi in.). Conventional1y processed plate: 949 oC (1740 0 P), 1 h, air cooled + 538 oC (1000 °P), 8 h
1050
~
~
"": 125 r------t------t-------t7'----V""""'---:::t:::::==9 875 :::i! ~ W
~
u;~
~ 100
700 ~ ~
1~
00
~
~
E~
~~
8
8
~----_r~~~t-----_+------+_-----t----~350
~--~G-----_+------+_----_r-----4----__4175
Strain, 0.001 in.lin.
Source: O.L. Deel, P.F. Ruff, and H. Mindlin, "Engineering Data on New Aerospace Materials," AFML-TR-75-97, Batelle-Columbus Laboratories, June 1975. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3717, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 25
744/Titanium (Ti)
60
1400
1500
Temperature, °F 1600
Ti.031 Ti-6AI-2Sn-2Zr-2Mo-2Cr-O.25Si annealed titanium-alloy sheet, flow stress versus temperature
1700
Sheet thickness = 2.5 mm (0.10 in.). As-annealed stepstrain-rate tensile tests under argon at severa! strain rates
8 50
Source: RMI Titanium Co. unpublished data. As published in R. Boyer, G. Welsch, and E. Collings, Ed., Materials Properties Handbook: Titanium Alloys, ASM InternationaI, 1994, p 727
7
2 x 10'
6
40
ro
o..
.¡¡¡
:2: ui r1) ~
1ñ
5
-'"
ui en
5 x 10'
~
30
1ñ
4
¡; o ¡¡:
¡; o ¡¡:
3
20 8
-5
X
10
2 10
L---------~
O 750
________
800
~
________
850 Temperature, oC
~
________
900
~O
950
-,
160
140
120 .¡¡¡ .><
~
Uí
80
V--
1120
Test direction: longitudinal. 0.5 h exposure. UNS R54620 980
''\ ~oom t¡mperature
~
'x
ro 700 ~
,
........
ui
'''\
900 °F (482 OC)
560
60
420
40
280
20
140
0.04
0.08
0.16 0.12 Strain, in./in.
0.20
Source: MIL-HDBK-5H, Dec 1998, p 5-50
840
_~OO °F (31~ OC)
,..,....... ~ 100
ui r1)
Ti.032 Ti-6AI-2Sn-4Zr-2Mo duplex-annealed titanium sheet, typical tensile stress-strain curves (full range) at room and elevated temperatures
1260
180
0.24
o
0.28
!
(/)
Titanium (Ti)/745
200
1400
160
1120
-¡¡; --'" ui
120
'"~
éi5
80
40
v-
/
/;
// 1/
840
'"
a.
:2
V-
V
900°F (482 OC)
'" ~
C/J
560
8
16 12 Strain. 0_001 inJin_
20
o
24
1400
160
1120
¡V-
/
--'"
ui
'"~
éi5
40
I---
Ti.034 Ti-6AI-2Sn-4Zr-2Mo duplex-annealed titanium alloy bar, typical tensile stress-strain curves at room temperature and 482 oC (900°F) Test direction: longitudinaL Bar thickness = 28.575-31.75 mm (L125-L250 in_)_ 0_5 h exposure_ UNS R54620_ Ramberg-Osgood parameters: n(room temperature) = 34; n(900 °P) = 10
Room temperature
Source: MIL-HDBK-5H, Dec 1998, p 5-49
840
120
a.'"
:2
V--
~
900°F (482 OC) 560
/;V
V
4
Source: MIL-HDBK-5H, Dec 1998, p 5-49
ui
200
80
Test direction: longitudinal and transverse_ Sheet thickness = 1.22-2_16 mm (0_048-0_085 in_)_ 0_5 h exposure_ UNS R54620_ Ramberg-Osgood parameters: n(room temperature) = 35; n(900 °P) = 12
Room temperature
280
4
-¡¡;
1-
Ti.033 Ti-6AI-2Sn-4Zr-2Mo duplex- and triplexannealed titanium alloy sheet, typical tensile stressstrain curves at room temperature and 482 oC (900°F)
280
8
12 16 Strain. 0_001 inJin_
20
o
24
~
746/Titanium (Ti)
Ti.035 Ti-6AI-2Sn-4Zr-2Mo duplex-annealed titanium alloy bar, typical tensile stress-strain curves at room and elevated temperatures
14or------,------r------,------r------,-----.98o Room temperature 120r-----~-----+------r-----~__~~----__1840
DupIex anneaIed: 900 oC (1650 °P), 1 h, air cooIed + 593 oC (1100 °P), 8 h, air cooIed. UNS R54620
100 f-------+-------f-------,lf-------f_-----+-------j 700
Source: "Metallurgical and Mechanical Properties of Titanium Alloy Ti6AI-2Sn-4Zr-2Mo Sheet, Bar, and Forgings," TMCA, Sept 1966. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3718, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 67
20f---.~~~----f_----_+_------r_----_+_----__1140
2
4
6
8
10
Strain, 0.001 in.lin.
Ti.036 Ti-6AI-2Sn-4Zr-2Mo titanium alloy tape red plate, compressive stress strain curves at room and elevated temperatures
1200 160 1000
Specimens were cast wedges (tapered pIates) and were tested in the as-received as-cast condition. UNS R54620
140
800 r-____4-____-+______r-~~_+_----_+----__1120 100
tU
a.
:;¡;
600 80
~
400 r-----4---~~~----r-----_+_----_+----~60 40
200 20
2
4 Strain, 0.001 mm/mm
~
~
1ií
Source: O.L. Deel, "Engineering Data on New Aerospace Structural Materials," AFML-TR-77-198, Batelle-Columbus Laboratories, 1977, p 28. As published in R. Boyer, G. Welsch, and E. Collings, Ed., Materials Properties Handbook: Titanium Alloys, ASM International, 1994, p 365
Titanium (Ti)/747
32
-
28
-----
r--
24 ¡ - - ~ 20
r-.....
r--..
16
~'"
12 ¡ - - -
Strain rate vs-:t;:;;;-
8 f---------
---
~
3.5
Tested at 915 oC for a + ~ (a) and ~ (b). For both, the stress decreases with strain (flow). UNS R54620
2.5
\
"",
iij
1.5
o 4.0
42
3.5
36
3.0
~ 30
2.5
... ... . .
'"
'2"
f-
1.5
12
1.0
6
0.5
oL----L----~---L----~--~----~--~--~o
o
0.1
(b)
0.2
0.3
0.4 0.5 True strain
0.6
2
2.0 c:
Strain rate vs strain
18
'",
~
.Stress vs strain
'"
:::>
0.5
48
~ 24
'"
¡!:
1.0
\
2
~
\
(a)
'",
c: 2.0 .~
1
t---...
4 f--------O
Ti.037 Ti-6AI-2Sn-4Zr-2Mo titanium alloy forging, true flow stress-strain and strain-strain rate curves
3.0
"-
'"~
iij
Stress ~s strain
4.0
0.7
0.8
~ ~'"
Source: S.L. Semiatin et al., in Process Modeling Fundamentals and Applications to Metals, American Society for Metals, 1980, p 387-408
748/Titanium (Ti)
Ti.038 Ti-6AI-2Sn-4Zr-2Mo titanium alloy, true stress-strain curves showing effects of temperature and strain rate
15or-------~------,_------_,------_,------__,
- 20 120
I---=-=--.::.=-t=-=-=-=-=-~~t~=-=-=-:=-=-t=-:::.::.::::.tr-",:9,-,-15=-·",:C~-I
Strain rate: solid line, 1O.O/s; dashed line, l.O/s. UNS R54620 Source: G.D. Lahoti and T. Altan, AFML-TR-79-4156, Dec 1979. As published in R. Boyer, G. Welsch, and E. Collings, Ed., Materials Properties Handbook: Titanium Alloys, ASM Intemational, 1994, p 366
- 15
~ 90
980 ·C
-----:¡.--
.....
955 ·C
i~ ~ ~l.-...-..-.. .-...-:-:+-••.• ..-.-.-9-151.:010.C - 955 '·C 260
......... .
1
•••
~
30
,1,
... . . . .. ... 0.2
. . . .......... . . . ...
•••••.•••• 980 ·C 1
.. ........ • •••••••• 1010·C
0.6
0.4
-
0.8
5
1.0
True strain
Ti.039 Ti-6AI-2Sn-4Zr-2Mo titanium alloy, true stress-strain curves showing effects of temperature and strain rate
70r-------,--------,-------,--------,--------~10
60~-----~---+------4----~---~
50 ~
Strain rate: solid line, O.lIs; dashed line, O.Olls. UNS R54620
- 8
~---=- .
---r---~~·~··~·t·~·~.~.~.~.~.~.~------~--955·C ........... ·910·C - 6
~~
g¡
~
~
w
~
~ ~
w ~
~
~
~ 30
rI:::::;;;::::::=t====t====:j=~ill:::f:t=-----~ 980·C - 4 ...............
..................
::::::::::::::::
·955 ·C ··980·C - 2
10~---r------+------4----~----~
•••..•••.••••••...••..•...••.•.•• ·1010·C
°0L-------0~.2--------0L.4-------0~.-6-------0~.8------~1.J True strain
~ 2
Source: G.D. Lahoti and T. Altan, "Research to Develop Process Models for Producing a Dual Property Titanium Alloy Compressor Disk," AFWAL-TR-80-4162, 1980. As published in R. Boyer, G. Welsch, and E. Collings, Ed., Materials Properties Handbook: Titanium Alloys, ASM Intemational, 1994, p 366
Titanium (Ti)/749
Ti.040 Ti-6AI-2Sn-4Zr-2Mo titanium alloy forging, true flow stress-strain curves
280 240
f\.
200
~
"' ... 160
............
-- --
~
Flow stress of the a-~ titanium alloy. The critical strains and temperatures for which the acicular a rnicrostructure transformed to an equiaxed rnicrostructure are shown. It is found that deformation to strains of the order of 1.0 at 900 oc (1650 °F), followed by heat treatment at 955 oC (1750 °F), produced the desired transformation. UNS R54620
899 oC, 0.1/s
-- ---- ~-
Source: T.G. Byrer, S.L. Semiatin, and D.C. Vollmer, Ed., Forging Handbook, Forging Industry Association of America, 1985, p 116
r---. "15
----------- --
982 oC, 0.001/s
10
--13 - - - (u+f3)
5
0.4 True plastic strain
0.2
0.6
120
Ti.041 Ti-6AI-2Sn-4Zr-2Mo titanium alloy forged compressor discs, typical tensile stress-strain curves at room temperature
1120
160
140
0.8
- r-:::-
~
980
Duplex annealed 968 oC (1775 °F), 1 h, air cooled, 593 oC (1100 °F), 8 h, air cooled. UNS R54620
840
700
100
(\l
a.
:2
560 !Ji
'"
~ 60
420
40
280
20
140
0.02
0.04
0.06 Strain, in.lin.
0.08
0.10
o
0.12
Source: G. Curbish1ey, "Mechanica1 Properties of Ti-6Al-6Sn-4Zr-2Mo Forgings," Garrett Corp. Airesearch Manufacturing Co., 1970. As published in Aerospace Structural Metals Handbook, Vo14, Code 3718, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p49
750/Titanium (Ti)
120
80
-
~
100
V--
,/
840
Ti.042 Ti-6AI-2Sn-4Zr-2Mo duplex-annealed titanium alloy forged compressor discs, tensile stress-strain curves at 316 oC (600°F)
700
Duplex annealed 968 oC (1775 °P), 1 h, air cooled, 593 oC (1100 °P), 8 h, air cooled. UNS R54620
560
'"
o.. ::!:
Source: G. Curbishley, "Mechanical Properties of Ti-6AI-6Sn-4Zr-2Mo Forgings," Garrett Corp. Airesearch Manufacturing Co., 1970. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3718, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 68
420 ui UJ ~
iñ 40
280
20
140
0.02
0.04
0.06
o
0.08
0.10
Strain, in.lin.
100
80
Ti.043 Ti-6AI-2Sn-4Zr-2Mo duplex-annealed titanium alloy forged compressor discs, tensile stress-strain curves at 427 oC (800°F)
840
120
,I
~
~
p--
-
Duplex annealed 968 oC (1775 °P), 1 h, air cooled, 593 oC (1100 °P), 8 h, air cooled. UNS R54620
700
560
'"
o.. ::!:
420 ui UJ
~
40
280
20
140
0.02
0.04
0.06
0.08 Strain, in.lin.
0.10
0.12
0.14
o
0.16
Source: G. Curbishley, "Mechanical Properties of Ti-6AI-6Sn-4Zr-2Mo Forgings," Garrett Corp. Airesearch Manufacturing Co., 1970. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3718, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 68
Titanium (Ti)/751
80
.¡¡; -'" ui (/)
60
~
~
Duplex annealed 968 oc (1775 °P), 1 h, air cooled, 593 oc (1100 °P), 8 h, air cooled. UNS R54620
560
(1
420
I
8:.
:2
:
lZ
I
~
Ti.044 Ti-6AI-2Sn-4Zr-2Mo duplex-annealed titanium alloy forged compressor discs, tensile stress-strain curves at 538 oC (1000 °F)
700
100
~
40
280 ¡¡;
20
140
0.02
0.04
0.06 Strain, in.lin.
0.08
0.10
o
0.12
Source: G. Curbishley, "Mechanical Properties ofTi-6AI-6Sn-4Zr-2Mo Forgings," Garrett Corp. Airesearch Manufacturing Co., 1970. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3718, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 68
752/Titanium (Ti)
200
~
160
~
V BIV'
ro
80
V
O
Test specimens 6.3 mm (0.25 in.) diam X 25.4 mm (1 in.) gage. Duplex anneal for curves A and B: 904 oC (1660 °P), 1 h, air cooled + 593 oC (1100 °P), 8 h, air cooled. Duplex annealing for curves C and D: 910 oC (1670 °P), 1 h, fast air cooled + 593 oC (1100 °P), 8 h, air cooled. Curve A: ultimate tensile strength = 1255 MPa (182 ksi); tensile yield strength = 1165 MPa (169 ksi); elongation in 25 mm (1 in.) = 15%; reduction of area = 37%. Curve B: u1timate tensile strength = 1220 MPa (177 ksi); tensile yield strength = 1117 MPa (162 ksi); elongation in 25 mm (1 in.) = 13%; reduction of area = 32%. Curve C: ultimate tensile strength = 1386 MPa (201 ksi); tensile yield strength = 1317 MPa (191 ksi); e1ongation in 25 mm (1 in.) = 9%; reduction of area = 22%. Curve D: ultimate tensile strength = 1276 MPa (185 ksi); tensile yield strength = 1227 MPa (178 ksi); elongation in 25 mm (1 in.) = 10%; reduction of area = 22%. UNS R56260
ro !L
:2
l
560 ro
V
/ /
40
1120
840
/ /
ro
'"~
Ti.045 Ti-6AI-2Sn-4Zr-6Mo duplex-annealed titanium alloy forging, duplicate stress-strain curves for two different duplex-annealing treatments
iI ~/
Al
120
1400
280
/ /
o
+-0.04-1 Strain, % ,-----,------,-----,-----,------,-----.14oo
1------+-----~~--_+~~~------+_--~1120
1------+----+~---,~----~------+_--~840
ro !L
:2
gf ~
1------+f~--~~--_+----~------+_--~560ro
1---,~+---F-~----_+----~------+_--~280
~
____JL____- L____
~
____
Strain, %
~
______L -_ _
~O
SOUTce: Personal communication from D.H. Wilson, RMI Co. to J.R. Kattus, 31 Jan 1972. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3714, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 9
Titanium (Ti)/753
-
1200
'
800
'" :2 D..
'"~
ro
400
.....
/~
- 160
....... Room temperatlre
1000
Ti.046 Ti-6AI-4V solution treated and aged titanium alloy, all forms, tensile stress-strain curves for room and elevated temperatures
,
Test direction: longitudinal. 0.5 h exposure. UNS R564001R56401
- 140 "205 oC X
............ -"
'x 370 oc
-- -----
r
Source: MIL-HDBK 5, 1991. As published in R. Boyer, G. Welsch, and E. Collings, Ed., Materials Properties Handbook: Titanium Alloys, ASM Intemational, 1994, p 592
- 120
--~ 480 oC
- 100 I--~
540 oC
~
'"~
- 80
-
ro
60
- 40 200 -
O O
0.04
0.08
20
o
0.12
0.16
Strain, mm/mm
160
140
Ti.047 Ti-6AI-4V annealed titanium alloy sheet, typical tensile stress-strain curves at room temperature (full range)
1120
r
-
--
-
980
...... ........
120
'x
Test direction: longitudinal and transverse . UNS R564001R56401
840
Source: MIL-HDBK-5H, Dec 1998, p 5-68 700
100
/f
:2
560
'"
~
ro 60
420
40
280
20
140
0.02
0.04
0.06 Strain, in.Jin.
0.08
0.10
o
0.12
754/Titanium (Ti)
Ti.048 Ti-6AI-4V, solution treated and aged titanium alloy sheet, typical tensile stress-strain curves (full range ) at room and elevated temperatures
2oo.-----,------,-----,----~------r_--__,1400
Test direction: longitudinal and long transverse. 0.5 h exposure. Ramberg-Osgood parameters: n(room temperature) = 16, n(200 °F) = 22, n(400 °F) = 15, n(600 °F) = 11, n(800 °F) = 9.4, n( 1000 °F) = 6.2. UNS R56400/ R56401
~----+-----~-----+~~~~~~~~~1120
840
'"
o.. :2
~ u)
Source: MIL-HDBK-5H, Dec 1998, p 5-79
u)
"'
~
560
i"'
~~~~----~-----+-----4------~--~280
L -_ _ _ _
~
4
_ _ _ _- L_ _ _ _- L_ _ _ _
8
~
_ _ _ _ _ _L __ _
12 16 Strain, 0.001 in.lin.
20
~O
24
Ti.049 Ti-6AI-4V, solution treated and aged titanium alloy sheet, typical compressive stress-strain curves at room and elevated temperatures
1400
200
160
200 °F (93 oC
120
400 IOF (204 oC) 600 °F (316 OC) 800 °F (427 OC)
Test direction: longitudinal. 0.5 h exposure. RambergOsgood parameters: n(room temperature) = 22, n(200 °F) = 27, n(400 °F) = 22, n(600 °F) = 12, n(800 °F) = 11, n(lOOO °F) = 5.7. UNS R564001R56401
1120
I
'00
-'"
840
I
u)
"' ~
"'~ 560
40~-.~~----~-----+----~------r---~280
L-----~4----~8------1L2----~16----~2~0----~2i
Strain, 0.001 in.lin.
'"
u)
1000 °F (538 OC)
(IJ
80
Source: MIL-HDBK-5H, Dec 1998, p 5-80 o.. :2 é'i5
Titanium (Ti)/755
Ti.OSO Ti-6AI-4V, solution treated and aged titanium alloy sheet, typical compressive stress-strain curves at room and elevated temperatures
2oor-----,------r-----,------r-----~----,1400
Test direction: long transverse. 0.5 h exposure. RambergOsgood parameters: n(room temperature) = 13, n(200 °F) = 15, n(400 °F) = 14, n(600 °F) = 10, n(800 °F) = 11, n(1000 °F) = 5.7. UNS R564001R56401
160 \-----+----+--~-j,~=--------j------+---____l1120 409°F (204 °9) 609 °F (316 °9) 120 f------+-----,fIh~__7"'~~--801 °F (427 °1)------1840 ~
~
~
~
1000 °F (538 OC)
UJ
Source: MIL-HDBK-5H, Dec 1998, p 5-81
!Z
~ 80 f-----4~~~-b~--_+---~~----+_--____l560
40f--.~~----+----_+---~~----+_---~280
°0L-----~4------8L------~12~--~1L6-----2~0~--~21 S!rain, 0.001 in.lin.
Compressive tangen! modulus, GPa
200 0r-____=r-____-=5,.:.6_____8-T4'--__---'-11r=2____....:1T40"---___ 16~400
Ti.OSl Ti-6AI-4V, solution treated and aged titanium alloy sheet, typical compressive tangent modulus curves at room and elevated temperatures
160 f------l-~"'"---..l.:=----_+------f------+_--____l 1120
Test direction: longitudinal. 0.5 h exposure. RambergOsgood parameters: n(room temperature) = 22, n(200 °F) = 27, n(400 °F) = 22, n(600 °F) = 12, n(800 °F) = 11, n(1000 °F) = 5.7. UNS R564001R56401 Source: MIL-HDBK-5H, Dec 1998, p 5-80
120
840
·00
'"
o.
""
~
UJ
'"
80
560
40f------~----+--~_+~1H~+-----+_--____l280
°OL-----J4------8L----~~12-L-LLi1U6-----2~0----~21 Compressive tangen! modulus, 106 psi
~
756/Titanium (Ti)
200 or-_ _-,28_ _ _5T"""6_ _----,84_ _ _11T"""2_ _ _1-.,.4_o_ _~16~400
Ti.052 Ti-6AI-4V, solution treated and aged titanium sheet, typical compressive tangent modulus curves al room and elevated temperatures
1601------""-..l--------'l"-----+---j-----+-----I 1120
Test direction: long transverse. 0.5 h exposure. RambergOsgood parameters: n(room temperature) = 13, n(200 °P) = 15, n(400 °P) = 14, n(600 °P) = 10, n(800 °P) = 11, n(1000 °P) = 5.7. UNS R564001R56401
Compressive tangent modulus, GPa
Source: MIL-HDBK-5H, Dec 1998, p 5-81 120 I--~._~--~~---+-~~~--+-----IMO 400 °F (204 OC)
o.. :2 ~
600°F (316 OC)
~ en
~
'"
!!!
1
Cií
ro
80 1----+-~~~--~~~~~--+-----I560 800°F (427 OC)
°0L---~4---8L--~~12-L~Li1U6---2~0--~2! Compressive tangenl modulus, 106 psi
Ti.053 Ti-6AI-4V aged titanium alloy sheet, tensile stress-strain curves at room and elevated temperatures
1400
200
Room temperature
160
Test direction: longitudinal. Sheet thickness = 1.6 and 3.18 mm (0.063 and 0.125 in.) Treatment: 927 oC (1700 °P), 3-20 min, water quenched, + 482-510 oC (900-950 °P), 4 h. UNS R564001R56401
1120
200°F (93 OC) 400°F (204 OC) 840 ro o.. 600°F (316 OC)
120 '00 -'"
:2
'"
'"
~
!!!
560
80
401---
~~L-
-+____-+_____ 280
___
~----4L-----8~----1~2-----71~ Slrain,
0.001 in.lin.
Cií
Source: "Surnmary of Mechanical and Physical Property Data Collected, Including Tensile Creep and Fatigue," Lockheed-Georgia, Dec 1962. As published in Aerospace Structural Metals Handbook, Vo14, Code 3707, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 14
Titanium (Ti)/757
200
Ti.054 Ti-6AI-4V aged titanium alloy sheet, tensile stress-strain curves at room and elevated temperatures
1400
Room temperature
Test direction: transverse. Sheet thickness = 1.6 and 3.18 mm (0.063 and 0.125 in.). Treatment: 927 oC (1700 °F), 3-20 min, water quenched, + 482-510 oC (900-950 °F), 4 h. UNS R564001R56401
~--------~---------+----~~~--------~1120
°F (93 OC) 400°F (204 OC)
~---r-200
~--------1-------~ít~~~==~~~~~~840 600°F (316 OC) 800°F (427 OC) 900 °F (482 oC)
~---------~~~~--+---------~~~~~560
&.
:2 ~
i
Source: "Summary of Mechanical and Physical Property Data Collected, Including Tensile Creep and Fatigue," Lockheed-Georgia, Dec 1962. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3707, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 14
1000 °F (538 OC)
~----~~~---------+----------r-------~280
~--------~--------~--------~~------~o
4
12
8
16
Strain, 0.001 inJin.
14or------,------,------,------,------,------,98o
120~-----+------+------+----~~~~-+----~840
100~-----_+_------~----~~~~~~--_+----~700
Ti.055 Ti-6AI-4V annealed titanium alloy sheet, compressive tensile stress-strain curves at room and elevated temperatures
Test direction: transverse. Sheet thickness = 1.6 mm (0.063 in.). Results are the average of eight heats. UNS R564001R56401 Source: J.K. Childs and M.M. Lemcoe, "Determination of Materials Design Criteria for 6Al-4V Titanium Alloy at Room and Elevated Temperatures," WADC TR 58-246, Aug 1958. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3707, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 18
40~-----_+_~~~+-7~--_+------+_----_+----~280
17~--~------~------r_----~----~140
2
4
6 Strain, 0.001 inJin.
8
10
758/Titanium (Ti)
200
Ti.056 Ti-6AI-4V aged titanium alloy sheet, compressive stress-strain curves at room and elevated temperatures
1400 Room temperature
160
200°F (93 oC)
Test direction: longitudinal. Sheet thickness = 1.6 and 3.18 mm (0.063 and 0.125 in.). Treatment: 927 oC (1700 °F), 3-20 min, water quenched, + 482-510 oC (900-950 °F), 4 h, air cooled. UNS R564001R56401
1120
I
400°F (204 OC) 600 °F (316 ~C) 800°F (427 OC)
120 'ijj
"'
840
I
(/)
al
a.
::2;
900°F (482 OC)
~
1ñ
I
80
1000 °F (538 OC)
(/)
~
560
1ñ
Source: "Surnrnary of Mechanical and Physical Property Data Collected, Including Tensile Creep and Fatigue," Lockheed-Georgia, Dec 1962. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3707, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 18
40~--~~~------~------~------~----~280
°0L-------4~------8~------1~2-------1~6-------J2~
Strain, 0.001 in.lin.
240 , - - - - - , - - - - , - - - - - - - r - - - . , - - - - - - , 1680
Ti.057 Ti-6AI-4V aged titanium alloy sheet, compressive stress-strain curves at room and elevated temperatures
200 f---------~------~------~------+_----~ 1400
Test direction: transverse. Sheet thickness = 1.6 and 3.18 mm (0.063 and 0.125 in.). Treatment: 927 oC (1700 °F), 3-20 min, water quenched, + 482-510 oC (900-950 °F), 4 h, air cooled. UNS R564001R56401
160 f-----+----+----".O""""'7""f==-----+-----I1120 400 01;' (204 OC) 600 °F (316 OC) -'" 800°F (427 OC)
'ijj
~
1ñ ~
I
_ _ 1000 °F (538 OC)
80
40
o o
4
8 12 Strain, 0.001 in.lin.
16
al
a.
::2;
840
~
Source: "Surnmary of Mechanical and Physical Property Data Collected, Including Tensile Creep and Fatigue," Lockheed-Georgia, 1962. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3707, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 19
Titanium (Ti)/759
Ti.058 Ti-6AI-4V aged titanium alloy sheet, tensile alloy stress-strain for room and low temperatures
28o,-------,-------,--------r-------,-------,196o -320°F (-196 OC)
Test direction: longitudinal and transverse. Sheet thickness = 1-6 mm (0.063 in.). Treatment: 921°C (1690 °F), 12 min, water quenched, + 482 oC (900°F), 4 h. UNS R564001R5640 1
240~------+--------~------~--~~-+------~1680
1400
200~------+--------~------~~--
.¡¡;
160
1120
~
~ ~
m
W
i
00
(/) 120
~------+_----.,._t_------_f_------_+_------~ 840 ~
Source: "Details of Data Collected Program Test Techniques and Results for Tension, Compression, Bearing, Shear, Crippling, Joints and Physical Properties," Lockheed-Georgia, Dec 1962. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3707, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 14
80~------~~-----t-------_f_------_+_------~560
40~--~--+_-------t-------_f_------_+_------~280
4
12
16
Strain, 0.001 in./in.
Ti.059 Ti-6AI-4V annealed titanium alloy sheet, typical tensile stress-strain curves at room, elevated, and low temperatures
280,---------,----------,----------,---------,1960 -425 °F (-254 OC) 240~----·----+_---------_f_--------_h~------~1680
Sheet thickness = 1-6 mm (0.064 in.). UNS R564001R56401
200r---------+----------_f_----~---b~------~1400
.¡¡;
160 r-----.----+------------V'------T'---==......--------~ 1120
~
~ ~
ui
1
840
1W
40~--~~~~~~------f---------_r--------_4280
~--------L-------~--------~--------~O
16
Strain, 0.001 in./in.
I
Source: J.K. Childs and M.M. Lemcoe, "Determination of Materials Design Criteria for 6Al-4V Titanium Alloy at Room and Elevated Temperatures," WADC TR 58-246, Aug 1958. R.L McGee, J.E. Campbell, R.L. Carlson, and G.K. Manning, "The Mechanical Properties of Certain Aircraft Structural Metals at Very Low Temperature," WADC TR 58-386, June 1958. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3707, CINDAS/USAF CROA Handbooks Operation, Purdue University, 1995,p 13
760/Titanium (Ti)
2oo,-----,------,------,-----,------,------,14oo
Ti.060 Ti-6AI-4V titanium alloy plate, typical tensile stress-strain curves at room and elevated temperatures
~----~-----+------~~~R-o~om--te-mLP~er~at+u~re----~1120
Test direction: longitudinal and long transverse. Solution treated and aged. Plate thickness = 6.35-25.40 mm (0.250-1.000 in.). 0.5 h exposure. Ramberg-Osgood parameters: n(room temperature) = 16, n(400 °P) = 19, n(600 °P) = 15, n(800 °P) = 11. UNS R564001R56401
~----~----~------~----4_-----+----~840
ro
400°F (204 oC) 600 °F (31'6 oC) 800°F (427 OC)
c..
::;;:
Source: MIL-HDBK-5H, Dec 1998, p 5-82
f
¡¡¡ ~----4_+h~~------~----4_-----+-----4560
~--~4_-----+------~----~-----+------1280
L -____
~
____- L_ _ _ _- L_ _ _ _
4
200
160
.¡¡;
o
28
~
_ _ _ _ _ _L -_ _
16 12 Strain, 0.001 in.lin.
Compressive tangent modulus, GPa 56 84 112
--V-
20
ui 1/)
!':'
¡¡¡ 80
/
I
24
Ti.061 Ti-6AI-4V solution treated and aged titanium alloy plate, typical compressive stress-strain and compressive tangent modulus curves at room and elevated temperatures
R564ooIR56401 840
/
Source: MIL-HDBK-5H, Dec 1998, p 5-82 ro
c..
::;;:
:i
~ 560
/
280
4
Test direction: longitudinal and long transverse. Sheet thickness = 6.35-25.40 mm (0.250-1.000 in.). RambergOsgood parameter: n(room temperature) = 26. UNS
1120
~
/
-'"
~O
140
. /~
..............
120
40
8
20 12 16 Strain, 0.001 in.lin. 6 Compressive tangent modulus, 10 psi 8
o
24
Titanium (Ti)/761
Ti.062 Ti-6AI-4V annealed titanium alloy bar, tensile stress-strain curves for room and elevated temperatures
140r------,------,------.------r------,------.980
120~----4-----_+------+_----_vL---~
__~~
100~----~------+_----_+~~--+_~--=+------;
~ 80~----~------+_~~~~--~~--~~----~
Sheet thickness = 31.75 mm (111 in.). Results are the average of 12 heats. UNS R564001R56401 700
560 ~ :2
ID
ID
~
en
Source: J.K. Childs and M.M. Lemcoe, "Determination of Materials Design Criteria for 6Al-4V Titanium Alloy at Room and Elevated Temperatures," WADC TR 58-246, Aug 1958. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3707, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 13
~
Ci5 6Ú~-----~----_A~~~_+----~~~---+------; 420 Ci5
40~----~~~~~~~--_+------+------+------;
280
20~~~~L---_+------+_----~----~----~
140
2
4
6
8
10
0 12
Sltrain, 0_001 in.lin.
140,------,------r------,------,------,------.980
120~----~----_+------+_--__~~~~~--~MO
100~----_+------+_-----+~~--t,~
700
40~----~~~~~~--_+------+_----_+----__4280
20r---~~~----+_----~------+_----_+----~140
2
4
6
Slrain, 0.001 in.lin.
8
10
Ti.063 Ti-6AI-4V annealed titanium alloy bar, compressive stress-strain curves for room and elevated temperatures
Sheet thickness = 31.75 mm (111 in.). Results are the average of 12 heats. UNS R564001R56401 Source: J.K. Childs and M.M. Lemcoe, "Determination of Materials Design Criteria for 6AI-4V Titanium Alloy at Room and Elevated Temperatures," WADC TR 58-246, Aug 1958. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3707, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 19
762/Titanium (Ti)
Ti.064 Ti-6AI-4V annealed titanium alloy extrusion, typical tensile stress-strain curves at room, elevated, and cryogenic temperatures
2 8 o , - - - - - - - , - - - - - , - - - - . . , . - - - - . , - - - - - - , 1960 -423 °F (-253 OC) 240 ¡----+-----+----+----:......---+_--__j 1680
200
0.5 h exposure. Ramberg-Osgood parameters: n(-243 °F) = 20, n(-321 °F) = 21, n(-110 °F) = 20, n(room temperature) = 33, n(400 °F) = 29, n(700 °F) = 19, n(900 °F) = 9.6. UNS R564001R56401
¡----+-----+------:~~---+_--__j1400
Source: MIL-HDBK-5H, Dec 1998, p 5-66
L-_--, 400°F (204 OC) I _ _ _~/b~::..4::::::::::;;;:::l--700 °F (371°C) 80 f900°F (482 °C),-----l 560
40/-----:~~~----+----+----+-----j280
~
__
~
_ _ __ L_ _ _
4
8
~
_ _ _L -_ _
12
~O
16
20
Strain, 0.001 in.lin.
200
1400
160
1120
Ti.065 Ti-6AI-4 V annealed titanium alloy extrusion, typical compressive stress-strain curves at room and elevated temperatures 0.5 h exposure. Ramberg-Osgood parameters: n(room temperature) = 21, n(400 °F) = 19, n(700 °F) = 14, n(900 °F) = 9.8. UNS R564001R56401
Room temperature
Source: MIL-HDBK-5H, Dec 1998, p 5-67 840
120
400°F (204 OC)
~
vi
700°F (371, OC) 900°F (482 OC)
~
é'ii
(J)
~
560
80
4
8
12
Strain, 0.001 in.lin.
16
'"
a. :2
I
vi
(J)
en
Titanium (Ti)/763
200
o
28
Compressive tangent modulus, GPa 56 84 112
Ti.066 Ti-6AI-4V annealed titanium alloy extrusion, typical compressive tangent modulus curves at room and elevated temperatures
140
1120
160
'-.¡¡;
~emperature
r--- t-..
120
'--
-'"
ui
"'
~ 80
Source: MIL-HDBK-5H, Dec 1998, p 5-67 840
~
~ 1"--~ 700 °IF (371°C)
560
~~
4
24
-
r ~ Koc ,130/S
--
1200
1000
ui
"'
~
600
400
1
o
8 12 16 20 Compressive tangent modulus, 106 psi
1400
::;:
~ ::;:
280
40
~ 800
Test direction: longitudinal. 0.5 h exposure. RambergOsgood parameters: n(room temperature) = 21, n(400 °P) = 19, n(700 °P) = 14, n(900 °P) = 9.8. UNS R564001R56401
¡-....
"l'..~ r---........
200
UNS R564001R5640 1 4
21°C, 10- /s
-
150
"'~1~
475 oC, 930/s
( re
541::- ~ 540 t;;:- ~ 0
fl
---
-
~ """::::
50
200
0.02
0.04
0.06 0.08 Strain, mm/mm
Ti.067 Ti-6AI-4V solution treated and aged titanium alloy rod, temperature and strain rate effects on tensile stress-strain curves
0.10
0.12
o
0.14
Source: D.L. McLellan and T.W. Eichenberger, "Constitutive Equation Deve10pment (COED)," Vol 1, Technical Summary, SAMSO-TR-68320, Ju1y 1968, P 80.. As pub1ished in R. Boyer, G. Welsch, and E. Collings, Ed., Materials Properties Handbook: Titanium Alloys, ASM Intemational, 1994, p 593
764/Titanium (Ti)
500
400
&.
:;;:
1\
~ ~e .....,
300
ui en
- 70
Ti.068 Ti-6AI-4V titanium alloy, temperature effect on flow stress-strain curves
-
Strain rate at lO/s with a starting microstructure of about 50% ex in a transfonned ~ matrix. UNS R564001R56401
60
- 50
r---,
-
~
tí
~ ¡¡:
200
~
900 oC
- 20
1000 oC
100
-
20
40
60
80
Strain, %
100
120
10
o
140
Source: G.w. Kuhlman, ALCOA, Forging Division. As published in R. Boyer, G. Welsch, and E. Collings, Ed., Materials Properties Handbook: Titanium Alloys, ASM International, 1994, p 593
Titanium (Ti)/765
700 600
---
600 oC -
Ti.069 Ti-6AI-6V-2Sn titanium alloy, true stress-strain curves (a) sensitized (b) reheated
- 100
~
- 80
500
'" ::2:. Il.
.,.,
400
~ ~ 300
¡..-
::J
----700 oC
200
g¡ ~
r-----
750 oC
t=
.¡¡;
- 60 "".
1---
800 oC
tí
'"
1-
/900 oC
850 oC
- 40 ~
Source: H.G. Suzuki et al., Effect of Phase Transformation on the Hot Workability ofTi·8AI·6V-2Sn, Ti-5AI-2.5Sn, and Other Alloys, Sixth World Conference on Titanium, P. Lacombe, R. Tricot, and G. Beranger, Ed., Les Editions de Physique, Paris, 1989, P 1427-1432. As published in R. Boyer, G. Welsch, and E. Collings, Ed., Materials Properties Handbook: Titanium Alloys, ASM futernational, 1994, p 663
- 20
100 1100 oC O
"1000 oC
o
(al
500 700 oC 400
'" ::2: .,rñ
Il.
300
~
tí
~'"
200
""----~, 1'--.... ........
-.......... t-......
--
~
60
~ 30
-
20
1000 oC 1100 oC -
10
900°C
'-
-
~ - 40 gf
~
100
70
- 50
t--..
1----~
-
1200 oC 0.1
0.2
0.3
Strain, in.lin.
0.4
o
0.5
In the sensitized mode, smooth stress-strain curves are shown aboye 750 oC (1380 °P), and work hardening occurs below 665 oC (1220 °P). At 850 oC (1560 °P), for example, the stress level of the reheated materials is almost twice that of the sensitized material at low strain. The sensitized mode involved quenching from 1220 oC (2190 °P) to the test temperature. The reheated mode involved heating to the test temperature in 60 s.
!!l
t=
766/Titanium (Ti)
180 160 140
(
-
1120
Ti.070 Ti-6AI-6V-2Sn annealed titanium alloy sheet, typical tensile stress-strain curves (full range ) at room temperature
980
Test direction: longitudinal and long transverse. UNS R56620
1260
1--....
Source: MIL-HDBK-5H, Dec 1998, p 5-108 840
120
en 700 ~
~ 100 vi
'" ~
vi
'"
80
560 ~
60
420
40
280
20
140
O O
en
0.02
0.04
0.06 0.08 Strain, in.lin.
0.10
0.12
o
0.14
Ti.071 Ti-6AI-6V-2Sn annealed titanium alloy sheet, tensile stress-strain curves at room and elevated temperatures
200,---------r---------r---------,---------,1400
Room temperature
Annealed, 760 oC (1400 °F), 4 h. UNS R56620
1120
Source: "Properties of Ti-6Al-6V-2Sn," Timet Titanium Engineering Bulletin No. 10, TMCA, Sept 1967. As published in Aerospace Structural Metals Handbook, Vo14, Code 3715, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 25
200 °F (93 OC) 400 °F (204 OC) 600 °F (316 OC)
.¡¡;
840
-'"
vi
vi
800 °F (427 oC)
'"
~
'"
560
1-------.W/7L-+---------+-----+----- 280
~------~---------L---------6L-------~80
Strain, 0.001 in.lin.
en c.. :2
~
Titanium (Ti)/767
200 -80°F
(-b OC)
/
180
1260
--........-......
r--...'"
1"'-
160 180°F (82 OC)
Ti.072 Ti-6AI-6V-2Sn mill-annealed titanium alloy plate, tensile stress-strain curves at several temperatures
1400
O o~ (-18 OC)
P1ate thickness = 12.7 mm (0.5 in.). Tensi1e yie1d strength = 1120 MPa (163 ksi). Tested to ASTM-399-70T. UNS R56620
1120
"" Room temperature ""
140
970
120
840
gf 100
700
~
8:.
:2
~
ui
Ul
~
80
560
60
420
40
280
20
140
0.02
0.04
0.06 Strain, in.lin.
0.08
C/J
o
0.10
0.12
Ti.073 Ti-6AI-6V-2Sn titanium alloy plate, tensile stress-strain curves at room temperature for different heat treatments
200.-----,----,------,-----r-----,----,-----,1400
180~--~~·~--·---·~~R--S_+-----+----_r----_r--~1260 I
____
-----r----- RM
TM
160 ~--J¡.--~.-::t-=-=-:-=+::;~~~::j;:;;;;:;:::::t:::::;j==~ 1120 -.1= : =t--. _ 1- _RD ",:." RB
, . . p:--= -=--
140~17~~--_1-----_+-----+-----r-----r--~970
120 ~-I---~--_1-----_+-----+-----r-----r--~ 840 '"
~ gf 100
~ 700
~
00
~
80~--~----_+----_+----_r----~----~--__1560
60~--~----_+----_+----_r----~----~--__1420
40H---~----_+----_+----_r----~----~--__1280
20~--~----_+----_+----_r----~----~--__1140
°OL----0-.0~2----0~.0-4----0~.0-6----0.~0-8---0-.~10----0~.1~2--~0.1S
Strain, in.lin.
Source: M.E Amateau, W.D. Ranna, and E.G. Kendall, "F-15 Program Final Report: Ti-6Al-6V-2Sn and Ti-6Al-4V Fatigue Crack Propagation," ATR-72(9990), The Aerospace Corp., Sept 1971. As pub1ished in Aerospace Structural Metals Handbook, Vol 4, Code 3715, CINDAS/USAF CRDA Randbooks Operation, Purdue University, 1995, p 26
00
AH curves 12.7 mm (0.5 in.) except RS which is 32 mm (1.25 in.). Heat treatment: RB, beta annea1ed, 1010 oC (1850 °P), 1 hin vacuum, argon coo1ed. RD, dup1ex annea1ed, 927 oC (1700 °P), 1 h in vacuum, argon coo1ed + 760 oC (1400 °P), 1 h, argon coo1ed. RM and TM, mill annea1ed. RS, so1ution treated and aged, 913 oC (1675 °P), 0.25 h, water quenched + 593 oC (1100 °P), 4 h. Yie1d strengths MPa (ksi): RB, 965 (140); RD, 1040 (151); RM, 1123 (163); RS, 1193 (173); TM, 1096 (159). Tested to ASTM-399-70T. UNS R56620 Source: M.E Amateau, w'D. Ranna, and E.G. Kendall, "F-15 Program Final Report: Ti-6Al-6V-2Sn and Ti-6Al-4V Fatigue Crack Propagation," ATR-72(9990), The Aerospace Corp., 1971. As pub1ished in Aerospace Structural Metals Handbook, Vo14, Code 3715, CINDAS/USAF CRDA Randbooks Operation, Purdue University, 1995, p 13
768/Titanium (Ti)
Ti.074 Ti-6AI-6V-2Sn aged titanium bar, tensile stress-strain curves for room and elevated temperatures
2oor-------,-------.-------.-------.-----~1400
Treatment: 870 oC (1600 °F), 1 h, water quenched + 565 oC (1050 °F), 4 h. UNS R56620
~----~-------+--~~~~~==~----~1120
Source: Aerospace Structural Metals Handbook, Vol 4, Code 3715, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 25
840
'"
a..
'00
-'"
::2'
ui
ui
'"~
ro
560
'" ~
~--~~r_------r_------r_------+_----~280
L -______L -______L -______L -______L -____
4
~O
10
8
6 Slrain, 0.001 in.lin.
2
200
1400
160
1120
V
120 ui
'" ~
UJ
80
40
Source: MIL-HDBK-5H, Dec 1998, p 5-107 840
ui
560
/
280
4
'"
a..
::2'
1/
V
Specimen tested in longitudinal direction. RambergOsgood parameter: n(longitudinal) = 30. UNS R56620
1-
/
'00
-'"
Ti.075 Ti-6AI-6V-2Sn annealed titanium alloy extrusion, typical tensile stress-strain curve at room temperature
8
12 Slrain, 0.001 in.lin.
16
20
o
24
'"~ ro
Titanium (Ti)/769
200
160
o
----- r--- ~~ J
120 -'"
l'!'"
1i5 80
Test direction: longitudinal. Ramberg-Osgood parameters: n(longitudinal) = 22. UNS R56620
1120
¡...-
Source: MIL-HDBK-5H, Dec 1998, p 5-107
~
840 ro a. ::;;:
~'" (f) 560
1/
/
1/
Ti.076 Ti-6AI-6V-2Sn annealed titanium alloy extrusion, typical compressive stress-strain and compressive tangent modulus curves al room temperature
140
/
"¡¡;
40
Compressive langen! modulus, GPa 112 56 84
28
280
12 16 20 Slrain, 0.001 in.lin. 6 Compressive langen! modulus, 10 psi
4
8
o
24
240
1680
Ti.077 Ti-6AI-6V-2Sn heat treated titanium alloy forging, tensile stress-strain curve at room temperature
200
1400
Porging size: 127 x 152 mm (5 x 6 in.). Treatment: 870 oC (1600 °P), 1 h, water quenched + 593 oC (1100 °P), 4 h. UNS R56620
1120
Source: Aerospace Structural Metals Handbook, Vol 4, Code 3715, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 12
/
160
~ ui 120
'"
l'!
i'i5
80
40
/
1/
/ V
V-
-
/
ro
a.
::;;: 840 ui
~
i'i5 560
280
4
8 12 Slrain, 0.001 in.lin.
16
770/Titanium (Ti)
Ti.078 Ti-7 AI-4Mo titanium alloy forged bar, isochronous tensile stress-strain curves at elevated temperatures
1oor------r------,------r------,------r.~~__.700
Treatment: 982-1010 oC (1800-1850 °P) + 788 oC (1450 °P), 1 h, force cooled to 566 oC (l050 °P), air cooled + 566 oC (1050 °P), 24 h air cooled. UNS R56740
80r-----_r------r_----_r~~~r_----_r----~560
~
60r-----_r------~~r_~_.~~r_----_r----~420
00
ro
~ ID
~'"
oo~
Exposure
~'" BOO
1h
10 h 100 h 250 h 500 h 1000 h
140
O~----~----~------L-----~----~----~O
80r------r------,------r------,------r------.560 /700 °F (371°C)
60~----_r------r_~~_r------r_----_r----__1420
ro
~
~
~
~
40
~----_r--~~i=;"OF,.-¡;~"'---r_--_r----__1280 gf
~
2
4
6
Strain, 0.001 in./in.
8
10
Source: "Tentative Data Sheet for Crucible C-135aMo7AI-4Mo," Crucible Steel Co., Dec 1958. As published in Aerospace Structurai Metals Handbook, Vol 4, Code 3708, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 20
Titanium (Ti)/771
200
1400
160
1120
120
¡f
'00 -" ui (1) ~
1ñ 80
40
v
/
¡...-
Source: MIL-HDBK-5H, Dec 1998, p 5-34 840
400°F (2?4 OC)
¡....-
8'.
::¡;
- 550°F (288 OC)
ui (1)
~ .C/) 560
280
V
4
8
12 16 Strain, 0.001 in./in.
20
o
24
200
1400
160
1120
/~~ 120
b
'00 -" ui (1) ~
1ñ 80
40
)
1
Test direction: longitudinal and long transverse. 0.5 h exposure. Ramberg-Osgood parameters: n(room temperature) = 33, n(400 °P) = 50, n(500 °P) = 50. UNS R54810
Room temperature
VI
)
Ti.079 Ti-8AI-l Mo-l V single-annealed titanium alloy sheet, typical tensile stress-strain curves at room and elevated temperatures
Source: MIL-HDBK-5H, Dec 1998, p 5-36 840
560
280
12 16 Strain, 0.001 in./in.
'"
c.. ::¡;
f..-- 400°F (204 OC) f..-- 550°F (288 OC)
8
Test direction: longitudinal and long transverse. 0.5 h exposure. Ramberg-Osgood parameters: n(room temperature) = 16, n(400 °P) = 32, n(550 °P) = 24. UNS R54810
¡..- Room temperature
1(
4
Ti.080 Ti-8AI-l Mo-l V duplex-annealed titanium alloy sheet, typical tensile stress-strain curves at room and elevated temperatures
20
g
772/Titanium (Ti)
120
Ti.081 Ti-8AI-l Mo-l V mill-annealed titanium alloy sheet, stress-strain curves at elevated temperatures
840 600°F (J16 OC)
Sheet thickness ::;: 1.3 mm (0.050 in.). Treatment: 788 oC (1450 °P), 8 h, force cooled. UNS R54810
~.
100
80
/
40
20
I
///
/
-/'
700
/
.-:
2
560 ro a.. :2
420
vi
tJ)
~ 280
!/
V
Source: "Creep Strength ofTi-8Al-IMo-1Y al 600 and 900 F,"Tilanium Melals Corp., 1962. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3709, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 10
900°F (4l2 OC)
140
4
8
6
10
Strain, 0.001 inJin.
100
.¡¡; -'" vi tJ)
450°F (232 OC)
Ti.082 Ti-8AI-l Mo-l V duplex-annealed titanium alloy sheet, stress-strain curves at elevated temperatures
700
80
560
60
420
Test direction: longitudinal. Sheet thickness ::;: 1.3 mm (0.050 in.). Duplex annea1: 788 oC (1450 °P), 8 h, force cooled + 788 oC (1450 °P), 15 min, air cooled. UNS R548 10 ro :2
a..
vi
tJ)
~
~
(f)
280
40
Strain, 0.001 inJin.
ro
Source: C.W. Alesch, "Onset of Creep Stress Measurement of Metallic Materials," Convair, 1964. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3709, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 10
Titanium (Ti)/773
200
o
160
~
550°F (288
cñ U>
~
iií 80
/
ocy
l---
550°F (288
840
oC)
o
28
g¡' ~
560
280
12 18 20 Slrain, 0.001 in./in. Compressive tangenl modulus, 106 psi
8
Compressive tangent modulus, GPa 84 112 56
~
U>
V-
/
~ V
-'"
cñ
'---
~
80
40
o
24
Ti.084 Ti-8AI-l Mo-l V duplex-annealed titanium alloy sheet, typical compressive stress-strain and compressive tangent modulus curves at room and elevated temperatures
140
Test direction: longitudinal and long transverse. 0.5 h exposure. RT, room temperature. Ramberg-Osgood parameters: n(RT) = 50, n(500 °P) = 22. UNS R54810
1120
120
4
1- RT
-
~
Source: MIL-HDBK-5H, Dec 1998, p 5-36 840
ro ;¡;
a.
~550°F(288°C)
r---
¡)
V
Source: MIL-HDBK-5H, Dec 1998, p 5-34
U)
160
.¡¡;
ro a. ;¡;
r-----,
J 4
Test direction: longitudinal and long transverse. 0.5 h exposure at temperature. RT, room temperature. Ramberg-Osgood parameters: n(RT) = 50, n(550 °P) = 50. UNS R54810
1120 RT
V
l!
Ti.083 Ti-8AI-l Mo-l V single-annealed titanium alloy sheet, typical compressive stress-strain and compressive tangent modulus curves at room and elevated temperatures
140
¡---,.,
---- ji
120
200
Compressive tangent modulus, GPa 56 84 112
~
~
40
28
gi ~
U)
~
560
550°F (288 "C) 280
8
12 16 20 Strain, 0.001 in./in. 6 Compressive tangent mOdulus, 10 psi
774/Titanium (Ti)
120r-------,--------.-------.------~------~
840
Ti.08S Ti-8AI-l Mo-l V mill-annealed titanium alloy sheet, isochronous stress-strain curves at elevated temperatures
700
Test direction: longitudinal. Treated: 788 oC (1450 °F), 8 h, force cooled. UNS R54810
250 h
0.1 h 80~------~~~--~------~~----_+------~
560 ctl
~
11.
Source: "Creep Strength of Ti-8AI-IMo-1 V al 600 and 900 F," Titanium Melals Corp., 1962. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3709, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 18
::¡; ~ 60~----_1+_------~-.~--_+------_+------~ 420
'"~
~
iñ
iñ 100 h 280
Slrain, 0.001 in.lin.
Ti.086 Ti-8Mn titanium alloy, comparison of experimental and calculated stress-strain curves
1000r---------~--------,----------,---------.
140
UNS R56080 800~------~~-----+~--------~--------~
120
Source: H. Margolin et al., Calculations of Stress-Strain Curves and Stress Strain Distribution for an Alpha-Beta Ti-8Mn Alloy, Mater. Sci. Eng., Vol 34, 1978, p 203-211. As published in R. Boyer, G. Welsch, and E. Collings, Ed., Materials Properties Handbook: Titanium Alloys, ASM Intemational, 1994, p 763
100 ctl
600~--------+_~L-~--~--------_+--------~
11.
80
:2
~
'ijj O
'~"
400~------~~--------~--------~------~
60
40 200~--AL----+_--------~--------_t----------
20
0.5
1.0 Slrain, %
1.5
O
2.0
(IJ
Titanium (Ti)/775
1000 I---I----I--::::=~¡::::::::======t
Ti.087 Ti-8Mn titanium alloy, stress-strain curves for a, ~, and a-~ phases
140
UNS R56080 800~--------_+------~~~
__~----_+--------~
120
Source: H. Margolin et aL, Calculations of Stress-Strain Curves and Stress Strain Distribution for an Alpha-Beta Ti-8Mn Alloy, Mater. Sci. Eng., Vol 34, 1978, p 203-21 LAs published in R Boyer, G. Welsch, and E. Collings, Ed., Materials Properties Handbook: TItanium Alloys, ASM International, 1994, p 763
100 ro 600~--------_+~~~"~--+_--------_+--------~
a. :2
80
~
Uí
"¡¡;
""
!!!
400~------~~------,~~~--------_+--------~
60 en
40 200~~'-----~--------_+----------~------~
20
L-----~-------~------
0.5
1.0
__ 1.5
_ L_ _ _ _ _ _~O
2.0
Strain, %
Ti.088 Ti-8Mn annealed titanium alloy sheet, tensile stress-strain curves at various temperatures
280r-------~------·,-------_,------_r------_,1960
-425 'F (-254 'C)
Sheet thickness = 1.63 and 1.78 mm (0.064 and 0.070 in.). 0.5-100 h exposure. UNS R56080
240~------~-------+--------~----~~------~1680
- - - 0.064 in. (1.626 mm) sheet - - 0.070 in. (1.778 mm) sheet" 200~------~-------+------"~------~------~1400
.¡¡;
160
f--------+--------+----:¡~,K::---+__-----'--_t_----'-----_I1120
8:.
""
:2
E en 120
~
~
~
840 Uí
40r---~~~------·_+_------~------+------~280
o o~------L-------·..L---------L--------L-------.J O 4 8 12 16 20 Strain, 0.001 in.lin.
Source: RL. McGee, J.E. Campbell, RL. Carlson, and G.K. Manning, "The Mechanical Properties of Certain Aircraft Structural Metals at Very Low Temperatures," WADC TR 58-386, 1958. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3712, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 3
776/Titanium (Ti)
14or---------~--------_.--------_.--------_.980
Room temperature 120~--------+---------~~------~--------~840
100~--------+-----~---r--------~--------~700
40~----~~~---------r--------~--------~280
1000 °F (538 OC)
20~,I,~----~~~-----r~--~--~--------~140
°0~--------~4----------8L---------~12--------~1;
Strain.O.001 inJin.
Ti.089 Ti-8Mn annealed titanium alloy sheet, compressive stress-strain curves at room and elevated temperatures
Sheet thickness = 1.78 mm (0.070 in.). 0.5-100 h exposure. UNS R56080 Source: D.E. MilIer, "The Detennination of Physical Properties of Ferrous and Non-Ferrous Structura1 Sheet Materia1s at E1evated Temperatures," AF Technica1 Report 6517, Part 3, Wright Air Dev. Cen., June 1954. As published in Aerospace Structural Metals Handbook, Vo14, Code 3712, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 4
Titanium (Ti)/777
250
Ir~
Ti.090 Ti-10V-2Fe-3AI titanium alloy, true stressstrain curves for ~ and a + ~ processed material
~
200
,
ro
~ 150
i
10/s
-
~ ~
~ 100
......
"
--
.....
A)
..rrJ..
¡!:
." ....
Tested at 790 oC (1455 °F) at various strain rates for (a) structure and (b) a + ~ structure
30
Source: G.W. Kuhlman et. al., Sixth World Conference on Titanium, P. Lacombe, R. Tricot, and G. Beranger, Ed., Les Editions de Physique, Paris, 1989, p 1269-1275. As published in R. Boyer,G. Welsch, and E. Collings, Ed., Materials Properties Handbook: Titanium Alloys, ASM Intemational, 1994, p 860
1.0/s
JT"
-
~
0.10/s -
10
50
o
o
(a)
250
~
200
10/s
~
rñ In
-
30
-
~ 20 gf
~
--
ro
~ 150
.....
..-
.... ¡-.-
1.0/s
~al
~
~ 100
()
¡!:
~
~
~
~
o.1O/s~ -
10
50
o
0.15
O (b)
0.30
0.45 True strain, in.lin.
0.60
0.75
~
o
0.90
778/Titanium (Ti)
Ti.091 Ti-10V-2Fe-3AI titanium alloy, true longitudinal tensile stress-strain curves, effect of ex fradion on unaged material
1000 A
í~
V
800
11 &.
:;¡;
600
I!/
~
iñ
200
V
JI
ID
~ 400
v
r -f
~
'/
/
/
17
./
/
V
V
--"'"
140
-
120
:..:::::
V I
- 100 'iii
- 80
"'
~
iñ
- 60
ID
:;,
~
- 40
I
- 20
2
3
4
5 6 True strain. %
7
9
8
Source: T.W. Duerig, G.T. Terlinde, and J.C. Williarns, Phase Transfonnations and Tensile Properties ofTi-l0V-2Fe-3Al, Metal/. Trans. A, Vol11, Dec 1980, p 1987. As published in R. Boyer, G. Welsch, and E. Collings, Ed., Materials Properties Handbook: Titaniurn Alloys, ASM International, 1994, p 859
o
10
Ti.092 Ti-10V-2Fe-3AI solution treated and overaged titanium alloy bar, tensile stress-strain curves at room and elevated temperatures
1200,----,-----,-----,-----,----,-----,-----, 160 1000~--~-----+-----+----~----~----+-----4
Test direction: longitudinal. Round bar. Maximum 0, 0.16 wt%; maximum N, 0.05 wt%
140 120 100
'"
a..
:;¡;
'iii
"'
600
(fJ
80
~
60
400
40 20
12 Strain. 0.001 mm/mm
O
14
UTS, ultimate tensile strength; TYS, tensile yield strength. Curve A: ex, 30 vol%; UTS, 875 MPa; TYS, 831 MPa. Curve B: ex, 10 vol%; UTS, 877 MPa; TYS, 467 MPa. Curve C: ex, O vol%; UTS, 878 MPa; TYS, 262 MPa. Increasing the amount of ex increases the yield strength but does not affect the ultimate tensile strength. The ~ transus was 805 ± 3 oC (1480 °P), somewhat high compared to other heats. This is probably due to oxygen content (0.15 wt%), which is on high side of normal range. Treatments aboye 600 oC (1110 °P) done by vacuum encapsulating specimens wrapped in tantalum foil. Below 600 oC treatments were performed in a liquid nitrate salt bath. Strain rate = 0.00055/s
~
1ií
Source: O.L. Deel, "Engineering Data on New Aerospace Structural Materials," AFML-TR-77-198, Batelle-Columbus Laboratories, 1977, p 97. As published in R. Boyer, G. Welsch, and E. Collings, Ed., Materials Properties Handbook: Titaniurn Alloys, ASM International, 1994, p 859
Titanium (Ti)/779
16
---
RJom templature
14
!/
12
1-
10 ·00 -'" ui
'" ~
lI:~V
6
2
j
V
800 °F
(~27 OC)
70 ro
a..
::;;;
56
ui
'" ~
Source: O.L. Deel, "Engineering Data on New Aerospace Structural Materials," AFML-TR-77-198, Batelle-Columbus Laboratories, 1977. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3726, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 44
42
28
~ 2
Test direction: longitudinal. Bar diameter = 76 mm (3 in.). Heat treated: 760 oC (1400 °P), 1 h, force cooled + 566 oC (1050 °P), 8 h, air cooled
84
/V
4
98
40~r40C)
~
h V ....-
8
Ti.093 Ti-l0V-2Fe-3AI heat treated titanium alloy bar, typical tensile stress-strain curves at room and elevated temperatures
112
14
4
6
8
10
12
o
14
Strain, 0.001 in./in.
Ti.094 Ti-l0V-2Fe-3AI solution treated and overaged titanium alloy bar, compressive stress-strain curves at room and elevated temperatures
1200 160 1000
ro
100
a..
::;;;
'"
Source: O.L. Deel, "Engineering Data on New Aerospace Structural Materials," AFML-TR-77-198, Batelle-Columbus Laboratories, 1977, p 98. As published in R. Boyer, G. Welsch, and E. Collings, Ed., Materials Properties Handbook: Titanium Alloys, ASM Intemational, 1994, p 859
120
800
ui
Test direction: longitudinal. Round bar
140
Room temperature
·00 -'"
600
ui
80 '" e!
~
ro
60
400
40 200 20
12 Strain, 0.001 mm/mm
O
14
780/Titanium (Ti)
16
-
Room telperature
14
V
12
~~
h~
.¡¡;
8
6
~
4
2
1---
400 °F,(204 ~
10
'"vi '" ~
Ti.095 Ti-l0V-2Fe-3AI heat treated titanium alloy bar, typical compressive stress-strain curves at room and elevated temperatures
112
)
/
~
Test direction: longitudinal. Bar diameter = 76 mm (3 in.). Heat treated: 760 oC (1400 °P), 1 h, force cooled + 566 oC (1050 °P), 8 h, air cooled
84
70 ro
c..
800°F 1(427 oC)
:;;
~
56
V--
vi
~'" (f)
Source: O.L. Deel, "Engíneering Data on New Aerospace Structural Materials," AFML-TR-77-198, Batelle-Columbus Laboratories, 1977. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3726, CINDAS/USAF CRDA Handbooks Operatíon, Purdue University, 1995,p46
42
Y
28
~ 2
98
14
6
4
8
10
12
o
14
Straín, 0.001 ínJín.
Ti.096 Ti-l0V-2Fe-3AI solution treated and aged titanium alloy die forging, typical tensile stressstrain, compressive stress-strain, and compressive tangent modulus curves
Compressive tangent modulus, GPa
5~6------8~4----~11-2-----1~4-0----_,16~400
r -____,28 ______
160 f----+----+----'~':#1__--__1_--__+--__i 1120
.¡¡;
840
120
ro
c..
:;;
'"vi '" ~
vi
'"~
560
80
40~~?-4----+---r---1+---+----~280
L-----~4------~8------1L2----~16L-----~----~2~
Strain, 0.001 inJin. 6 Compressive tangent modulus, 10 psí
1ií
Test directions: longitudinal (L), long transverse (LT), and short transverse (ST). Thickness = 78.74-83.82 mm (3.100-3.300 in.). Die forging aged 482-510 oC (900-950 °P). Ramberg-Osgood parameters: n(L, tension) = 9.6, n(LT, tension) = 13, n(ST, tension) = 13, n(L, compression) = 18, n(LT, compression) = 15, n(ST, compression) = 18 Source: MIL-HDBK-5H, Dec 1998, p 5-137
Titanium (Ti)/781
Ti.097 Ti-l0V-2Fe-3AI solution treated and aged titanium alloy hand forging, typical tensile stressstrain, compressive stress-strain, and compressive tangent modulus curves
Compressive tangent modulus, GPa
200 O;_ _---=2;::8_ _-.:5;:6~_
____=r84:...--~11.::.2---'-14rO--__i16~400
Test directions: longitudinal (L), long transverse (LT), and short transverse (ST). Hand forging aged 510-538 oC (950-1000 °F). Ramberg-Osgood parameters: n(L, tension) = 24, n(LT, tension) = 20, n(L, compression) 21
160 1-----+""_=-+---.,,-L-b--==.!~='--_+_--_I1120
=
840
120
Source: MIL-HDBK-5H, Dec 1998, p 5-137
'"
o..
'iñ
""
::E
Ul
Ul
~ 560
401--~~+---+---4---4+---+---_I280
L---~4--~8----~12----1~6---2~0--~21 Strain, 0.001 in.lin. Compressive tangent modulus, 106 psi
Ti.098 Ti-l0V-2Fe-3AI titanium alloy, strength ductility trend curve showing effect of varying amounts of primary a
1500,-----r-----,--------y-------r---210
200 ro
g¡ 1300 1---"-1r-----~'-r---_Ip.,.--__t---_+---- 190 ] ~Q)-
~
]l -
,¡go
180 o
~
~
N ~ 1200
N ~
z¡
170
~
~
g¡
~
~
~
>= 1100
160
150 1000~--~-----1---_+---_+--~V~-4 L -_ _
o
~~
0.2
____
~
____
0.4
~
____
0.6
True fracture strain
~
______
0.8
~
140
1.0
~
>=
Data on yield strength versus tensile fracture strain can be plotted for each of several primary a volume fractions, as shown in this figure. These data show that the alloy in the most ductile condition at any of the strength levels studied is that which contains a small (-0.1) volume fraction of primary a. This condition represents a compromise in the sense that alloys containing no primary a unavoidably have grain-boundary a, whereas at higher volume fractions of primary a, strain localization tends to occur between the primary a partic1es. Both grain-boundary a and strain localization lead to premature fracture initiation, and thus the alloy that does not exhibit either of these conditions has better ductility. Source: G. Krauss, Ed., Deformatíon, Processíng, and Structure, ASM Materia1s Science Seminar, 1982, American Society for Meta1s, 1984, p 323
782/Titanium (Ti)
300
°-
J
Below
Above
f3 transus f3 transus
-
J.
250
8:::;;;
Ti.099 Ti-l0V-2Fe-3AI titanium alloy, effect of microstructure on flow stress
-
I
V_
°1 ¡e (/
f3 .1-
IJ)
[l!
/0
tí ;: ~ 150
..
~
/rX.
~-
j
~
100 cf
CJ
50 12
14
16
18
Ln Z is the temperature-compensated strain rate as defined by C.D. Zener and J.R. Rollaman, J Appl. Phys., Vol 15, 1944, p 22-32
-
I
200
40
~
30
~
V' et+f3
:i[l!
Source: G.W. Kuhlman et al., Sixth World Conference on Titanium, P. Lacombe, R. Tricot, and G. Beranger, Ed., Les Editions de Physique, Paris, 1989, p 1269-1275. As published in R. Boyer, G. Welsch, and E. Collings, Ed., Materials Properties Handbook: Titanium Alloys, ASM Intemational, 1994, p 860
tí ;: o
u:: -
20
-
10
V
20
22
28
26
24
Ln Z
Ti.l00 Ti-l0V-2Fe-3AI titanium alloy, flow stress versus strain
250
Effect of strain rate at 815 30
-
200
1O/s
~
8:::;;;
---.....,
150 -
IJ)
~
u::~
100 0.1/s -
10
50
.
0.001/s
10
20
30 Strain, %
40
50
o
60
oc (1500 °P)
Source: R. Boyer, G. Welsch, and E. Collings, Ed., Materials Properties Handbook: Titanium Alloys, ASM Intemational, 1994, p 860
Titanium (Ti)/783
Ti. 1 01 Ti-1 OV-2Fe-3AI titanium alloy, flow stress
400r------,------,------,------,------,------,
versus strain
Effect of forging temperature at lO/s strain rate 50
Source: R. Boyer, G. We1sch, and E. Collings, Ed., Materials Properties Handbook: Titanium Alloys, ASM International, 1994, p 860
300
'" :2
40 ~
'"
~
Q.
'" (fJ
(fJ
~
1ñ
~
;: o
¡¡:
lL
30
200
20
10
20
30
50
40
60
Strain, %
-
16o
J...--
14
~
O(
12O
Ti.102 Ti-11 Sn-5Zr-2.25AI-1 Mo-0.21 Si titanium alloy forging, large ring, tensile stress-strain curve at room temperature
1120
~ 840
Heat treated in full section: 900 oC (1650 °F), 1 h, fan cooled + 500 oC (930°F), 24 h, air cooled
10O
'"
Q.
:2 O
560 '"
~
1ií 6O
4O
280
2o-
O
O
0.02
0.04
0.06
0.08 Slrain, in./in.
0.10
0.12
0.14
O
0.16
Source: R.E Simenz and W.L. Macoritto, "Eva1uation of Large Ti-6A14V and IMI-679 Forging," Technica1 Report AFML-TR-66-57, Lockheed-Ca1ifornia Co., 1966. As pub1ished in Aerospace Structural Metals Handbook, Vo14, Code 3711, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 21
784/Titanium (Ti)
200
1400
160
1120
120
~ !Ji !I)
~
1i.í 80
40
/
V
v
iV
v---
~
Room temperature
560
4
12 8 Strain, 0.001 in./in.
o
20
16
,.---
/
k:::::+--
~~
'w
120
5
Test direction: longitudinal. Sheet thickness = 1.6 mm (0.063 in.). Solution treated + 510 oC (950°F), 8 h, air cooled. UNS R58030
1120
Source: O.L. Deel and H. Mindlin, "Engineering Data on New and Emerging Structural Materials;' AFML-TR-70-252, BateIle-Columbus Laboratories, Oct 1970. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3722, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 33
'"
o.. :2
850 °F (454 OC)
840 !Ji !I)
~ 560
)V
V
1400
600 °F (316 OC)
I~
1i.í
40
Room temperature
400 °F (Jo4 OC) ~
80
Ti.l04 Ti-ll.5Mo-6Zr-4.5Sn titanium alloy sheet, typical tensile stress-strain curves at room and elevated temperatures
1680
160
~
X
Source: R.E Simenz and W.L. Macoritto, "Evaluation of Large Ti-6AI4V and IMI-679 Forging," Technical Report, AFML-TR-66-57, Lockheed-California Co., 1966. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3711, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 28
280
200
!I)
'"
o.. :2
550°F(288°C)
240
"'!Ji"
Specimen size: 15.88 mm (0.625 in.) diam; 44.45 mm (1.750 in.) long. Heat treated in full section: 900 oC (1650 °F), 1 h, fan cooled + 500 oC (930°F), 24 h, air cooled
840 ~
Ti.l03 Ti-l1 Sn-5Zr-2.25AI-l Mo-0.21 Si titanium alloy forging, large ring, compressive stress-strain curves at room temperature and 288 oC (550 °F)
280
10
20 15 Strain, 0.001 in./in.
25
30
Titanium (Ti)/785
Ti.l05 Ti-ll.5Mo-6Zr-4.5Sn titanium alloy sheet, typical tensile stress-strain curves at room and elevated temperatures
240 .----'----,---,----,----,-------r--,----, 1680
Room temperature
200
1400
Test direction: transverse. Sheet thickness = 1.6 mm (0.063 in.). Solution treated + 510 oC (950 °P), 8 h, air cooled. UNS R58030
400°F ( 04 OC)
160
~~~+~~-.~~~~==~~::::+;;;~¡;;;~1120 600°F (316 OC) 850 'F (454 'C)
'iii -"
vi
CI)
1!!
ti:!
a.
:::E
120
vi
~~~1--~~~~--~~~~~~~~~+-~~840
~
é'ñ
Source: O.L Deel and H. Mindlin, "Engineering Data on New and Emerging Structural Materials," AFML-TR-70-252, Batelle-Columbus Laboratories, Oct 1970. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3722, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 33
80 ~~~~~~+-~--+-~~+-~~+-~~+-~~560
40
~-M~i--~~+-~--+-~~+-~~+-~~+-~~280
5
10
15
20
25
30
Strain, 0.001 inJin.
240
Ti. 106 Ti-l1.5Mo-6Zr-4.5Sn titanium alloy sheet, typical compressive stress-strain curves
1680 Tiansverse
/ ..... ~9itudinal
Jír
200
160
1120
11
'iii -"
vi
CI)
~
120
40
ti:!
a.
:::E 840 CI) vi
V
é'ñ 80
Sheet thickness = 1.6 mm (0.063 in.). Solution treated + 510 oC (950 °P), 8 h, air cooled. UNS R58030
1400
+-
~ 560
I
V
5
280
10
15
20
Strain, 0.001 inJin.
25
30
Source: O.L Deel and H. Mindlin, "Engineering Data on New and Emerging Structural Materials," AFML-TR-70-252, Batelle-Columbus Laboratories, Oct 1970. As published in Aerospace Structural M etals Handbook, Vol 4, Code 3722, CINDASIUSAF CRDA Handbooks Operation, Purdue University, 1995, p 30
786/Titanium (Ti)
240
1680
Ti.l07 Ti-ll.5Mo-6Zr-4.5Sn titanium alloy sheet, typical compressive stress-strain curves at room and elevated temperatures
1400
Test direction: longitudinal. Sheet thickness = 1.6 mm (0.063 in.). Solution treated + 510 oC (950 °P), 8 h, air cooled. UNS R58030
1120
Source: O.L. Deel and H. Mindlin, "Engineering Data on New and Emerging Structural Materials," AFML-TR-70-252, Batelle-Columbus Laboratories, Oct 1970. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3722, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 35
RLm tempJature
200
~
160
/;V-
.¡¡;
""ui
m ~
120
40
(~04 OC)
600°F (316 OC) 850°F (454 OC)
~
rf. :2
840 ui
VI
ii5
80
I
400 °F
)
V
~
560
280
10
5
15
20
25
30
Strain, 0.001 in.lin.
240
/'
200
~ lA ~
160
/¡
.¡¡;
""uim ~
120
80
40
1680
Ti.l08 Ti-ll.5Mo-6Zr-4.5Sn titanium alloy sheet, typical compressive stress-strain curves at room and elevated temperatures
1400
Test direction: transverse. Sheet thickness = 1.6 mm (0.063 in.). Solution treated + 510 oC (950 °P), 8 h, air cooled. UNS R58030
1120
Source: O.L. Deel and H. Mindlin, "Engineering Data on New and Emerging Structural Materials," AFML-TR-70-252, Batelle-Columbus Laboratories, Oct 1970. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3722, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 35
Room temperature
I
O
400°F (J04 oC) ~
600°F (316 OC) 850°F (454 OC)
~
V
rf.
:2
840 ui
,~
V
o
,..---
~
560
280
5
10
15
20
Strain, 0.001 in.lin.
25
30
Titanium (Ti)/787
Ti.l09 Ti-13V-ll Cr-3AI titanium alloy, tensile stressstrain curves at very high temperatures
4 r---------.---------,----------r---------, 28
UNS R58010 Source: P.E. Moorhead, "Tensile and Creep Properties of Columbium, Tantalum and Titanium Alloys at Elevated Temperatures," Bell Laboratory Report BLR-62-26M, Dec 1962. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3712, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 11
3~-------7~--------+_--------~--------~21
2050 'F (1121 'C)
~
~---------¡
~
gf 2 I-----J'---------t.-~------_t_--------+------------j 14 gf ~ ~ w 00 2300 'F (1260 'C)
°OL--------~2--------~4~--------6~------~80
Strain, 0.001 in.lin.
150 ,------r-----,------,------,------,------1050
Ti.ll0 Ti-13V-ll Cr-3AI annealed titanium alloy sheet, typical tensile stress-strain curves at room and elevated temperatures
125
Test direction: longitudinal and long transverse. 0.5 h exposure. Ramberg-Osgood parameters: n(room temperature) = 43, n(200 °P) = 30, n(400 °P) = 17, n(600 °P) = 12, n(800 °P) = 11, n(lOOO °P) = 10. UNS R58010
100 ~
.¡¡;
75
r------,.M+-r-+------+-----+-----1----~525
~
00 1----~~----_+------+_----+----_4----~350
251--~--~----_+------+_----+----_4----~175
L -_ _ _....l-_ _ _ _
4
_ _ _ _ _ _:':__ _ _ __'__ _ _ __ _ l_ _ _ _
8
12 16 Strain, 0.001 in.lin.
20
~
(J)
¡
::;;
~
"'
O
24
Source: MIL-HDBK-5H, Dec 1998, p 5-118
788/Titanium (Ti)
Ti.lll Ti-13V-ll Cr-3AI solution treated and aged titanium alloy sheet, typical tensile stress-strain curves at room and elevated temperatures
200
1400
160
1120
120
840 ro o..
'iij
-'"
Test direction: longitudinal and long transverse. 0.5 h exposure. Ramberg-Osgood parameters: n(room temperature) = 23, n(200 °P) = 17, n(400 °P) = 16, n(600 °P) = 15, n(800 °P) = 11, n(lOOO °P) = 10. UNS R58010 Source: MIL-HDBK-5H, Dec 1998, p 5-125
::;¡;
U)
~
'" ~
1000 °F (538 OC)
éií
560
80
en
40~--~Y------+------~----4------+----~280
ooL-----~4------~8------1L2----~16------2~0----~2;
Slrain, 0.001 in.lin.
Ti.112 Ti-13V-ll Cr-3AI solution treated titanium alloy sheet, tensile stress-strain curves at room and various temperatures
200 ,..---------,..---------,----------,-----------, 1400 -65 °F (-54 OC)
Sheet thickness ~--------~--------~------~~------~1120
840 ro o..
~
::;¡;
U)
U)
~
~
560
~----~~~~------~--------~------~280
~--------L---------L---------L-------~1~
Slrain, 0.001 in.lin.
éií
= 1 mm (0.040 in.). UNS R58010
Source: "Data Sheet B 120 VCA," Titanium Alloys Issue 2, TDS-20075M, Crucible Steel Co. of America, Dec 1960. As published in Aerospace Structural Metals Handbook, Vo14, Code 3712, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 11
Titanium (Ti)/789
,------,------,------,-------,------,14oo
200
160~-----~------+_---
__~~~
Ti.113 Ti-13V-ll Cr-3AI solution treated and aged titanium alloy sheet, tensile stress-strain curves at room and elevated temperatures
+_-----11120
Test direction: longitudinal (a) and transverse (b), Sheet thickness = 3.18 mm (0.125 in.). UNS R58010 Source: P.J. Hughes, "Determination of Design Data for Heat Treated Titanium Alloy Sheet," Vol 1, ASD-TR-62-335, May 1962. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3712, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 11
40~--~~------+_-----~-------r------+_----_1280
OL------L----~------~----~------~----~O
(a)
200,------T------,------,-------,------,------,1400
---+------1 1120
r------+-----t~~~_1------_r------+_----_4840 ro
o-
:2 ui
r------+,Q.r#~4_----~------_r------+_----~560
r---~~------+_----_1------_r------+_----_4280
~-----4~----~8------J12~----~1-6------2LO----~240
(b)
Strain, 0,001 inJin,
'"~
00
790/Titanium (Ti)
Ti.114 Ti-13V-ll Cr-3AI solution treated and aged titanium alloy sheet, tensile stress-strain curves at room and low temperatures
320,-------,-------,-------,-------,-------,2240
V>
~
ro
-65 'F (-54 'C)
·00
"'vi"
Test direction: longitudinal (a) and transverse (b). Sheet thickness = 1.6 mm (0.063 in.). UNS R58010
1680
240
I
160
Room temperature
o..
::2:
1120
éñ
li ~
éñ
560
80
o~------L-------L-------~------~------~O
(a)
320.-------,-------,-------,-------,-------,2240
1680
240 -65 'F (-54 'C) ·00
"'vi" V>
~
ro
o..
I
Room temperature
160
::2:
1120
560
80
°0~------4L-------L8-------1~2------~16------~2~ (b)
Strain. 0.001 in.lin.
li
~
Source: W.M. McGee and R.B. Mathews, "Determination of Design Data for Heat Treated Titanium Alloy Sheet," Vol2a, ASD-TR-62-335, May 1962. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3712, CINDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 12
Titanium (Ti)/791
20or-----~-----,------r_----_r----_,----__.
1400
1400
200 Room temperature
Room temperature
I
I
lo 200 F (93 OC) 400°F (204 OC) 600:F (316 OC) 800°F (427 OC) 900 °F (482 OC)
160~----~-----+--7S~~~
1120
840 c.. '"
:;;:
1/'IIIi!!
560 Cií
40~--~A_-----+-------~----4_----_+----~
200°F (93 OC) 400 °F (204 OC) 600°F (316 OC) 800 °F (427 OC) 900°F (482 OC)
160
._120
g¡
840 c.. '"
ui
1Il"
:;;:
III
i
280
III
80
i!! 560 Cií
40
280
O
4 (a)
8
12
16
20
4
24
8
(b)
Strain, 0.001 in.lin.
1400
200
1120
12
16
20
O
24
Strain, 0.001 in.lin.
1400
200
R90m temper~ture
200°F (93 OC) 400 °F (204 OC) 600°F (316 OC) 800 °F (427 oC 900°F (482 OC)
160
1120
._120
1120
840 c.. '" :;;:
III
-" uf
840 c.. '" :;;:
ui
III
ui
III
ui
Cií
~
Cií
i!! 560 Cií
III
i!!
80
560 en
40
280
III
i!!
280
L-----~----~-------~----~----~----~O
4
(e)
8
12 Strain, 0.001 in.lin.
16
20
8
24 (d)
12
16
20
O
24
Strain, 0.001 in.lin.
Ti.115 Ti-13V-ll Cr-3AI solution treated and aged titanium alloy sheet, typical compressive stress-strain curves at room and elevated temperatures (a) Sheet thickness = 1.6 mm (0.063 in.); test direction: longitudinal. (b) Sheet thickness = 1.6 mm (0.063 in.); test direetion: transverse. (e) Sheet thiekness = 3.18 mm (0.125 in.); test direetion: longitudinal. (d) Sheet thickness = 3.18 mm (0.125 in.); test direetion: transverse. UNS R58010 Source: P.J. Hughes, "Determination of Design Data for Heat Treated Titanium Alloy Sheet," Vol l, ASD-TR-62-335, 1962. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3712, ClNDAS/USAF CRDA Handbooks Operation, Purdue University, 1995, p 14
792/Titanium (Ti)
I -423 "F 320
Ti.116 Ti-13V-11 Cr-3AI solution treated titanium alloy bar, tensile stress-strain curves at room and low temperatures
2800
400
,1",
"C)
UNS R58010 Bar diameter = 19 mm (Y. in.)
2240
I
-
240
-320 'F (-196 'C) 1680 ro
~
--
ui
rn
i
160
Il.
::¡;
...
80
0.16
0.08
~
r-... -10 'F (-23 'C)
Room temperature
Source: ER Schwartzberg, S.H. Osgood, RD. Keys, and T,E Kiefer, "Cryogenic Materials Data Handbook," Progress Report No. 1, ML-TDR-64-280, SuppL, 1965. As published in Aerospace Structural Metals Handbook, Vol 4, Code 3712, CINDASfUSAF CRDA Handbooks Operation, Purdue University, 1995, p 12
1120
""
ro
560
o
0.32
0.24
Strain, in./in.
200
1400
160
1120
.¡¡;
V
120
~
ro
80
40
Source: MIL-HDBK-5H, Dec 1998, p 5-132 840
::¡;
560
/
280
4
ro
Il.
1/
V
Test direction: longitudinaL Aged at 538 oC (1000 OP). Ramberg-Osgood parameter: n(longitudinal) = 30
1-
/
""uirn
Ti.117 Ti-15V-3Cr-3Sn-3AI solution treated and aged titanium sheet, typical tensile stress-strain curve at room temperature
8
12 Strain, 0.001 in./in.
16
20
o
24
N
Titanium (Ti)/793
200
160
o
28
Compressive tangent modulus, GPa 56 84 112
'--1---
k
J
120 'iñ
"'ul" '"
~
80
40
/
/
Ti.118 Ti-15V-3Cr-3Sn-3AI solution treated and aged titanium alloy sheet, typical compressive stress-strain and compressive tangent modulus curves
140
Aged at 538 oc (1000 °F). Ramberg-Osgood parameter: n(longitudinal) = 26
1120
~
Source: MIL-HDBK-5H, Dec 1998, p 5-132
~
840
/
'"
a.
~
ul
'"
560
/
~
280
4
8
12 16 20 Strain, 0.001 in.lin. Compressive tangent mOdulus, 106 psi
o
24
1200~------.----·----~-------~------~
Ti.119 Ti-15V-3Cr-3Sn-3AI solution treated and aged titanium alloy sheet, typical tensile stress-strain curves
160 140
Test direction: longitudinal and long transverse. Sheet thickness = 0.5-1.9 mm (0.020-0.076 in.)
120
Source: MIL-HDBK-5, 1991. As published in R. Boyer, G. Welsch, and E. Collings, Ed., Materials Properties Handbook: TztaniumAlloys, ASM International, 1994, p 913
f------+---.--h4--.::........--+__------j 100
~ ul
80
~----~~-----+-----+__----~60
40
20
4
8 Strain, 0.001 mm/mm
12
~ iií
794/Titanium (Ti)
900 -
800
I~
700 Long
-
'"~
ii5 400
~
300
V
/
'"
~
-
60
-
40
ii5
b?'
~
2
.¡¡;
/
200
80
Source: MIL-HDBK-5. 1991. As pub1ished in R. Boyer, G. We1sch, and E. Collings, Ed., Materials Properties Handbook: Titanium Alloys, ASM Intemational, 1994, p 913 -'<
#
100
100
~ngitudinal
'" ::;¡; 500 o..
Test direction: longitudinal and long transverse. Sheet thickness =0.53-3.17 mm (0.021-0.125 in.)
L---
transverse~V
600
Ti.120 Ti-15V-3Cr-3Sn-3AI solution treated titanium alloy sheet, typical tensile stress-strain curves
120
- 20
4
6
8
10
Strain, 0.001 mm/mm
o 1200
30
Compressive tangent modulus, GPa 60 90 120
Ti.121 Ti-15V-3Cr-3Sn-3AI aged titanium aJloy sheet, typical compressive stress-strain and compressive tangent modulus curves
150 160
1000
Test direction: longitudinal and long transverse. Sheet thickness =0.5-1.9 mm (0.020-0.076 in.). Aged at 540 oC (1000 °P)
140
Source: MIL-HDBK-5E, 1988. As pub1ished in R. Boyer, G. We1sch, and E. Collings, Ed., Materials Properties Handbook: Titanium Alloys, ASM Intemationa1, 1994, p 913
120
800
100.¡¡;
'"
o..
::;¡;
-'<
'" ~ (f)
80
60
400
40
20
4
8
16 12 Strain. 0.001 mm/mm
20
O
24
~ ii5
Titanium (Ti)/795
1400
o
4
2 1
1
Compressive tangent modulus, 10' psi 6 8 10 12 14 11
1
1
1
1
Ti.122 Ti-15V-3Cr-3Sn-3AI solution treated and aged titanium alloy, typical compressive tangent modulus curves for room and elevated temperatures
16
I
1
- 200
Test direction: transverse
' - Room temperature 1200 205 oC.........
ro
1000
Il..
425°C
::;;
r--1---r-__ 1---~ 1---
1---
'"
~ 1;)
800
---
'\
1\
\
............
> '00
'c.~"
~
.............
al
600
-
Source: Collected Engineering Data Sheets, AFML-TR-78-179, 1978. As published in R. Boyer, G. Welsch, and E. Collings, Ed., Materials Properties Handbook: TitaniumAlloys, ASM International, 1994, p 913
150
~
i al
-
100 .~
'"c.~ E
E
o
o
ü
Ü
400
-
50
200
20
1200
O
3
40 60 80 Compressive tangent modulus, GPa
6
Strain, 0.001 in.lin. 12 15
9
18
100
21
o
120
Ti.123 Ti-16V-2.5AI solution treated and aged titanium alloy sheet, typical tensile stress-strain curves for various temperatures
24
27 oC (80°F)
I
160
I
93 °C (200 1°F) 1 20 oc (400 °F)
1000
1
140
120
ro
100
Il..
::;;
'" 2!
80
1ií
60
400
40 200 20
00
'00
-'"
3
6
!l 12 15 Strain, 0.001 mm/mm
18
21
O 24
= 1.6 mm
Source: "Determination of Design Data for Heat Treated Titanium Alloy Sheet," Report No. ASD-TDR-62-335, Vol 1, Lockheed-Georgia, Dec 1962. As published in R. Boyer, G. Welsch, and E. Collings, Ed., Materials Properties Handbook: TItanium Alloys, ASM International, 1994, P 1007
1
3)6 oC (6qO °F) 427 oC (800°F)
800
Test direction: longitudinal. Sheet thickness (0.063 in.)
'"
~
1ií
796/Titanium (Ti)
1200
o
3
6
21
Ti.124 Ti-16V-2.5AI solution treated and aged titanium alloy sheet, typical tensile stress-strain curves for various temperatures
24 160
1000
Test direction: transverse. Sheet thickness = 1.6 mm (0.063 in.)
140
Source: "Determination of Design Data for Reat Treated Titanium Ailoy Sheet," Report No. ASD-TDR-62-335, Vol 1, Lockheed-Georgia, Dec 1962. As published in R. Boyer, G. Welsch, and E. Collings, Ed., Materials Properties Handbook: Titanium Alloys, ASM International, 1994, P 1007
120
800 ro
100
Q..
2
'00
""
'~"
80
U5
'"
~
U5
60
400 538 oC (1000 °F)
40
200 20
00
3
6
3
6
12 15 Strain. 0.001 mm/mm 9
18
21
O 24
18
21
24
Ti.125 Ti-16V-2.5AI solution treated and aged titanium alloy sheet, typical compressive stress-strain curves for various temperatures
Strain, 0.001 in./in.
9
12
15
160
100
400~--~~~~---+----+----4~~~----r---=,60 40 200~~~~--+----+----+---~-----r----r---~
20
Strain, 0.001 mm/mm
Test direction: longitudinal. Sheet thickness (0.063 in.)
= 1.6 mm
Source: "Determination of Design Data for Reat Treated Titanium Alloy Sheet," Report No. ASD-TDR-62-335, Vol 1, Lockheed-Georgia, Dec 1962. As published in R. Boyer, G. Welsch, and E. Collings, Ed., Materials Properties Handbook: Titanium Alloys, ASM International, 1994, p 1006 ~
Titanium (Ti)/797
O
3
6
Strain, 0.001 in./in. 9 12 15
18
21
24
14oor----~----~---,-------.----.----.----,----.200
Test direction: transverse_ Sheet thickness = 1.6 mm (0.063 in.)
1200~--~----+----+----~~--~·--~----+---~
1000~---+----+---~7-~~~~
~------¡
150
~ 800~---+----+--I~~~~----~---+----+---~
:2
'"
~ 600~---+--~AU~~7~~~----~---+----+---~ 400~---+-~~4---~----~-=~5=3~8=OC~(1~00~0~O=F~)-+--~
50
3
6
9 12 15 Strain, 0.001 mm/mm
18
21
Ti.126 Ti-16V-2.5AI solution treated and aged titanium alloy sheet, typical transverse compressive stress-strain curves for various temperatures
Source: "Determination of Design Data for Heat Treated Titanium AlIoy Sheet," Report No. ASD-TDR-62-335, Vol 1, Lockheed-Georgia, Dec 1962. As published in R. Boyer, G. Welsch, and E. Collings, Ed., Materials Properties Handbook: Titanium Alloys, ASM Intemational, 1994, p 1006
Pure Metals and Miscellaneous Alloys (MA)/799
Pure Metals and Miscellaneous Alloys (MA) MA.OO1 Lead and lead alloy single crystals, tensile stress-elongation curves
4000 MUltiCrysJalline .. Pb
3500
2500
00 al
2S b
'"'"~
2000
tí
/
..!!1
'iii 1500 <=
~
/ /
1000
500
o
/(\ S-1
.'
/ /// / V->/ ~
~ .,," ,,/
~
l---"S-1 Pb
1'5-1 0.35% Sn
I
///'
.'/
O
0.05
0.10
4.5 1
0
0.15 Elongation
0.20
co~merci~1 rbll~d shlet 30 lc
0.25
• V
b. Commercial rolled sheet, 65 oC
/
3.5
V
v,v /
ro ~ 2.5
cñ
~
'" 2.0 ~
en
P ,~
¿ ./ /:
/
V
~/
/' /
600
Test specimens 19 x 32 mm (3/4 X 1/8 in.) with 250 mm (10 in.) gage length. Specimen longitudinal 500
V
~
'iii
~
c. cñ
I~
300 ~
ro
/
L~""
1- 200
i- 100 0.5
0.01
0.1
10 Greep rate, %/year
Souree: Lead and Lead Alloys, Properties and Selection: Nonferrous Alloys and Special-Purpose Materials, Vol 2, ASM Handbook, ASM lnternational, 1990, p 549
400
1.0
o
MA.002 +99.90% lead sheet, stress versus creep rate
(o.
/
7' V~
~
~
v/ 3.0
0.30
l
• Laboratory extruded, tested 30 oc
4.0
1.5
°P)
S-1
10.0007% Cu
I
(~321
Souree: S. Guruswamy, Engineering Properties and Applications of Lead Alloys, Mareel Dekker. As prepared for the lnternational Lead Zinc Researeh Organization, lne., p 110
//
ro O~
V
/
3000
Tested at 77 K
o
100
800/Pure Metals and Miscellaneous Alloys (MA)
3or-----,-----.------.-----.-----.------~~
MA.003 Refined lead and lead alloys, stress-strain curves Curve 1, refined lead. Other curves, various alloys. Curve 4 is fine grained, and curve 5 is course grained. Lead has httle mechanical strength, and its strength is very sensitive to changes in chemical composition. Variation of 99.99% purity (UNS L5001O) to 99.9999% purity (UNS L50001) can result in a change in ultimate tensile strength from 14 to 9 MPa. Changes in rate of strain of testing cause similar variatíon. Creep strength (Pb. 004) is more signíficant.
25 4
20 ro
a.
::;¡; rñ
~"' (f)
Source: B.P. Haigh and B. lones, J. Inst. Metals, Vol 51, 1933, p 49. As published in W. Hofmann, Lead and Lead Alloys, Springer Verlag, 1970, p 201
10
°0~----2~0-----4~0------6~0-----8LO-----1~0-0----~12-0~ Elongation, %
60
I
50
l/Y
11
"' 40
~t.¡
1
(])
.s= (f)
20 10
o
(
V
/
30
~
-
111
~
111-
L-
/'
001
011
12
~ 10
o o
:J
00
'6 8 O'b
0=
"o
4
o o
"o o
o o
'e"
Cl
jg
o
o
6
x :J
U
'b
cP
~
.!:::
o o
ce
2
00
oi"°o o~o
~ ~
';!:¡
o ó' o o o
'b00
00
~CO
40 Shear strain
60
80
100
MA.004 Pb-5ln lead rod, stress-strain curve (top) and change in flux versus strain (bottom) Top: stress-strain measured at 4.2 K and a strain rate of 0.0001/s. Bottom: the change in flux accompanyíng the motion of dislocatíon as a functíon of shear strain Source: e.s. Pang and 1.M. Galligan, in Precious Metals: Science and Technology, The International Precious Metals Institute, 1991, p 61
Pure Metals and Miscellaneous Alloys (MA)/801
100
80
.¡¡; c.
I
/
MA.005 Battery grade lithium (2% impurities),
0.70
I
compressive stress-strain curves
'.--- f..---0.56
I(
0.42
60
~
::;;
"'
~
40
0.28
20
0.14
0.5
1.0
1.5
2.0
2.5
3.0
~
Test direction: longitudinal. Sample size = 42.9 mm diam x 89 mm (1.688 in. diam x 3.5 in.) tested at room temperature at 3.81 mm/min (0.15 in./min). Modulus of elasticity = 1880 MPa (273 ksi); 0.2% yield strength = 0.652 MPa (94.5 psi). Other tests with rates varying from 0.127-3.81 mm!min (0.05-0.15 in./min) yielded an average modulus of elasticity of 1900 MPa (276 ksi) and an average 0.2% yield strength of 0.558 MPa (81 psi). Source: Private cornmunication with R. Schultz, Fermi National Accelerator Laboratory, March 2002
o
3.5
Slrain x 0.001
MA.006 (l-PU and 8-Pu-l.7 Ga plutonium room temperature full-range stress-strain curves Full range uniaxial stress-strain curves for unalloyed (l-
500 X a-Pu
- 60
400
ro
300
o-
- 40
::;;
~
~
"'
~
plutonium and fcc 8-phase Pu-1.7 Ga (at.%). X is fracture point compared to cast iron fracture point. 8-phase is ductile and work hardens like aluminum.
¡¡¡ 200
Casi iron
- 20 Aluminum
100
~
o-Pu
10
20 Slrain, %
30
Source: s.s. Hecker and M.E Stevens, Mechanical Behavior of Plutonium and lts Alloys, Los Alamos Science, Los Alamos National Laboratory, Vol II (No. 26), 2000, P 339
802/Pure Metals and Miscellaneous Alloys (MA)
MA.007 a-Pu and o-Pu-l.7 Ca plutonium room temperature expanded-range stress-strain curves
600
Expanded-range uniaxial stress-strain curves for unalloyed a-plutonium and fcc o-phase Pu-l.7 Ga (at.%). Modulus of elasticity, a-plutonium, 97 GPa; o-plutonium, 42 GPa.
500
x Fracture
/
400
a-pul ~ 200
Source: S.S. Hecker and M.E Stevens, Mechanical Behavior of Plutonium and Its Alloys, Los Alamos Science. Los Alamos National Laboratory, Vol II (No. 26), 2000, P 339
V
/VE /
~ = 97 GPa
-42GP,
'Jield strength
100
/
ji-
o-Pu
~
0.2
0.6
0.4
1.0
0.8
1.2
Strain. %
MA.008 Silver-copper eutectic alloys, stress-strain curves at 25 and 625 oC for lamellar and equiaxed grain structure
40 Equiaxed grain structure (25 'C)
50
Lamellar structure produced by unidirectional solidification had an initial strain rate of O.020/min. Equiaxed structure produced by extrusion and recrystallization had an initial strain rate of O.025/min. It is superplastic at 675 oC with low stress and elongation as great as 500%.
30 40
"E E
'0;
30
""~ 20
uf
ti)
~
uf ti) ~
ti)
20 10 Lamellar structure (675 'C)
10
I
Equiaxed grain structure (675 OC)
00
-'"
10
20
30
Elongation. o %
40
O
50
Source: H.E. Cline and D. Lee, Precious Metals: Science and Technology, The International Precious Metals Institute, 1991, p 645
Pure Metals and Miscellaneous Alloys (MA)/803
500~----~------~------r-----~-------r---'
MA.009 Silver, Ag-6Sn alloy, stress-strain curves for silver and silver-6 at. % Sn solid solution at various temperatures Arrows indicate end of linear hardening range (stage 2).
400~-----+------~------+------4~---,~
Source: R W.K. Honeycombe, The Plastic Deformation of Me tals, American Society for Metals, 1984, p 233
& 300~-----+------~----~~~~~---=~~=-_4 :;¡¡ ,,; Ul
~
~ 200~-----+--~~~~~--+------4------~--_4
0.1
0.2
0.3 Natural strain
0.5
0.4 8
500r------r------r-·----,------,------,-~--_,
MA.010 Silver, Ag-Ga alloy, stress-strain curves for silver and silver-gallium solid solutions Tested at 77 K, constant grain size. Arrows indicate linear hardening range (stage 2). Source: R.W.K. Honeycombe, The Plastic Deformation of Metals, American Society for Metals, 1984, p 235
& 300~----~------~~~~~~_4--~--+_----_4
:;¡¡
i
~ 200~----~~~~~~--+_----_+------+_----~
100~~~~----~-------4------+------+-----~
0.1
0.2
0.3 Natural strain
0.4 8
0.5
0.6
804/Pure Metals and Miscellaneous Alloys (MA)
MA.011 Sn-0.5Bi tin solder, true stress-strain at -20 oc (_4°F)
80
Curve 1,Sn-O.5 Bi at.% (Sn-O.9 Bi wt%); curve 2, Sn-l.5 Bi at.% (Sn-2.6 Bi wt%). Strain rate 5 x 10-5 S-l.
2
60
ca o..
:;;
~ 40 ¡¡¡ ID
~
20
/'
1--
!( -ir v
o o
0.1
Souree: T. Reinikainien and J. Kivilahti, Deformation Behavior of Dilute SnBi (0.5 to 6 Al. Pet) Solid Solution, as published in Metal!. Mater. Trans. A. ASM, Vo130A, Jan 1999, p 126
!-----~- [\1
0.2
0.3
0.4
0.5
True strain
MA.012 Sn-3.0Bi tin solder, true stress-strain at 90 oC (194°F)
80
60
ca o..
:;;
~ 40 ¡¡¡ ID
Curve 1, Sn-O.5 Bi at. % (Sn-O.9 Bi wt%); curve 2, Sn-1.5 Bi at.% (Sn-2.6 Bi wt%); curve 3, Sn-3.0 Bi at.% (Sn-5.2 Bi wt%); curve 4, Sn-6.0 Bi at.% (Sn-lO.O Bi wt%). Strain rate 5 x 10-5 S-l.
f4
1('~2 [(
~
20
Souree: T. Reinikainien and J. Kivilahti, Deformation Behavior of Dilute SnBi (0.5 to 6 Al. Pet) Solid Solution, as published in Metall. Mater. Trans. A, ASM Intemational, Vo130A, Jan 1999, p 126
~
¡..---
0.1
11
0.2
0.3 True strain
0.4
0.5
Pure Melals and Miscellaneous Alloys (MA)/805
40.-------,-------~------_,------_r------_,
30~+_----+_------~-------~------~------~
MA.013 Sn-1.5Bi tin solder, true stress-strain at 23 oC (73°F) Curve 1, Sn-O.5 Bi at. % (Sn-O.9 Bi wt%); curve 2, Sn-l.5 Bi at.% (Sn-2.6 Bi wt%); curve 3, Sn-3.0 Bi at.% (Sn-5.2 Bi wt%); curve 4, Sn-6.0 Bi at. % (Sn-1O.0 Bi wt%). Strain rate 5 x 10-5 S-l. Souree: T. Reinikainien and J. Kivilahti, Deformation Behavior of Dilute SnBi (0.5 to 6 At. Pet) Solid Solution, as published in Metal/. Mater. Trans. A, ASM Intemational, Vo130A, Jan 1999, p 126
'"
O-
:2 rJÍ
~ 20~~~~~~~~~-------4_------~------~ üi ())
~
0.1
0.3
0.2
0.4
0.5
True strain
20 --
MA.014 Sn-6.0Bi tin solder, true stress-strain at 150 oC (302°F) Curve 1, Sn-O.5 Bi ato % (Sn-O.9 Bi wt%); curve 2, Sn-l.5 Bi at.% (Sn-2.6 Bi wt%); curve 3, Sn-3.0 Bi at.% (Sn-5.2 Bi wt%). Strain rate 5 x 10 -5 S-l.
15
Souree: T. Reinikainien and J. Kivilahti, Deformation Behavior of Dilute SnBi (0.5 to 6 At. Pet) Solid Solution, as published in Metall. Mater. Trans. A, ASM, Vo130A, Jan 1999, p 126
'"
O-
:2
rJÍ
~
10
üi ())
~ 5
~
3
,---- ""~. 0.1
,
~
'-
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0.3
0.2 True strain
0.4
0.5
806/Pure Metals and Miscellaneous Alloys (MA)
400 4
350
I
V
300
2450
Comparison of curve 1, pure uranium; curve 2, U-3 Mo (wt %); curve 3, U-5 Re (wt %); and curve 4, U-3Mo-0.5 Cr (wt %). Alloys were annealed 700 to 800 oC, 2 h; water quenched, tempered 400 oC, 2 h.
2100 -2
1750 '" a.
::¡;
~
~ 200
1400
Q)
::;¡
t=
MA.015 Uranium alloys, compressive stress-strain for high hardness alloys
3
f
250
2800
150 100
~
/
~
Source: P.A.Kulin, J. De Avellar, and R. Jenkins, The Preparation of Uranium Alloys of High Density and High Hardness, as published in WD. Wilkinson Uranium Metallurgy, Vol II: Uranium Corros ion and Alloys, Interscience Publishers, 1962, p 870
tí
---
Q)
1
1050
2 1-
700
1/
350
50
0.1
0.3
0.2
o
0.5
0.4
Slrain
50
350
45
315
/ '-
40 35 30
MA.016 ZA3Fl zinc flats, tensile stress-strain curve Flat size: 12.7 x 6.35 mm (0.5 x 0.25 in.). Five specimens were tested. Average ultimate tensile strength, 281.8 MPa (40.87 ksi), average yield strength, 194.1 MPa (28.15 ksi)
260
Source: Noranda Technology Centre, Pointe Claire, Quebec, Canada
245
/
210
I
&.
::¡;
175 !Ji
I
'" ~
U)
20
140
15
105
10
70
5
35
1.00
2.00
3.00
4.00 Slrain, %
5.00
6.00
7.00
o
8.00
Pure Metals and Miscellaneous Alloys (MA)/807
~
MA.017 Powder-metallurgy zinc rod, effect of various amounts of prestrain at 240 oC (464°F) on stress-strain behavior at room temperature
36
252
32
224
28
196 Il.ro
:2
ui !I)
ui
~
1ií
~
(1)
Source: G.R. Edwards, J.C. Payne, and O.D. Sherby, Strain Softening in Powder Metallurgy Zinc, Met. Trans. A, Oct 1971, P 2956
(1)
::¡
¡!::
Rods compressed longitudinally at room temperature. Initial strain rate 0.067/min. Curves indicate that specimens which had been prestrained 55% or more at 240 oC (464 °P) no longer strain-softened appreciably and were considerably weaker than material that contained the much larger, elongated grains.
168 ~
24
16oL-----oL.1----~O.-2----0-l.-3----0~.4-----0~.5-----0~.6----~o.i12
True strain
15r-------,-------,-------,--------,-------,105
MA.018 Powder-metallurgy zinc rod, compressive stress-strain curves with effect of strain aging at 0.6 Tro
14~----~+-------+-------_r------_r-------i98
13H-------~------+_------~------_r------~91
Unload 9r-__~1~h~a~n~ne=a~I~7_+_~~~~~----_r------~68
Tm' melting temperature. These curves compare true
stress-strain curves for a continuously deformed sample and for a sample (solid circles) that was unloaded and annealed at several points in strain (open circles). Both samples were compressed, parallel to the extrusion axis at 140 oC (0.6 Tm) and at initial strain rate of 0.067/min. No drop in flow stress was ever observed when the interrupted test was continued, even after a 4 h anneal at 0.6 Tm on a sample deformed to 25% true strain. The effects of strain rate and temperature on the degree of strain softening in powder-metallurgy zinc were also inconsistent with dynamic recovery. Strain softening was enhanced by high strain rate and low temperature, being most prominent at -76 oC and 0.17/min. Source: G.R. Edwards, J.e. Payne, and O.D. Sherby, Strain Softening in Powder Metallurgy Zinc, Met. Trans. A, Oct 1971, P 2956
80~------O~.1-------0~.2-_------0~.-3-------0~.4--~~~O.~6
True strain
808/Pure Metals and Miscellaneous Alloys (MA)
36
32
r¡ ~
\
-'"
196 ¡f ::¡; cñ
\"""'"
0000
~
tí aJ
24
\
20
/
~ 0.1
Comparison of longitudinal (parallel to extrusion axis) and transverse (perpendicular to extrusion axis) mechanical behavior for powder-metallurgy zinc rods at room temperature with an initia! strain rate O.067/min
224
'00 28
~
MA.019 Powder-metallurgy zinc rod, compressive stress-strain curves at room temperature
252
~ aJ
168 ~
~
~nsverse
0.2
0.3
.6. ~-vo
OA
True strain
140
-.>
0.5
0.6
112 0.7
Source: G.R. Edwards. J.C. Payne, and O.D. Sherby, Strain Softening in Powder Metallurgy Zinc, Met. Trans. A, Oct 1971, P 2957
Alloy Index 1.1 % carbon W-type water-hardening (tool steel) .......................... 276 2.25Cr-lMo chromium-molybdenum alloy steel ........................... 94 3.3% silicon alloy steel .............. 127 3.60-3.90% carbon ductile steel ........ 29 4.35 carbon equivalent compacted graphite iron ............................ 25 9Ni-4Co-0.20C ultrahigh-strength steel ...................... 151, 152 9Ni-4Co-0.30C ultrahigh-strength steel ...................... 153-155 lOB46 carbon sleel .................. 85 13-8PH Mo (stain1ess steel) ....... 220-224 14-8PH Mo (stainless steel) .......... 225 15-5PH (stain1ess steel) .......... 225-228 15-7PH (stainless steel) .......... 228-234 17-4PH (stainless steel) .......... 234-238 17-7PH (stainless steel) .......... 238-249 17-22A(S) ultrahigh-strength steel ..... 150 18Ni (250) high-strength maraging steel ...................... 142-147 18Ni (280) high-strength maraging steel ...................... 147, 148 18Ni (300) high-strength maraging steel ...................... 148, 149 21-6-9 (stainless steel) ........... 163-165 +99.90% lead ..................... 799 124EG-T5 (cast alurninum) ........... 279 200 high-strength maraging steel ...... 141 201 (stainless steel) ............. 161, 162 201.0-T43 (cast aluminum) ....... 282, 283 201.0-T6 (cast aluminum) ........ 279,280 201.0-T6 (cast alurninum) ........ 279, 280 201.0-T7 (cast aluminum) ........ 281, 282 201-1 (stainless steel) ............... 162 201-2 (stain1ess steel) ............... 162 202 (stainless steel) ................. 163 205 (stainless steel). . . . . . . . . . . . . . . . . 162 242.0-T5 (cast aluminum) ............ 284 300M ultrahigh-strength steel ......... 150 301 (stainless steel) ......... 162, 166-180 302 (stainless steel) ................. 180 303 (stainless steel) ................. 181 304 (stainless steel) ..... 162., 181-189,214 304L (stainless steel) ............... 190 310 (stainless steel) ............. 190-192 316 (stainless stee1) ............. 193-202 316L (stain1ess steel) ............... 202 321 (stainless steel) ............. 203-205 347 (stainless steel) ............. 205-208 348 (stainless steel) ............. 209, 210 354.0-T5 (cast aluminum) ............ 286 356.0-T6 (cast alurninum) ........ 288-291 409 (stainless steel) ................. 268
410 (stain1ess steel) ............. 215, 216 420 (stainless steel) ............. 216, 217 422 (stainless steel) ............. 217, 218 434 (stainless steel) ................. 162 439 (stain1ess steel) ................. 268 1007 carbon steel ................... 69 1008 carbon steel ................ 69, 70 1015 carbon steel ................ 70, 72 1018 carbon steel ................... 92 1020 carbon steel .......... 72, 73, 80-82 1023 carbon steel ................... 83 1025 carbon (0.25% C) steel. .......... 84 1030 carbon steel ................ 73, 92 1035 carbon steel ................ 81, 82 1040 carbon steel ............. 82, 84, 92 1041 carbon steel ................... 92 1045 carbon steel ................... 85 1060 carbon steel ................... 86 1060-H12 (wrought alurninum) ........ 300 1060-H18 (wrought alurninum) ........ 300 1060-0 (wrought aluminum) . . . . . . . .. 299 1100-HI2 ........................ 301 1095 carbon steel ................... 82 1100-H16 (wrought aluminum) ........ 302 1100-H18 (wrought aluminum) ........ 302 1100-H26 (wrought alurninum) ........ 303 1100-0 (wrought aluminum) ......... 301 1112 carbon steel ................... 87 1340 carbon stee1 ................... 92 1522 carbon steel ................... 91 2014-T4 (wrought alurninum) ..... 299,311 2014-T6 (wrought alurninum) ..... 304-314 2014-T6, ciad (wrought aluminum) .............. 304-311,313 2014-T62 (wrought aluminum) ........ 315 2014-T651 (wrought aluminum) ... 315, 316 2014-T651X (wrought alurninum) ..... 316 2014-T652 (wrought aluminum) ....... 317 2017-T4 (wrought alurninum) ......... 318 2024, ciad (wrought alurninum) ....... 319 2024-T3 (wrought alurninum) .... 319,325, 327,331,332,343,346,347 2024-T3, ciad (wrought alurninum) .... 343, 346,347 2024-T3+ararnid 2/1 (alurninum larninate) ............... 503, 505, 507 2024-T3+ararnid 3/2 (alurninum larninate) ............... 503, 505, 507 2024-T3+ararnid 4/3 (alurninum laminate) ............... 504, 506, 508 2024-T3+ararnid 5/4 (alurninum laminate) ............... 504, 506, 508 2024-T351 (wrought alurninum) ... 327,332 2024-T351, ciad (wrought alurninum) ... 332 2024-T351X (wrought alurninum) ..... 333
2024-T36 (wrought aluminum) ....... 299, 334,343 2024-T36, ciad (wrought alurninum) .... 343 2024-T4 (wrought aluminum) .... 319, 322, 326,327,335,344 2024-T4, ciad (wrought alurninum) ..... 344 2024-T42 (wrought alurninum) .... 335, 336 2024-T42, cIad (wrought aluminum) ... 335, 336 2024-T6 (wrought alurninum) .... 321, 325, 328 2024-T62 (wrought alurninum) .... 337, 338 2024-T81 (wrought alurninum) ... 323,325, 329,338,339,345 2024-T81, ciad (wrought aluminum) .... 345 2024-T851 (wrought aluminum) ... 338-340 2024-T851O (wrought aluminum) .. 338, 339 2024-T8511 (wrought aluminum) .. 338, 339 2024-T852 (wrought alurninum) ... 320,321, 325 2024-T86 (wrought alurninum) ... 299,324, 325,330,341,345 2024-T86, ciad (wrought alurninum) .... 345 2024-T861 (wrought alurninum) ....... 342 2048-T851 (wrought alurninum) ... 348, 349 2090-T83 (wrought aluminum) ........ 350 2124-T851 (wrought alurninum) ... 351-354 2219-T6 (wrought alurninum) ......... 355 2219-T62 (wrought aluminum) .... 355,357 2219-T81 (wrought alurninum) .... 356,358 2219-T851 (wrought aluminum) ....... 358 2219-T852 (wrought alurninum) ... 359,360 2219-T87 (wrought alurninum) ... 356,360, 361 2519-T87 (wrought alurninum) ........ 362 2618 (wrought aluminum) ........... 363 2618-T61 (wrought aluminum) .... 363-367 3003-H12 (wrought aluminum) ........ 368 3003-H14 (wrought alurninum) ........ 368 3003-H18 (wrought aluminum) ........ 369 3003-H24 (wrought aluminum) ........ 369 3003-0 (wrought alurninum) ......... 367 3004-H34 (wrought aluminum) ........ 370 3004-H38 (wrought aluminum) ........ 371 3004-H39 (wrought aluminum) ........ 371 3004-0 (wrought alurninum) ......... 370 3140 carbon steel ................... 92 4023 carbon steel ................... 92 4027 carbon steel ................... 92 4042 carbon steel ................... 92 4130 chrornium-molybdenum alloy steel ........................ 95-99 4140 carbon steel ................... 92 4140 chrornium-molybdenum alloy steel ...................... 100-102
810 / Alloy Index
4330 nickel-chromium-molybdenum alloy steel .. . . . . . . . . . . . . . . . . . . . . 103-105 4340 carbon steel ................... 92 4340 nickel-chromium-molybdenum alloy steel . . . . . . . . . . . . . . . . . . . . . . 103-112 4350 nickel-chromium-molybdenum alloy steel . . . . . . . . . . . . . . . . . . . . . . 103-105 4419 carbon steel ................... 92 4440 carbon steel ................... 92 5052-H34 (wrought aluminum) .... 373-375 5052-H38 (wrought aluminum) .... 375-377 5052-0 (wrought aluminum) ......... 372 5083-0 (wrought aluminum) ...... 378,379 5086-H112 (wrought aluminum) ....... 381 5086-H32 (wrought aluminum) .... 381, 382 5086-H34 (wrought aluminum) .... 383, 384 5086-H36 (wrought aluminum) ........ 384 5086-0 (wrought aluminum) ...... 379,380 5140 carbon steel ................... 92 5154-0 (wrought aluminum) ......... 389 5454-H32 (wrought aluminum) ........ 390 5454-H34 (wrought aluminum) ........ 391 5454-H38 (wrought aluminum) ........ 392 5454-0 (wrought aluminum) ......... 389 5456-H111 (wrought a1uminum) ....... 397 5456-H311 (wrought a1uminum) ....... 395 5456-H321 (wrought a1uminum) ... 394, 398 5456-0 (wrought a1uminum) ..... 393, 396, 397 6013-T4 (wrought aluminum) ..... 399,400 6013-T6 (wrought aluminum) ..... 400-402 6061-0 (wrought a1uminum) ..... 299,409, 414 6061-T4 (wrought aluminum) .... 299,410, 414 6061-T6 (wrought aluminum) .... 299,406, 407,411-413,415-419 6061-T62 (wrought aluminum) .... 403,419 6061-T651 (wrought aluminum) ... 404,405, 408 6061-T651X (wrought aluminum) ..... 420, 421 6063-0 (wrought aluminum) ......... 422 6063-T6 (wrought aluminum) ..... 299, 422 701O-T7451 (wrought aluminum) ..... 423, 424 701O-T7651 (wrought aluminum) ..... 425, 426 7049-T73 (wrought aluminum) ... 427,428, 430-432,434,435,437 7049-T7351 (wrought aluminum) ..... 429, 430 7049-T76 (wrought aluminum) ... 433,434, 436 7050 (wrought aluminum) ........... 443 7050-T7351 (wrought aluminum) ..... 439, 440,442 7050-T7351X (wrought aluminum) .................. 445-447
7050-T73651 (wrought aluminum) .................. 438, 439 7050-T74 (wrought aluminum) ... 438,442, 447,448 7050-T7451 (wrought aluminum) ..... 438, 439,443-445,448,449 7050-T74511 (wrought aluminum) .449,450 7050-T7452 (wrought aluminum) ..... 441, 450-452 7049-T73511 (wrought aluminum) ..... 429 7050-T753l (wrought aluminum) ...... 442 7050-T76 (wrought aluminum) ........ 441 7050-T7651 (wrought aluminum) ..... 440, 452,453 7050-T7651X (wrought aluminum) .................. 453-455 7055-T77511 (wrought aluminum) ..... 455 7075-0 (wrought aluminum) ...... 299,463 7075-0, dad (wrought aluminum) ..... 459 7075-T6 (wrought aluminum) .... 299, 456460,463-466 7075-T6, dad (wrought aluminum) .......... 459-462, 464, 465 7075-T62 (wrought a1uminum) .... 466,467 7075-T651 (wrought aluminum) ... 465,466, 468 7075-T651X (wrought aluminum) .. 469,470 7075-T73 (wrought aluminum) .... 470,471 7075-T7351X (wrought aluminum) .... 471, 472 7075-T7352 (wrought aluminum) .. 472,473 7079-T6 (wrought aluminum) ..... 299,473 7149-T73 (wrought aluminum) .... 427,428 7149-T73511 (wrought aluminum) ..... 429 7150-T6151 (wrought aluminum) ...... 474 7150-T61511 (wrought aluminum) ..... 475 7150-T7751 (wrought aluminum) ...... 476 7150-T77511 (wrought aluminum) ..... 477 7175-T73511 (wrought aluminum) .... 477, 478 7175-T74 (wrought aluminum) .... 478-480, 482-485 7175-T7452 (wrought aluminum) .. 480,481 7178-T6 (wrought aluminum) ..... 299,486 7249-T7452 (wrought aluminum) .. 486,487 7475-T61 (wrought aluminum) .... 493,494 7475-T61, dad (wrought aluminum) ... 489, 495 7475-T651 (wrought aluminum) ... 488,490, 491 7475-T7351 (wrought aluminum) .. 488,491, 492 7475-T761 (wrought aluminum) ... 496,497 7475-T761, dad (wrought a1uminum) .. 489, 490,497-500 7475-T761+aramid 2/1 (aluminum laminate) .................. 509,510,512 7475-T761+aramid 3/2 (aluminum 1aminate) ............... 509, 511, 512
7475-T761+aramid 4/3 (aluminum laminate) ....................... 513 7475-T761+aramid 4/3,5/4 (aluminum laminate) ................... 510,511 7475-T761 +aramid 5/4 (aluminum laminate) ....................... 513 7475-T7651 (wrought aluminum) .. 492,493 8090-T8 (wrought aluminum) ......... 501 8630 nickel-chromium-molybdenum alloy steel . . . . . . . . . . . . . . . . . . 113-118 8640 carbon steel ................... 92 9310 nickel-chromium-molybdenum alloy steel . . . . . . . . . . . . . . . . . . 119, 120 52100 chromium alloy steel ........... 93 A2 (tool steel) ..................... 269 A20l.0-T7 (cast aluminum) .......... 284 A286 nickel-chromium-molybdenum alloy steel . . . . . . . . . . . . . . . . . . 102, 103 A332.0-T5(PC) (cast aluminum) ....... 285 A356.0-T6 (cast aluminum) ...... 291-293 A356.0-T6P (cast aluminum) ..... 293,294 A357.0-T6 (cast aluminum) ...... 294-297 AAR grade A high-carbon steel ........ 75 AAR grade B high-carbon steel ........ 75 AAR grade C high-carbon stee1 ........ 75 AAR specification M101 grade C austenitic manganese steel. ........ 77 AAR specification MI01 grade E austenitic manganese steel ......... 78 Admiralty brass (antimonial)(copper) ... 536 Admiralty brass (arsenical)(copper) .... 535 AerMet 100 high-strength structural steel. .............. 135, 136, 137, 138 AF 1410 ultrahigh-strength stee1 ... 155, 156 AFC-77 (stain1ess stee1) ..... 218, 219, 220 AFC-77 (stainless steel) ......... 218-220 Ag-Ga (silver) ..................... 803 Ag-6Sn (silver) .................... 803 AL 2205 (stain1ess steel) ............. 266 Alloy steel. .................... 93-127 Alpha (a) iron alloy ................. 63 Alpha (a)-Pu (plutonium) ........ 801, 802 Aluminum bronze (copper) ........... 540 A1uminum bronze D (copper) ......... 540 Aluminum-killed deep-drawing carbon steel ........................... 71 A1uminum-killed steel. ............ 67, 71 AM-350 (stainless steel) ......... 250-255 AM-355 (stain1ess steel) ......... 256-260 AM-362 (stain1ess steel) ............. 261 AM-363 (stainless steel) ............. 261 Arctic stee1 . . . . . . . . . . . . . . . . . . . . . . . 140 Arsenical tough-pitch copper. ..... 517, 518 As-quenched carbon (0.2% C) stee1 ........................... 78 ASTM A36 carbon steel ......... 132, 133 ASTM A36 high-strength low-alloy steel .......................... 129 ASTM A128-E2 carbon steel ....... 89,90
Alloy Index / 811
ASTM A242 high-strength low-alloy steel . . . . . . . . . . . . . . . . . . . . . . 129, 130 ASTM A514 grade A high-strength structural steel. .............. 133, 134 ASTM A514 high-strength structural steel ...................... 132, 133 ASTM A517 grade A high-strength structural steel. .............. 133, 134 ASTM A517 grade B high-strength structural steel. .............. 134, 135 ASTM A517 grade F high-strength structural steel. .............. 134, 135 ASTM A517 grade H high-strength structural steel. .............. 134, 135 ASTM A537 high-strength structural steel ...................... 132, 133 ASTM A572 high-strength low-alloy (grade 50) steel .............. 132, 133 ASTM A633 grade C high-strength low-alloy steel. .................. 132 Austempered ductile iron .......... 26-28 Austenitic manganese steel ......... 77, 78 AZ3IB-F (magnesium) .............. 555 AZ3IB-H24 (magnesium) ........... 556 AZ3IB-O (magnesium) ............. 556 AZ61A (magnesium) ........ 557,558,559 AZ63A (magnesium) ............... 562 AZ63A-F (magnesium) .............. 560 AZ63A-T4 (magnesium) ............. 560 AZ63A-T6 (magnesium) ......... 560,561 AZ80A-T5 (magnesium ............. 563 AZ91-T4 (magnesium) .............. 567 AZ91-T6 (magnesium) .............. 567 AZ91A-F (magnesium) .............. 564 AZ91C-T4 (magnesium) ......... 564--566 AZ91C-T6 (magnesium) ......... 565, 569 AZ9IE-T6 (magnesium) ......... 568,569 AZ92A-F (magnesium) .......... 569-571 AZ92A-T4 (magnesium) ......... 569-571 AZ92A-T5 (magnesium) ............. 571 AZ92A-T6 (magnesium) ......... 569-574 B-1900 (nickel) ................ 632, 633 Battery grade lithium (2% impurities) ... 801 Be-38Al, Lockalloy (beryIlium) ... 708, 709 Be-2%BeO (beryIlium) .............. 705 BG 170 brake grade (beryIlium) ....... 705 Blackheart malleable iron .......... 56, 57 Boron-niobium high-strength lowalloy steel ...................... 140 Boron steel . . . . . . . . . . . . . . . . . . . . . . . 140 C5 dual-phase high-strength low-alloy steel .......................... 139 C355.0-T61 (cast aluminum) ......... 287 Carbon steel .................... 67-92 Carbon steel, cold-worked (0.2% C) ..... 74 Carbon steel (Fe-0.08C-1.45Mn-0.21Si) .. 90 Cartridge brass 70-30 (copper) .... 526-528 Cast iron, unclassified ................ 23 Cast steel, unclassified ............... 23
Chrornium alloy steel ................ 93 Chromium-molybdenum alloy steel. . 94-102 Chrornium-rhenium alloy (chrornium) ... 711 Commercial bronze (copper) ...... 522, 523 Commercial high-strength low-alloy steel ...................... 139, 140 Commercially pure grade 2 titanium .................... 731,732 Commercially pure grade 3 titanium .... 734 Commercially pure grade 4 titanium 734, 735 Commercially pure molybdenum ...... 717 Commercially pure-0.03C molybdenum .................... 718 Commercially pure niobium .......... 720 Commercially pure recrystallized tantalum ....................... 724 Commercially pure tantalum .......... 723 Commercially pure titanium (CP-Ti) ................ 729-731,735 Commercially pure tungsten .......... 726 Compacted cast iron, unclassified ....... 23 Compacted graphite iron ............ 25, 62 CON-PAC high-strength low-alloy steel .......................... 129 Conventional niobium high-strength low-alloy steel. .............. 139, 140 Conventional silicon-manganese highstrength low-alloy steel ............ 140 Copper beryllium-TFOO (copper) ... 519,520 Copper beryIlium-TH04 (copper) ...... 520 Copper-boron high-strength low-alloy steel .......................... 140 Copper gilding-metal (copper) ........ 521 Copper-nickel 10% (copper) .......... 543 Copper-nickel 20% (copper) ...... 543, 544 Copper-nickel 30% (copper) ...... 544-546 Copper-nickel-aluminum (copper) ...... 554 Copper-nickel-silicon (copper) ........ 541 Copper-niobium-nickel high-strength low-alloy steel. .................. 140 Copper-niobium-titanium high-strength low-alloy steel. .................. 140 COR-TEN high-strength low-alloy steel .......................... 129 Custom 450 (stainless steel) .......... 262 Custom 450 (stainless steel) .......... 262 Custom 455 (stainless steel) .......... 263 Custom 455 (stainless steel) ...... 263-265 D2 (tool steel) ................. 269,270 D3 (tool steel) ..................... 270 D357.0-T6 (cast alurninum) .......... 297 D6A ultrahigh-strength steel. ......... 156 D6AC ultrahigh-strength steel. ........ 156 Dead soft rimmed steel ............... 67 Deep-drilling copper ................ 533 Delta (o)-Pu-1.7Ga (plutonium) ... 801,802 Dispersion strengthened copper ....... 519 Dual phase steel .................... 86 Ductile cast iron ............ 26-35, 41, 45
E8ZR (niobium) ................... 722 E332.0-T5 (cast aluminum) .......... 285 EK3IXA-T6 (magnesium) ........... 575 Electrolytic tough-pitch copper .... 515,516 EX-TEN 42 high-strength low-alloy steel .......................... 129 EX-TEN 50 high-strength low-alloy steel .......................... 129 EX-TEN 60 high-strength low-alloy steel .......................... 129 EZ33A-T5 (magnesium) ......... 576-581 F332.0-T5(SR) (cast alurninum) ....... 286 Fe-5Ni-Cr-Mo-V high-strength low-alloy steel. .................. 130 Fe-8.4Cr-8.4Ni transformation-induced plasticity (TRIP) high-strength steel .. 158 Fe-17Cr-7Ni-Ti(stainless steel) .... 265, 266 Ferritic commercial high-strength low-alloy Arctic steel ............. 140 Ferritic compacted graphite iron ..... 25, 62 Ferritic ductile iron ......... 29,31-33,35 Ferritic ductile iron, unclassified ........ 24 Ferritic malleable iron ................ 56 Ferritic nodular ductile iron ........ 36, 37 Flake cast iron, unclassified ........... 23 Flake graphite, gray iron ........... 52, 53 Forging brass (copper) .............. 534 Fully alurninum-killed deep-drawing carbon steel. ..................... 71 Gamma (y) iron alloy ................ 64 GM 980X dual phase carbon steel ...... 86 Grade 2 equivalent titanium .......... 733 Gray cast iron ................... 46-55 Gray iron, class 20 to 50 .............. 48 Gray iron, class 20 ............... 50, 51 Gray iron, class 30 .................. 48 Gray iron, c1ass 35 .................. 50 Gray iron, c1ass 40 ............... 49-51 Gray iron, c1ass 60 .................. 51 Gray iron, unclassified ............... 24 H-l1 Mod (tool steel) ........... 271-275 Hadfield steel ................... 88-90 Hastelloy X (nickel) ............ 682, 683 HaynesAlloy No. 188 (cobalt) .... 715-717 Heat-treatable aluminum alloys ........ 279 High brass (copper) ................ 529 High-carbon steel ................... 75 High leaded brass (copper) ....... 531, 532 High-silicon bronze A (copper) ........ 542 High-silicon nodular graphite iron ...... 61 High-strength low-alloy (HSLA) steel ... 86, 129-133, 138-140 High-strength maraging steel. . . . . . 141-149 High-strength nonresulfurized carbon steel ........................... 76 High-strength steel ............. 129-160 HK3IA (magnesium) ............... 582 HK3IA-H24 (magnesium) ....... 582-587 HK3IA-O (magnesium) ......... 587-592
812 / Alloy Index
HK31A-T6 (magnesium) ......... 592-594 HM21A-T8 (magnesium) ........ 595-599 HM21A-T81 (magnesium) ........... 600 HM31A (magnesium) ........... 600-602 HM31A-F (magnesium) ......... 602-606 HM31A-T5 (magnesium) ........ 607, 608 HNM nicke1 al10y steel. ............. 121 HY-TUF nickel alloy steel. ....... 122, 123 HZ32A-T5 (magnesium) ............. 609 170 brake grade (beryllium) .......... 705 1400 (beryllium) ................... 705 IN 100 (nicke1) .................... 640 IN 617 (nickel) .................... 679 Inco 713LC (nickel) ................ 634 Incoloy 25-6 (nickel) ............ 702, 703 Incoloy 330 (nickel) ................ 702 Incoloy 800 (nickel) ............ 675, 676 Incoloy 800H (nickel) ........... 676, 677 Incoloy 803 (nickel) ............ 123, 124 Incoloy 825 (nickel) ................ 701 Incoloy 840 (nickel) ............ 124, 125 Incoloy 864 (nickel) ............ 126, 127 Incoloy 901 (nickel) ................ 693 Incoloy 909 (nickel) ............ 698, 699 Incoloy A286 (nickel) ............ 125, 126 Incoloy C276 (nickel) ............... 636 Inconel 600 (nickel) ............ 637-639 Inconel 601 (nickel) ............ 683, 684 Inconel 617 (nickel) ................ 680 Inconel 625 (nickel) ............ 670-675 Inconel 686 (nickel) ................ 678 Inconel 702 (nickel) ................ 641 Inconel 706 (nickel) ............ 694-697 Inconel 713C (nickel) ............... 635 Inconel 718 (nicke1) ............ 652-659 Incone1 725 (nickel) ............ 660,661 Inconel HX (nickel) ................ 681 Inconel MA 754 (nickel) ......... 659, 660 Incone1 X-750 (nicke1) .......... 644-646 Interstitial-free steel ................. 67 Iron alloy ......................... 24 L6 (tool steel) ..................... 276 L-605 (cobalt) ................. 712, 713 L-type 10w-alloy special purpose (too1 steel) ...................... 275 Lancashire brass (copper) ............ 533 Lead alloy single crystal ............. 799 Leaded nicke1 silver (copper) ......... 551 Lead single crystal ................. 799 Low brass 80-20 (copper) ............ 525 Low-carbon steel. ............. 67-69, 71 Low-silicon bronze type B (copper) .... 542 M2 (tool steel) .................... 269 MA 6000 (nickel) .............. 642-644 Magnesium single crystal ............ 555 Malleable cast iron ............... 56-60 Manganese-chromium dual-phase high-strength 10w-alloy steel .... 139, 140
Manganese dual-phase high-strength lowalloy steel . . . . . . . . . . . . . . . . . . . . . . 140 Manganese nitride dual-phase high-strength 10w-alloy steel .... 139, 140 Maraging steel . . . . . . . . . . . . . . . . 141-149 Metastable austenitic stainless steel ...................... 210-213 Microalloyed high-strength 10w-alloy steel .......................... 131 Molybdenum-modified Hadfield steel ........................ 89, 90 Monel 400 (nickel) ............. 692, 693 Monel K-500 (nickel) ........... 684-687 MP35N multiphase alloy (cobalt) ...... 719 MP159 multiphase alloy (cobalt) ...... 719 Muntz metal copper ................ 530 N50 (beryllium) ................... 709 Naval brass (copper) ............ 537,538 Nb752 (niobium) ............... 720, 721 Ni 200 (nicke1) .................... 631 Nickel alloy iron .................... 62 Nickel alloy steel. .............. 121-127 Nickel-chromium-molybdenum alloy steel ...................... 102-120 Nickel-molybdenum alloy (nickel) ..... 700 Nickel silver (copper) ........... 546-549 Nickel silver 55-18 (copper) .......... 550 Nickel silver 65-12 (copper) .......... 550 Nickel silver 65-18 (copper) .......... 548 Nimonic 75 (nickel) ............ 647, 648 Nimonic 90 (nickel) ............ 665-668 Nimonic 263 (nickel) ............... 669 Nitronic 33 (stainless steel) ........... 214 Nitronic 60 (stainless stee1) ........... 214 Nodular ductile cast iron .... 36, 37, 39, 40, 42--44 Nodular graphite cast iron ............. 61 Nonresulfurized carbon steel. .......... 76 01 (tool stee1) ..................... 269 Oxygen-free copper ................ 515 Pb-5In (lead) ...................... 800 Pearlitic compacted graphite iron .... 25, 62 Pearlitic ductile iron ........ 29, 31-34, 41 Pearlitic ductile iron, unclassified ....... 24 Pearlitic gray iron ................ 47,49 Pearlitic malleable iron ............ 56-60 Pearlitic nodular ductile iron ..... 40, 42--44 Pen-metal copper .............. 534, 535 Phosphor bronze (copper) ........ 538,539 Phosphorus-deoxidized high residual phosphorus (copper) .... 516, 517 Powder-metallurgy zinc .......... 807, 808 Powder metal preform steel ........... 65 Pure uranium ..................... 806 QE22A-T6 (magnesium) ......... 610-612 QE22A-T8 (magnesium) ............. 613 Quenched-and-tempered carbon (0.2% C) stee1 ........................... 78
Recarburized ductile steel. ............ 38 Red brass (copper) ............. 523,524 Refined lead ...................... 800 Refined lead alloys ................. 800 René 41 (nickel) ............... 649-652 Rhenium ......................... 723 Rimmed carbon (0.03% C) steel ........ 68 Rimmed low-carbon (0.03% C) steel .... 69 Rimmed steel ................... 67-69 S200E (beryllium) .............. 705-707 SAE 950 high-strength 10w-al10y steel .. 138 SAE 950X high-strength low-alloy steel .. 86 SAE 980 high-strength low-alloy steel .. 138 SAE 980X high-strength low-alloy steel .. 86 Silicon aluminum bronze (copper) ..... 541 Silicon brass No. 1 (copper) .......... 552 Silicon brass No. 2 (copper) ...... 552,553 Silicon-manganese dual-phase high-strength 10w-alloy steel. .............. 139, 140 Silver ........................... 803 Silver-copper eutectic alloys (silver) ........................ 802 Sn-0.5Bi (tin) ................. 804, 805 Sn-1.5Bi (tin) ................. 804, 805 Sn-3.0Bi (tin) ................. 804, 805 Sn-6.0Bi (tin) ................. 804, 805 Spheroidal cast iron, unclassified ....... 23 Spring brass (copper) ........... 525, 526 SR200 (beryllium) ............. 705, 706 Standard grade nonresulfurized carbon steel ........................... 76 Steel, unclassified ................... 24 Stee1 preform powder metal ........... 65 T-1 ASTMA517, grades B, F, and H high-strength structured steel. ... 134, 135 T-l type A high-strength 10w-alloy steel .......................... 129 T-1 type B high-strength low-alloy steel .......................... 129 T-250 high-strength maraging steel ..... 141 Ta-lOW (tantalum) ............. 724, 725 TD nicke1 (nickel) .............. 688-692 Temper rolled low-carbon steel ......... 67 Thorium-carbon alloy (thorium) ....... 725 Ti-0.02C-0.20Fe-0.005H-0.01N-0.200 (titanium) ...................... 734 Ti-lOV-2Fe-3Al (titanium) ....... 777-782 Ti-l1.5Mo-6Zr-4.5Sn (titanium) ... 784-786 Ti-11Sn-5Zr-2.25Al-1Mo-0.21Si (titanium) .................. 783, 784 Ti-13V-llCr-3Al (titanium) ....... 787-792 Ti-15V-3Cr-3Sn-3Al (titanium) .... 792-795 Ti-16V-2.5Al (titanium) ......... 795-797 Ti-3Al-8V-6Cr-4Mo-4Zr (titanium) .................. 736, 737 Ti--40 (titanium) ................... 729 Ti-5Al-2.5Sn (titanium) .......... 738-740 Ti-55 (titanium) ............... 729, 735
Alloy Index / 813
Ti-6Al-2Sn-2Zr-2Mo-2Cr-0.25Si (titanium) .................. 741-744 Ti-6AI-2Sn-4Zr-2Mo (titanium) ... 744-751 Ti-6AI-2Sn-4Zr-6Mo (titanium) ....... 752 Ti-6Al-4V (titanium) ............ 753-764 Ti-6Al-6V·2Sn (titanium) ........ 765-769 Ti-70 (titanium) ................... 729 Ti-7Al-4Mo (titanium) .............. 770 Ti-8Al-lMo-lV (titanium) ....... 771-774 Ti-8Mn (titanium) .............. 774-776 Transformation-induced plasticity (TRIP) high-strength steel ...... 157-159 TRI-TEN high-strength lo~-alloy steel .. 129 TRIP steels ................... 157-159 Tungsten copper composite (copper) .... 553 TZM molybdenum alloy (molybdenum) .................. 718
U-3Mo (uranium) .................. 806 U-3Mo-0.5Cr (uranium .............. 806 U-5Re (uranium) .................. 806 Udimet 700 (U-700)(nickel) ...... 646, 647 Ultrahigh-strength steel .......... 150-156 Uranium alloys .................... 806 USS COR-TEN A high-strength low-alloy steel. .............. 129, 130 U.S.S. dual-phase 80 high-strength low-alloy steel. .................. 138 Wl (tool steel) .................... 269 W-Hf-C (tungsten) ................. 726 Waspaloy (nickel) .............. 661-664 Weathering steel ................... 140 WI-52 (cobalt) .................... 714 Worked chromium (chromium) ........ 710 X-40 (cobalt) ..................... 714
X2020-T6 (wrought aluminum) .... 299, 318 X5090-H36 (wrought aluminum) ...... 385 X5090-H38 (wrought aluminum) .. 386-388 XM-27 (stainless steel) .............. 267 ZA3Fl (zinc) ..................... 806 ZElOA-H24 (magnesium) ............ 614 ZElOA-O (magnesium) .............. 614 ZE41A-T5 (magnesium) ......... 615, 616 ZH62A-T5 (magnesium) ............. 616 Zircaloy 2 (zirconium) .............. 727 Zirconium copper (copper) ........... 518 ZK60A-F (magnesium) .......... 617, 620 ZK60A-T5 (magnesium) ......... 617-626 ZK60A-T6 (magnesium) ......... 623-628 ZK61A-T5 (magnesium) ............. 628 ZK61A-T6 (magnesium) ......... 628,629 Zr-1.5Sn (zirconium) ............... 727
UNS Index The Unified Numbersing System (UNS) is a joint effort of the Society of Automotive Engineers (SAE) and ASTM Intemational providing designations for the purpose of metal and alioy identification. The designation is not a specification. No requirements are established or implied. A02010 ...................... 279-283 A02420. '" ...................... 284 A03320 (formerly A63320) ........... 286 A03360 (formerly A13320) ........... 285 A03540 ................. '" ...... 286 A03560 ....................... 288-291 A120l0 .......................... 284 A13560 ................. , .... 291-294 A13570 ................. , .... 294-297 A33550, ................ , ......... 287 A43570 .......................... 297 A91060 .............. , .. , .... 299, 300 A91100 ...................... 301-303 A92014 ...................... 304-317 A92017 ................. , ........ 318 A92024 ...................... 319-347 A92048 ...................... 358, 359 A92090 .................., ........ 350 A92124 ...................... 351-354 A92219 ...................... 355-361 A92519 ................. , ........ 362 A92618 ...................... 363-367 A93003 ...................... 367-369 A93004 ...................... 370, 371 A95052 ...................... 372-377 A95083 ...................... 378, 379 A95086 ......... '" .......... 379-384 A95154 .......................... 389 A95454 ...................... 389-392 A95456 ...................... 393-398 A96013 ...................... 399-402 A96061 ...................... 403-421 A96063 .............. , ........... 422 A97010 ...................... 423-426 A97049 ...................... 427-437 A97050 ........ , ............ ,438-455 A97055 .......................... 455 A97075 ...................... 456-473 A97079 ................. , ........ 473 A97149 ...................... 427-429 A97150 ...................... 474-477 A97175 ...................... 477-485 A97178 .......................... 486 A97249 ...................... 486, 487 A97475 ...................... 488-500 A98090 .......................... 501 C10200 .......................... 515 CliOOO ...................... 515, 516 C12200 ...................... 516,517 C14200 ...................... 517, 518 C15000 ...................... , ... 518
C15725 .......................... 519 C17200, ..................... 519,520 C21000 .......................... 521 C22000 ...................... 522, 523 C23000 ...................... 523, 524 C24000 ...... '" ................. 525 C25600 ...................... 525; 526 C26000 ...................... 526-528 C27000 .......................... 529 C28000 .......................... 530 C33200 .......................... 531 C34200 .... , .............. 532 C35330 .......................... 533 C37700 ............... " ......... 534 C44300 .......................... 535 C44400. , .......... , ......... , ... 536 C46400 ...................... 537, 5~8 C51000 ...................... 538, 539 C61400 .......................... 540 C63000 .......................... 540 C6421O .......................... 541 C64700 .......................... 541 C65100 .......................... 542 C65500 .......................... 542 C70600 .......................... 543 C71000 ...................... 543, 544 C71500 ...................... 544-546 C74400 ...................... 546,547 C74500 ...................... 547, 548 C75200 ....... " ................. 548 C75400 .......................... 549 C75700 ................ , ......... 550 C77000 .......................... 550 C79000 .......................... 551 G10080 ........................ 69,70 G10150 ........................ 70,72 G10200 .................. 72, 73, 80-82 Gl0230 ........................... 83 Gl0250 ........................... 84 Gl0350 .............. , ......... 81, 82 G 10400 ..................... 82, 84, 92 Gl0450 ........................... 85 G10600 ....................... , ... 86 Gl0950 ....................... '" . 82 G15220 ........................... 91 G41300 ........................ 95-99 G41400 ................ , ..... 100-102 G43400 ...................... 106-112 G52986 ........................... 93 G86300 .............. 113-115, 117, 118 G93106 ...................... 119,120 ó
••••••
113042 ...... , ......... , ......... 116 113050 .......................... 116 K1151O .............. , ....... 129,130 K11576 ........ , ............. 134, 135 K11630 .. , ................... 134, 135 Kl1646 ...................... 134, 135 K11856 ...................... 133, 134 K12000 .. " ....................... 132 K14675 ..... , .................... 150 K24728 ........................ , . 156 K32550 .................... , . 122, 123 K33517 ............. '" ....... , .. 105 K92571. ..................... 155, 156 L50001 .. , .......... , ............ 800 L5001O .... , ..................... 800 Ml1311 ..................... 555, 556 M1161O ....... , .............. 557-559 M11630 ...................... 560-562 M11800 ......................... 563 M11910 ......................... 564 M11914 .................. 564-566, 569 M11918 ..................... 568, 569 Ml1920 ...................... 569-574 M12330 ...................... 576-581 M1321O ...................... 595-600 M13310, . , ................... 582-594 M13312 ...................... 600-608 M13320 ......................... 609 M16100 ......................... 614 Ml6410 ..................... 615, 616 M16600 ..... , ................ 617-628 M16610 ..................... 628, 629 M16620 ........ , ................ 616 M18220 ...................... 610-613 N02200 .......................... 631 N04400 ...................... 692, 693 N05500 ................. , .... 684-687 N06002 .................. 681, 682, 683 N06075 ...................... 647, 648 N06600 ...................... 637-639 N06601 .. , ........... , ....... 683,684 N06617 ...................... 679, 680 N06625 .. , ................... 670-675 N06686 .......................... 678 N07001 .................. , ... 661-664 N07041. , ............ , . , ..... 649-652 N07090 ...................... 665-668 N07263 .......................... 669 N07702 ............ '" ........... 641 N07713 .......................... 635 N07718 ...................... 652-659
816/ UNS Index
N07725 ...................... 660, 661 N07750 ...................... 644-646 N07754 .......................... 659 N08330 ............ '" ......... , .702 N08800 ...................... 675, 676 N0881O ...................... 676,677 N08825 .......................... 701 N08926 ...................... 702, 703 N09706 ...................... 694-697 N09901 .......................... 693 N10276 ........................ , .636 N13100 ........... , .............. 640 N19909 ...................... 698,699 R30035 .......................... 719 R30159 .......................... 719 R30188 ...................... 715-717 R30605 ...................... 712, 713 R50400 .................. 729, 731-733 R50550 .................. 729, 734, 735 R50700 .................. 729, 734, 735 R54520 ...................... 738-740 R54521 ...................... 738-740 R54620 ...................... 744-751 R5481O ...................... 771-774 R56080 ...................... 774-776 R56260 ........................ , .752 R56400 ...................... 753-764
R56401 ...................... 753-764 R56620 ...................... 765-769 R56740 .......................... 770 R5801O ...................... 787-792 R58030 ...................... 784-786 R58640 ...................... 736, 737 S 13800 ...................... 220-224 S14800 .......................... 225 S15500 ...................... 225-228 S15700 ...................... 228-234 S17400 ...................... 234-238 SI7600 ............ , ......... 265,266 S 17700 ...................... 238-249 S20100 ...................... 161, 162 S20200 .......................... 163 S20500 .......................... 162 S21800 .......................... 214 S21900 ...................... 163-165 S21904 .......................... 165 S24000 .......................... 214 S30100 .................. 162, 166-180 S30200 .......................... 180 S30300 .......................... 181 S30400 .............. 162, 181-189,214 S30403 .......................... 190 S31000 ...................... 190-192 S31600 ...................... 193-202
S31603 .......................... 202 S31803 .......................... 266 S32100 ...................... 203-205 S34700 ...................... 205-208 S34800 ...................... 209,210 S35000 ...................... 250-255 S35500 ...................... 256-260 S36200 .......................... 261 S40900 .......................... 268 S41000 ...................... 215, 216 S42000 ...................... 216, 217 S42200 ...................... 217, 218 S43035 .......................... 268 S43400 .......................... 162 S44627 .......................... 267 S45000 .......................... 262 S45500 ...................... 263-265 S65770 ...................... 218-220 S66286 ...................... 102, 103 T11302 .......................... 269 T20821 ...................... 271-275 T30102 .......................... 269 T30402 ...................... 269, 270 T30403 .......................... 270 T31501 .......................... 269 T61206 .......................... 276 T72301 .......................... 269
