215465892-Aircraft-Design-Project-150-seater-passenger-aircraft (1).pdf

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215465892-Aircra�-Design-Project150-seater-passenger-aircra� (1).pdf

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Aircra� Systems Lab Manual

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Aircra� Design Project - 280 Seat

Aircra� Design Project-1

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AIRCRAFT DESIGN PROJECT-1 150 SEATER PASSENGER AIRCRAFT

Master your semester with Scribd & The New York Times Special offer for students: Only $4.99/month.

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ACKNOWLEDGEMENT

I would like to extend my heartful thanks to Prof. ASHOK (Head of Aeronautical Department) for giving me his able support and encouragement. At this juncture I must emphasis point that this DESIGN DESIGN PROJECT PROJECT would not have have been po without the highly informative and valuable guidance by Prof.SARVESWARAN, whose vast knowledge and experie has must us go about this project with great ease. We have gr pleasure in expressing expressing our sincere sincere & whole whole hearted gratitude gratitude them. It is worth mentioning about my team mates, friends and colleagues of the Aeronautical department, for extending thei kind help whenever the necessity arose. I thank one and all w have directly or indirectly helped me in making this design project a great great success.



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ACKNOWLEDGEMENT

I would like to extend my heartful thanks to Prof. ASHOK (Head of Aeronautical Department) for giving me his able support and encouragement. At this juncture I must emphasis point that this DESIGN DESIGN PROJECT PROJECT would not have have been po without the highly informative and valuable guidance by Prof.SARVESWARAN, whose vast knowledge and experie has must us go about this project with great ease. We have gr pleasure in expressing expressing our sincere sincere & whole whole hearted gratitude gratitude them. It is worth mentioning about my team mates, friends and colleagues of the Aeronautical department, for extending thei kind help whenever the necessity arose. I thank one and all w have directly or indirectly helped me in making this design project a great great success.



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INDEX Serial No. Topic

Page No.

1 Aim of the Project 5 2 Abstract 7 3 Introduction 9 4 Comparative DataSheet 16 5 Graphs 20 6 Mean Design Parameters Parameters 39 7 Weight Estimation 41 8 Powerplant Selection 49 9 Fuel Weight Validation 53 10 Wing Selection 55 11 Airfoil Selection 60 12 Lift Estimation 70 13 Drag Estimation 75 14 Landing Gear Arrangement Arrangement 81 15 semesterFuselage Design 87 Master your with Scribd Read Free Foron 30this Days Sign up to vote title 16 Performance 94 & The New York Times  Useful  Not useful Characteristics Special offer for students: Only $4.99/month. 17 3 View Diagram 100 Cancel anytime.

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ABBREVIATION A.R. - Aspect Ratio B - Wing Span (m) C - Chord of the Airfoil (m) C root - Chord at Root (m) C tip - Chord at Tip (m) - Mean Aerodynamic Chord (m) C Cd - Drag Co-efficient Cd,0 - Zero Lift Drag Co-efficient Cp - Specific fuel consumption (lbs/hp/hr) CL - Lift Co-efficient D - Drag (N) E - Endurance (hr) E - Oswald efficiency L - Lift (N) (L/D)loiter - Lift-to-drag ratio at loiter l oiter (L/D)cruise - Lift-to-drag ratio at cruise Master your semester withofScribd M - Mach number aircraft Read Free Foron 30this Days Sign up to vote title & The New York Timesfuel fraction  Useful  Not useful Mff Mission Special offer for students: Only $4.99/month. R - Range (km) Cancel anytime.

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Sfr - Free roll Distance (m) Sg - Ground roll Distance (m) T - Thrust (N) Tcruise - Thrust at cruise (N) Ttake-off - Thrust at take-off (N) (T/W)loiter - Thrust-to-weight ratio at loiter (T/W)cruise - Thrust-to-weight ratio at cruise (T/W)take-off - Thrust-to-weight ratio at take-off Vcruise - Velocity at cruise (m/s) Vstall - Velocity at stall (m/s) Vt - Velocity at touch down (m/s) Wcrew - Crew weight (kg) Wempty - Empty weight of aircraft (kg) Wfuel - Weight of fuel (kg) Wpayload - Payload of aircraft (kg) W0 - Overall weight of aircraft (kg) W/S - Wing loading (kg/m²) ρ - Density of air (kg/m³) μ- Dynamic viscosity (Ns/m²) λ - Tapered ratio Master your semester with Scribd  Read Free Foron 30this Days Sign up to vote title  R/CYork - Rate of Climb & The New Times  Useful  Not useful Special offer for students: Only $4.99/month.

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AIM OF THE PROJECT

The aim of this design project is to design a150 seater passenger aircraft by comparing the data and and specifications of prese aircrafts in this category and to calculate the performance characteristics. Also necessary graphs need to be plotted and diagra have to be included wherever needed.

The following design requirements and research studies are set for project:  Design an aircraft that will transport 150 passengers and th baggage over a design range of 4820 km at a cruise speed about 890 km/h. To provide the passengers with high levels of safety and Master your comfort. semester with Scribd 


& The New York Times  Useful airports.  Not useful To operate from regional and international Special offer for students: Only $4.99/month.

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To offer a unique and competitive service to existing schedule operations.

To assess the development potential in the primary role of the aircraft. To produce a commercial analysis of the aircraft project.

You're Reading a Preview Unlock full access with a free trial.

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ABSTRACT

The purpose of the project is to design a 150 seater Medium Range International passenger aircraft. The aircraft will possess a low win tricycle landing gear and a conventional tail arrangement. Such an aircraft must possess a wide body configuration to provide sufficie seating capacity. It must possess turbofan engines to provide the required amount of speed, range and fuel economy for the operator The aircraft will possess two engines. You're Reading a Preview Unlock full access with a free trial.




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INTRODUCTION

At the instant time there are different types of aircraft with latest technology. Every year there is a great competition for making an aircraft of having higher capacity of members inside the aircraft. So here in thi You're Reading a Preview report, we intend to implant the differentiation among Unlock full access with a free trial. the aircrafts having sitting capacity of 100-180 members. This reportDownload givesWith theFreedifferent aspects of Trial specifications like wing specification, weight specification, power plant specification and performance specification. Airbus started the development of a very large airline Master your semester withby Scribd  (termed Megaliner Airbus in the early developme Read Free Foron 30 Days Sign up to vote this title  & The New York Times Useful  Not useful  stages) in the early 1990s, both to complete its own Special offer for students: Only $4.99/month. range of products and to break the dominance that Cancel anytime.

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only one new aircraft to be profitable in the 600 to 80 seat market segment. Each knew the risk of splitting such a niche market, as had been demonstrated by the simultaneous debut of the Lockheed L-1011 and the McDonnell Douglas DC-10: both planes met the market’s needs, but the market could profitably sustai only one model, eventually resulting in Lockheed's departure from the civil airliner business. In January 1993, Boeing and several companies in the Airbus consortium started a joint feasibility study of an aircra known as the Very Large Commercial Transport (VLCT), aiming to form a partnership to share the limited market. Airplanes come in many different You're Reading a Preview shapes and sizes depending on the mission of the Unlock full access with a free trial. aircraft, but all modern airplanes have certain Download With Free Trial components in common. These are the fuselage, wing tail assembly and control surfaces, landing gear, and powerplant.

For any airplane to fly, it must be able to lift the weig Master your semester with Scribd  Read Free Foron 30this Days Sign up to vote title  of the airplane, and the cargo. & The New York Times its fuel, the passengers,  Useful  Not useful generate most of the lift to hold the plane i Special offer forThe students:wings Only $4.99/month. the air. To generate lift, the airplane must be pushed Cancel anytime.

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The fuselage is the body of the airplane that holds all the pieces of the aircraft together and many of the oth large components are attached to it. The fuselage is generally streamlined as much as possible to reduce drag. Designs for fuselages vary widely. The fuselage houses the cockpit where the pilot and flight crew sit and it provides areas for passengers and cargo. It may also carry armaments of various sorts. Some aircraft carry fuel in the fuselage; others carry the fuel in the wings. In addition, an engine may be housed in the fuselage. You're Reading a Preview Unlock full access with a free trial.

The wing provides the principal lifting force of an Download With Free Trial airplane. Lift is obtained from the dynamic action of t wing with respect to the air. The cross-sectional shape of the wing as viewed from the side is known as the airfoil section. The planform shape of the wing (the shapesemester of the wing viewed from above) and placeme Master your withasScribd  Read Free Foron 30this Days Sign up to vote title of the wing on the fuselage (including the angle of & The New York Times  Useful  Not useful as well as the airfoil section shape, depend Special offer forincidence), students: Only $4.99/month. upon the airplane mission and the best compromise Cancel anytime.

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The control surfaces include all those moving surface of an airplane used for attitude, lift, and drag control. They include the tail assembly, the structures at the re of the airplane that serve to control and maneuver the aircraft and structures forming part of the tail and attached to the wing.





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PURPOSE AND SCOPE OF AIRPLANE DESIGN OBJECTIVES 

To meet the FUNCTIONAL, OPERATIONAL a SAFETY requirements set out OR acceptable to t USER.

ACTUAL PROCESS OF DESIGN    



Selection of aircraft type and shape Determination of geometric parameters Selection of power plant You're Reading a Preview Structural design and analysis of various Unlock full access with a free trial. components With Free Trial Determination ofDownload aircraft flight and operational characteristics .



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DESIGN CYCLE PRELIMINARY DESIGN

It consists of the initial stages of design, resulting in t presentation of a BROCHURE containing prelimina drawings and clearly stating the operational capabiliti Reading a Preview of the airplane beingYou're designed. This Brochure has to b full access with a free trial. APPROVED by the Unlock manufacturer and/or the custome The steps involved: Download With Free Trial  Layout of the main components  Arrangement of airplane equipment and control systems  Selection of power plant Master your semester with Scribd  Read Free Foron 30this Days Sign up to vote title  Aerodynamic and stability calculations & The New York Times  Useful  Not useful Special offer for students: Only $4.99/month. structural design of MAJOR  Preliminary Cancel anytime.

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DESIGN PROJECT Internal discussions  Discussions with prospective customers You're Reading a Preview  Discussions with Certification Authorities Unlock full access with a free trial.  Consultations with suppliers of power plant and Download With Free Trial major accessories  Deciding upon a BROAD OUTLINE to start the ACTUAL DESIGN, which will consist of Construction of Mock-up  Structural layout of all the individual units, and Master your semester with Scribd  Read Free Foron 30this Days Sign up to vote title  theirTimes stress analysis & The New York  Useful  Not useful Special offer for students: Only $4.99/month.  Drafting of detailed design drawings 

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Master your semester with Scribd Read Free Foron 30this Days Sign up to vote title & The New York Times  Useful  Not useful CYCLES OF DESIGN PROCESS : Special offer for students: Only $4.99/month.

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(a) Conceptual Design (b) Preliminary Design (c) Detail Design

CONCEPTUAL DESIGN:

Conceptual design is a very fluid process. Ne

ideas and problems emerge as a design is investigat

in ever increasing detail. Each time the latest design You're Reading a Preview

full access with trial. analyzed and sized, Unlock it must bea freeredrawn to reflect t

Download With Free Trial new gross weight, fuel weight, wing size, engine siz

and other changes.

Conceptual design will usually begin w

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by the prospective customer or a company generat

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The actual design effort usually begins w

conceptual sketch. A good conceptual sketch w

include the approximate wing and tail geometries, t

fuselage shape, and the internal locations of the ma components

such

as

the

engine,

cockp

payload/passenger compartment, landing gear a fuel tanks. You're Reading a Preview Unlock full access with a free trial.


PRELIMINARY DESIGN:

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configuration. During this design the specialists in are

such as structures, landing gear, and control system

will design and analyze their portion of the aircra

Testing is initiated in areas such as aerodynami propulsion, structures, and stability and control.

A key activity during this type of design

“LOFTING’. Lofting is the mathematical modeling of t outside skin of the aircraft with sufficient accuracy You're Reading a Preview

insure proper fit between its different parts, even Unlock full access with a free trial.

Download With Free designers Trial they are designed by different and possib

fabricated in different locations. The ultimate objecti

during this design is to ready the company for t

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Assuming a favorable decision for enterin

full-scale development, the detail design phase begin in which the actual pieces to be fabricated are designed. For example, during conceptual and

preliminary design the wing box will be designed and

analyzed as a whole. During detail design, that whole will be broken down into individual ribs, spars, and

skins, each of which must be separately designed and You're Reading a Preview

analyzed.

Unlock full access with a free trial.

Download With Free Trial Another important part of detail design

called production design. Specialists determine ho

the airplane will be fabricated, starting with smalle

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assembly process. Production designers frequen

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During detail design, the testing effo

intensifies. Actual structure of the aircraft is fabricat

and tested. Control laws for the flight control syste

are tested on an “iron-bird” simulator, a detail

working model of the actuators and flight cont surfaces. Flight simulators are developed and flown both company and customer test pilots.

Detail design ends with fabrication of t You're Reading a Preview

aircraft. Frequently Unlock thefull fabrication begins on part access with a free trial.

With Free Trial the aircraft before Download the entire detail-design effort

completed.



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NAME OF AIRCRAFT

Boeing

Boeing C-40 Boeing

737-100

Clipper

737-200

CAPACITY

124

LENGTH (M)

28.65

WING SPAN (M)

28.35

HEIGHT (M)

11.23

WING AREA(m^2)

102

102

THRUST (kN)

64

77

EMPTYWEIGHT(kg)

28100

31600

121 33.3 34.2 12.55

136

117

30.53

37.7

28.35

28.4

11.23

8.87

82.3

57150 MAX

TAKE

OFF 50300 You're Reading a Preview

WEIGHT

52400

4990

10700

2645


78000

Download With Free Trial SERVICE SEILING (m) 10670 12500 RANGE (km) 2850 5600 ASPECT RATIO 8

4300 8

8.5

ENDURANCE

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THRUST TO WEIGHT


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NAME OF AIRCRAFT

AIRBUS

BOEING

Boeing

A 318-100 737-300

737-500

CAPACITY

132

149

132

140

LENGTH (M)

31.44

33.414

31.008

31.2

WING SPAN(M)

34.1

28.9

28.9

35.8

HEIGHT(M)

12.51

11.15

11.15

12.5

90

90

101

EMPTY WEIGHT(Kg) 39500

32700

31300

3637

MAX

62800

60550

6600

11277

1250

4200

4444

5970

9.11

9.46

9.45

WING AREA(M^2) 112.6 THRUST( kN)

TAKE

106

OFF 68200

You're Reading a Preview

WEIGHT (Kg)


SERVICE SEILING(M) 11887 RANGE

5700

ASPECT RATIO

10

11277


ENDURANCE WINGsemester LOADING with Scribd Master your & TheTHRUST New York Times TO WEIGHT Special offer for students: Only $4.99/month.

RATIO


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Comparative Datasheet – 3 NAME OF AIRCRAFT

Boeing

Boeing

ANTONAV

COM

737-700

717-200

AN-10

ARJ

CAPACITY

148

117

100

105

LENGTH (M)

33.63

37.8

34

36.3

WING SPAN (M)

35.8

28.47

38

36.3

HEIGHT (M)

12.55

8.92

9.8

8.44

84.5

121

80

WING AREA (M^2) THRUST (kN)

117

82.3

82.3

EMPTY WEIGHT (Kg) 38147 30618 You're Reading a Preview MAX

TAKE

65700

2630

Unlock full access with a free trial. OFF 66000 49900

4361


WEIGHT (Kg)

SERVICE SEILING (M) 12500

11000

11000

1190

RANGE (kM)

6370

2645

2532

2200

ASPECT RATIO

8

7.8

7

7.9

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WING LOADING


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Comparative Datasheet – 4 NAME OF AIRCRAFT

FOKKER100 FOKKER100 Boeing TAY620

TAY650

707-020

CAPACITY

122

122

140

179

LENGTH (M)

35.53

35.53

41.25

44.0

WING SPAN (M)

28.08

28.08

39.9

39.9

HEIGHT (M)

8.5

8.5

12.65

12.9

46785

5558

100800

1165

WING AREA (M^2) 93.5

93.5

THRUST (kN)

67.2

61.6

EMPTY WEIGHT(Kg) 24375 24541 You're Reading a Preview MAX

TAKE

Unlock full access with a free trial. OFF 43090 45810


WEIGHT (Kg) SERVICE SEILING(M)

11000

11000

RANGE (KM)

2450

3170

7040

8704

ASPECT RATIO

8.5

8.5

11

11

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WING LOADING


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NAME OF AIRCRAFT

Boeing

Boeing

Boeing

An

707-320B

727 – 100

727 – 200

CAPACITY

147

149

189

99

LENGTH (M)

46.61

40.6

46.7

28.91

WING SPAN (M)

44.42

32.9

32.9

28.91

HEIGHT (M)

12.93

10.3

10.3

8.6

An

WING ARE (Sq.M)

87.32

THRUST (kN)

67.0

EMPTY WEIGHT (Kg) 66406 MAX

TAKE

OFF 151320

45360

45360

76818

95028


WEIGHT (Kg)


SERVICE SEILING Download With Free Trial

RANGE (kM)

10650

5000

4400

ASPECT RATIO

11

9

9

6.9

ENDURANCE WINGsemester LOADING with Scribd Master your & TheTHRUST New York Times TO WEIGHT Special offer for students: Only $4.99/month.

RATIO


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COMPARITIVE GRAPHS:





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LENGTH: 3o



RANGE:4800KM



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ASPECT RATIO:9.3



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MAXIMUM TAKE OFF WEIGHT:38506 kg



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EMPTY WEIGHT:31620 kg



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FUEL WEIGHT:10405 kg



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SERVICE CELING:11640 m Master your semester with Scribd & The New York Times Special offer for students: Only $4.99/month.


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Master your semester with Scribd & The New York Times THRUST:60 kN



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Master your semester with Scribd WING LOADING:547 Kg/Sq.M & The New York Times Special offer for students: Only $4.99/month.


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Master your semester with Scribd WING AREA:80 M^2 & The New York Times Special offer for students: Only $4.99/month.


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DESIGN DATA SHEET

GENERAL CHARACTERISTICS CREW

4

PASSENGER CAPACITY

100-180

LENGTH


WING SPAN (b)



WING AREA (S) 2

ASPECT RATIO(b /S)

EMPTY WEIGHT


27.2 m (89ft 2 inch) 2

80.1 m (862.18 ft 9.3 38,506 kg (84,891

MAX TAKE OFF WEIGHT

Master your semester with Scribd & The New York Times

30 m (98ft 5 inch)

lb)(corrected)


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31620 kg (69,710

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THRUST

60 KN (13,488 lbf)

PERFORMANCE CHARACTERISTICS 940 km/h (0.78

MAX SPEED

mach, 584 mph) 890 km/h (0.74

CRUISE SPEED

mach,553 mph) 4,820 km (n 2,995

RANGE SERVICE CEILING

miles) You're Reading a Preview

11,640 m(38,188



MISSION SPECIFICATION

Master your semester with Scribd  Read Free Foron 30this Days Sign up to vote title  & The New York Times  Useful  Not useful The aircraft undergoes a simple mission. The need of fue Special offer for students: Only $4.99/month.

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PAYLOAD: 150 passengers at 75kg each and 25kg of bagga each.

CREW: 2 pilots and 2 cabin attendants at 200lbs and 30 baggage each respectively.

RANGE: 2502nm, followed by 1 hour loiter followed by 100nm flight to alternate. ALTITUDE: 33,100 feet (For the design range). CRUISE SPEED: M=0.74, at 38,100 ft. You're Reading a Preview

access with aft. freeat trial.Max. W CLIMB: A dir6-ect climbUnlock to full 33,100 TO is desired


POWERPLANTS: 2 Turbo-fan engines.


MISSION SPECIFICATION


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PAYLOAD: 150 passengers at 75kg each and 25kg of bag each.

CREW: 2 pilots and 2 cabin attendants at 75kgs and 25k baggage each respectively.

RANGE: 2502nm, followed by 1 hour loiter followed by 100nm flight to alternate. ALTITUDE: 33,100 feet (For the design range). You're Reading a Preview Unlock access with aft. free trial. CRUISE SPEED: M=0.74, at full 38,100


CLIMB: A direct climb to 33,100 ft. at Max. W TO is desired. POWERPLANTS: 2 Turbo-fan engines.



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WEIGHT ESTIMATION

You're Readingmeet a Previewvery stringent ran Airplane must normally Unlock full access with a free trial.

endurance, speed and cruise speed objectives while carry Download With Free Trial

a given payload. It is vital in predicting the minimum airpla

weight and fuel weight needed to accomplish a giv

mission. We know the lift acquired is directly proportional

Master your semester with Scribd  Free Foron 30this Days Sign up to vote title weight the weight of the aircraft. Hence theRead estimation of  & The New York Times  Useful  Not useful Special offer for students: Only $4.99/month.

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a given aircraft plays a key role in design analysis.

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Payload Weight Validation (W PL):

WPL =

No. of passengers*(Wt.of passenger+Wt.of

baggage) = WPL =

150*(75+25) 15000 kg



Crew Weight Validation (W CREW):

Master your with Scribd  WCrewsemester = No. of crew members*(Crew wt. +Baggage) Read Free For 30this Days Sign up to vote on title  & The New York Times  Useful  Not useful Special offer for students: Only $4.99/month.

=

4*(75+10)

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WTO(approx)=

38393 kg [From Design data sheet]

Now, taking into consideration the appropriate mission phases:





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Airplane Type

Take Off

Climb

Descent

Landing

Business Jets Transpor t Military Trainers Superson ic Cruise

0.995

0.980

0.990

0.992

0.970

0.985

1.000

0.995

0.990

0.980

0.990

0.995

0.995

0.92-0.87

0.985

0.992





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For takeoff, segment 0-1 historical data’s shows that,

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For climb, segment 1-2 historical data shows that, W2 = 0.985 W1

Aircraft Design Project - 1 For loiter, segment 3-4 ignoring the fuel consumption during descent we assume,

4/3 = 1


Download With Trial For landing, segment 4-5 based onFree historical data we assum that,

5/4 = 0.995



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The Brequet’s range equation is used to calculate the value o 32. As we all know that maximum range is covered duri cruise we considering this equation,

R = (∞/)(/)ln (2/3) You're Reading a Preview Unlock full access with a free trial.

Download With Free Trial L/D values of similar type of aircrafts we come to know tha the approximate the value of L/D for our aircraft to be 15. So,

/ =15

Master your semester with Scribd From the Times comparative data sheet, & The New York Special offer for students: Only $4.99/month.

V∞ = 872 km/hr


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So now substituting these values in the Brequet’s range equation, R = (∞/(/)(ln 2/3) = (940/.6)(15)ln( W2/W3) ln(w2/w3)=(4820/23500)= 0.225 (w2/w3)=1.25 W3/w2=0.8 You're Reading a Preview Unlock full access with a free trial.


Master your semester with Scribd (M ):this Mission Fuel Fraction Weight Validation FF Read Free For 30 Days Sign up to vote on title & The New York Times  Useful  Not useful Special offer for students: Only $4.99/month.

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MFF =

0.796

Fuel Weight Validation (W FUEL):

WFUEL = WFUEL

=

(1-Mff )* WTO appro

(1-0.796)*38393 =

7832.2 kg

Approximate Operational Operational Weight Validation (WOE(approx) ):

WOE(apporx ) = =

WOE(apporx)- WFUEL- WPL 38393-7832-9180

Master your semester with Scribd & The New York )Times WOE(apporx = 21381 kg Special offer for students: Only $4.99/month.


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WE(tent)

=

WOE(approx) -WTFO - WCREW

Where , WTFO = = WE(tent)

0.5% of WTO(approx) 21381-0.005*38393-378 =

20811 kg

Maximum Takeoff Weight Validation (W TO):

WTO =semester WE(tent)with + WFUEL + WPL+ WCREW Master your Scribd Read Free Foron 30this Days Sign up to vote title & The New York Times  Useful  Not useful =

20811+7832.2+9180+378


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Aircraft Empty Weight Validation (WE) can be furthe split up into:

WE =

Wstruc +WPP + WFE

We estimate the Gross Wt. (Wg) =

0.9* WTO =34381 kg

From the Group Weight Jet Transport data, Wstruc =0.321

Master your semester with Scribd Wg & The New York Times Special offer for students: Only $4.99/month.

Hence

Wstruc = 11061.45 kg


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Hence

WFE = 5828 kg

WPP = 0.114 Wg

Hence WPP = 3921.5 kgYou're Reading a Preview Unlock full access with a free trial.


Hence the empty weight

WE =

=

Wstruc +WPP + W

11061.45+3921.54+5828.15

Master your semester withW Scribd Read Free Foron 30this Days 20811 kg Sign up to vote title E = & The New York Times  Useful  Not useful Special offer for students: Only $4.99/month.

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Download With Free Trial POWERPLANT SELECTION

As estimated from the design data sheet, the aircraft to

Master your semester with Scribd designed requires a thrust of 60kN.A consolidated list  of t Read Free Foron 30this Days Sign up to vote title  & The New York Times  Useful  Not useful

Cancel anytime. various engines that tally with the thrust required for t


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(kg)

RollsRoyce

1501

69.93

61.60

1200

71.2

64.54

1595

69.93

67.16

TAY 620 GE-CF348 RollsRoyce TAY 650



RollsRoyce

2104

72.97

66.72

BR710-48

Master your semester with Scribd & The New York Times Rolls-


1856

77.02


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Hence, the optimum choice of engine, from those listed

above would be the Rolls-Royce TAY 620 engine which mee

the demand of weight and thrust required at similar payloa such as the one under design.

In our design, we select 2 rear engines, namely Rolls-Royce

TAY 620 Turbo Fan Engine to meet the given design standards.





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Manufacturer

ROLLS-ROYCE

Type of the engine

TAY -620 TURBOFAN

Thrust at SL/ISA

61.6 kN (13850 lbs)

Inlet mass flow

184 Kg/s(408 lb/s)

Bypass Ratio

3.04

Overall Pressure Ratio

16.0

Fan diameter

1.17 m(44 inch)

Engine weight



14220.57 Kg(3135lbs)


Engine length

2.4 m(94.8 inch)

Turbine entry Temperature

1305 K

Master your semester with Scribd 69.93Kg/kN.hr(0.69  Specific fuel consumption Read Free Foron 30this Days Sign up to vote title lb/lbf.h  & The New York Times  Useful  Not useful (SFC)


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ROLLS-ROYCE TAY620 You're Reading a Preview Unlock full access with a free trial.




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FUEL WEIGHT VALIDATION

The choice of a suitable engine, having been made, it is now possible to estimate the amount of fuel required for a flight the given cruising speed for the given range. Wfuel = (  You're ∗  Reading a Preview Unlock full access with a free trial.

∗∗∗.)/   Download With Free Trial

The factor of 1.2 is provided for reserve fuel. Thrust at altitude is calculated using the relation:

Master your semester with Scribd =Ρalt/ ρo & The New York Times Special offer for students: Only $4.99/month.

Altitude = 10800m = 35433ft


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Number of engines = 3

CALCULATION:

Wfuel = 3×7784.2×7200×0.4×1.2 872

Wfuel = 92,553.42 kg


WING SELECTION



AERODYNAMICS

Wing Configuration:



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GEOMETRY OF THE WING:

Wing geometry is described by

a. Plan-form shape b. Aspect ratio (which is already obtained from comparative graphs) c. Wing sweep d. Taper ratio


With Free Trial the span e. Aerofoil shape andDownload thickness along

f. Geometric twist (change in aerofoil chord incidence angle along the span).

Master your semester with Scribd & The New York Times


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The maximum design velocity is 940 km/h (.78 M) - below


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Wing span, b = 27.2m Wing Area, S = 80.1 m^2 Aspect ratio, AR = b^2/S = 9.3

Taper Ratio λ = 0.36 (from Roskam book – BAE 196-200)

We know that taper ratio, λ = Ct = 0.36Cr You're Reading a Preview Unlock full access with a free trial.


Where, Ct is the root chord

Master your semesterCwith Scribd is the tip chord r & The New York Times Special offer for students: Only $4.99/month.

Ct =0.36 Cr


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Hence

Cr = 4.33m

Also Ct = 1.56m

A leading edge sweep angle of 15°. Hence we get th plan form as shown





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DETERMINATION OF THE MEAN AERODYNAMIC CHORD:

Mean chord

2

= {(2/3)*Cr (1+λ+ λ )}/ (1+λ)

= 3.16 m

Distance of the mean chord = {b*(1+2 λ)}/{6*(1+λ)} You're Reading a Preview


from the aircraft centre line


= 5.73 m



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RELATIVE LOCATION OF THE WING:

There are three basic vertical locations of the wing relative the fuselage: 1. High wing


2. Mid wing


3. Low wing

High wing: Master your semester with Scribd & The New York Times


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1. Low-slung fuselage – ease to place the fuselage lower


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Mid wing: 1. Least interference drag. 2. Gives best stability with little dihedral.

Low wing:

1. Landing gear can easily be retracted into the wing box 2. Added

fillet

interference.

will

avoid

undesirable

aerodynam



In light of all the above considerations, we choose a hi

wing configuration mainly due to structural and Landing ge considerations.



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In order to select an aerofoil the appropriate thickness chord ratio(t/c) is to be determined.

The given formula can be used to determine the thickness chord ratio: Volume of fuel = 2*{((2/3)*(t/c)*c)*c*(b/4)}*0.5*1.33

Volume of fuel = 2*{((2/3)*(t/c)*c)*c*(b/4)}*2 You're Reading a Preview Unlock full access with a free trial.


Master your semester with Scribd Read Free Foron 30this Days Sign up to vote title & The New YorkofTimes  Useful  Not useful Volume fuel = Weight of fuel(kg) Special offer for students: Only $4.99/month.

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Substituting the above weight of fuel in the equation a solving, we get the value of thickness to chord ratio as

10.965 2*{((2/3)*(t/c)*2.945)*2.945*(27.2/4)}*0.5*1.33

t/c = 0.209 (or) 0.21

As our aircraft will fly only at subsonic speeds, we ha Reading a Preview chosen a NACA 6 seriesYou're aerofoil. Unlock full access with a free trial.

Based on the t/c ratio, we have chosen the aerofoil NA Download With Free Trial 664-221.



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FUSELAGE LAYOUT

The fuselage layout is important as the length of the entire aircraft depends on this.

The length and diameter of the fuselage is related to the seating arrangement.

The fuselage of a passenger aircraft is divided into a numbe of a sections: You're Reading a Preview Unlock full access with a free trial.

1. Nose


2. Cockpit 3. Cabin 4. Tail fuselage Master your semester with Scribd & The New York Times Special offer for students: Only $4.99/month.


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Functions of fuselage:



provision of volume for payload



provide overall structural integrity



access with agear free trial. and power plant possible mountingUnlock of full landing



Once fundamental configuration is established, fuselage layout

proceeds almost independent of other design aspect Master your semester with Scribd  Read Free Foron 30this Days Sign up to vote title  & The New York Times  Useful  Not useful

Pressurisation


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A relation between the gross weight of the aircraft and the length of the aircraft.

b

Lfus = aW Where W is in lbs and Lfus is in ft. For jet transport,a=0.67,b=0.43 Lfus = 19.5m

You'refuselage Reading a Preview Nose and cockpit-Front Unlock full access with a free trial.

With Free Trial The layout of the flightDownload deck and specified pilot window

geometry is often the starting point of the overall fuselage layout.

Master your semester with Scribd  Read Free Foron 30this Days Sign up to vote title  & The New York Times  Useful  Not useful For the current design, flight decks of various airplanes are Special offer for students: Only $4.99/month.

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Passenger cabin layout

Two major geometrical parameters that specify t

passenger cabin are Cabin Diameter and Cabin Length . The

are in turn decided by more specific details like number seats, seat width, seating arrangement

(number abrea

seat pitch, aisle width and number of aisles.





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airlines. The main decision to be taken is the number of se

abreast and the aisle arrangement. The number of se

across will fix the number of rows in the cabin and there

the fuselage length. Design of the cabin cross section

further complicated by the need to provide different clas like first class, business class, economy class etc.

Cabin length:


The total number of Download seats With 150FreeisTrial distributed as 2 sea abreast.

Cabin parameters are chosen based on standards for simi airplanes. Master your semester with Scribd Read Free Foron 30this Days Sign up to vote title & The New Times  Useful  Not useful The York various parameters chosen are as follows Special offer for students: Only $4.99/month.

Cancel anytime.

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No .of aisles =1

Hence, the total cabin length will be

=

pitch*rows

= 1.06*17+additio space = 23.23m

Cabin Diameter You're Reading a Preview

Unlock full access with a free trial. width, aisle width w Using the number of seats abreast, seat

calculate the


Internal diameter of the cabin.

Master your semester with Scribd Read Free Foron 30this Days Sign up to vote title & The New York Times  Useful  Not useful d (internal) = 0.50 × 1 + 0.46 × 5 = 2.8m fus


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According to the standards prescribed, the structural

Master your semester with Scribd thickness is given by & The New York Times Special offer for students: Only $4.99/month.


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Rear Fuselage:

The rear fuselage profile is chosen to provide a smooth, l

drag shape which supports the tail surfaces. The lower side

the profile must provide adequate clearance for aircr

when rotation during take off. The rear fuselage should a

house the auxiliary power unit(APU).Based on data collect for similar aircraft we choose the ratio L tail/dfus as 4. You're Reading a Preview


With Free Trial LDownload tail = 11.2m

Total Fuselage Length



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Total

= 27.18m

Centre of gravity location:

The major weight components for which we have some id

of their location are the engine, the passengers and pilot, a

the baggage. Using this information, we can make

preliminary estimate of the location of the centre of gravity

Reading a Preview Considering the forcesYou're to be acting at middle of each pa Unlock full access with a free trial.

and hence


taking moment about the nose, we get the centre of gravit

Master your semester with Scribd Cg = & The New York Times Special offer for students: Only $4.99/month.





Useful

{190*1.975+9440*(11.61+3.95)+400*17+3952*21}

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LIFT ESTIMATION LIFT:

Component of aerodynamic force generated on aircr perpendicular to flight direction.





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Lift Coefficient (CL) • Amount of lift generated depends on: – coefficient (CL) Lift=(1/2 ρ V^2)SCl=qSCl

• CL is a measure of lifting effectiveness and mainly depend upon: – Section shape, compressibility effects (Mach number), viscous effects (Reynolds’ number). Generation of Lift You're Reading a Preview Unlock fullfrom access with a free trial. • Aerodynamic force arises two natural sources: – Variable pressure distribution. Download With Free Trial

– Shear stress distribution. • Shear stress primarily contributes to overall drag force on aircraft.

• Lift mainly due to pressure distribution, especially on mai Master your with Scribd liftingsemester surfaces, i.e. wing .  Read Free Foron 30this Days Sign up to vote title  & The New York Times Useful Not useful   • Require (relatively) low pressure on upper surface and


higher pressure on lower surface.

Cancel anytime.

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Pressure variations with angle of attack – Negative (nose-down) pitching moment at zero-lift

Master your semester with Scribd – Positive lift at  = 0 & The New York Times .



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Download Free Trial Lift Curves of Cambered andWith Symmetrical airfoils



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CALCULATION:

General Lift equation is given by,

Lift=(1/2 ρ V^2)SCl=qSCl Lift at Cruise  = 0.3715 (at the cruising altitude of 10800m) V = 242.2 m/s S = 400.72 kg/m2 You're Reading a Preview CL(cruise) = 0.63022 (from wing and airfoil Unlock full the access with a free trial. estimation) Download With Free Trial

Substituting all these values in the general lift equation,

L = 12×0.3715×242.22×400.72×0.63022 Master your semester ScribdN Lift at cruise = with 2751761.6 Read Free Foron 30this Days Sign up to vote title

& The New York Times

Lift at Take-Off  = 1.225 (at sea altitude)


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L=12×1.225×(0.7×1.2×66.86)^2×400.72×2.5

Lift at Landing  = 1.225 (at sea altitude) V = 0.7 x Vt = 0.7 x 1.3 x Vstall S = 400.72 kg/m2 CL(landing) = 3.058 (flaps extended and kept at the landing position of 40)

Substituting all these values in the general lift equation, L =12×1.225×(0.7×1.3×60.55)^2×400.72×3.5 Lift at landing =.  You're Reading a Preview Unlock full access with a free trial.




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DRAG ESTIMATION


DRAG: - Drag is the resolved component of the complete Master your semester with Scribd  aerodynamic force which is parallel Read to direction Free Foron 30this Days Signthe flight up to vote title  & The New York Times Useful Not useful   relative oncoming airflow). Cancel anytime. Special offer for students: Only $4.99/month.

- It always acts to oppose the direction of motion.

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Planform area (S), air density , flight speed (V), drag coefficient (CD) o

CD is a measure of aerodynamic efficiency and mainly depends upon: o Section shape, planform geometry, angle of attack , compressibility effects (Mach number), viscous effects (Reynolds’ number).

Drag Components - Skin Friction: You're Reading a Preview o Due to shear stresses produced in boundary layer . Unlock full access with a free trial.

Significantly more for turbulent than laminar types of Download With Free Trial boundary layers o



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Form (Pressure) Drag o Due to static pressure distribution around body component resolved in direction of motion. 

Sometimes considered separately as forebody and rear (base) drag components. o





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Result of both direct shock losses and the influence of shock waves on the boundary layer. o

o  

Often decomposed into portions related to: Lift. Thickness or Volume.





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Typical streamlining effect





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Lift induced (or) trailing vortex drag

The lift induced drag is the component which has to be included to account for the 3-D nature of the flow (finite span) and generation of wing lift





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Master your semester withisScribd The lift induced drag the component which has to be  Read Free Foron 30this Days Sign up to vote title  & The New York Times Useful Not useful   included to account for the 3-D nature of the flow (finite Special offer for students: Only $4.99/month.

span) and generation of wing lift

Cancel anytime.

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Where τ = (t/c) t / (t/c) r



(r – root, t – tip)

WING WETTED AREA: Wing wetted area

= 2 *80.1 {1+0.25(0.21) 1+

(0.95) (0.36) }

1+0.

S (wing)wet 

2

= 168.52m

You're Reading a Preview TAIL WETTED AREA: Unlock full access with a free trial.


Tail Wetted Area

= 2 x 20.81 {1+0.25(0.21) 1+

(0.95) (0.29)}

Master your semester with Scribd & The New York Times 1+0.29 Special offer for students: Only $4.99/month.

S


 2

= 43.788m


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Fuselage wetted area

=Π x Diameter x Length

=Π (2.87) (30) 2

S(fuselage)wet 

=270.49m

PARASITE DRAG ESTIMATION(CDO): CDO =

Σ K Cf Swet Sref

Where, K

-

Form factor

Cf

-

Co-efficient of Friction

Sref -





Reference Wing Area Download With Free Trial

FORM FACTOR(K):

Master your semester with Scribd  Read Free Foron 30this Days Sign up to vote title  & The New York Times Useful  Not useful  Form factor is induced to estimate the pressure drag Special offer for students: Only $4.99/month.

Cancel anytime.

caused due to viscous separation. It is estimated for the

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WING & TAIL

Kwing

=

4

0.18

4

0.18

[1+ 0.6 (0.21) + 100 (0.21) ][1.34x0.74

0.28

15)

] 0.45

=

1.8535


Ktail

=

full access with a free trial. [1+ 0.6 Unlock (0.21) + 100 (0.21) ][1.34x0.74

0.28

45)

]


0.45

Master your semester with Scribd = 1.6989 & The New York Times Special offer for students: Only $4.99/month.


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FUSELAGE



f (Fineness Ratio)

=

l/d

= 30 / 2.87 Master your semester with Scribd Read Free Foron 30this Days Sign up to vote title & The New York Times  Useful  Not useful Special offer for students: Only $4.99/month.

=

10.45

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FORMULAS USED IN DRAG ESTIMATION



Reynolds Number (at Altitude 40000ft) =

ρVD μ



Co-efficient of friction (Cf )




Total Parasite Unlock Drag Co-efficient full access with a free trial. CDO =

Σ K CfWith Swet Download Free Trial Sref



Drag Correction for 4% Interference effect

1.04xC DOwith Scribd Master your semester & The New York Times Special offer for students: Only $4.99/month.


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Induced Drag (CDI)

2

=

CL

ΠeAR

CALCULATIONS: Reynolds Mach No

Cf

CDO

no.

CDO INTERFERENCE CORRECTION(4%)

700000

0.3 0.004747 0.044145 You're Reading a Preview

0.045910773


1000000

0.4 0.004412 0.041028

0.042669057

3000000

0.5 0.003595 0.033433

0.03477016

6000000

0.6


0.00317 0.029475

0.030653716

Master your semester with Scribd  Read Free Foron 30this Days Sign up to vote title 9000000 0.7 0.002937 0.027307 0.028398934  & The New York Times  Useful  Not useful Special offer for students: Only $4.99/month.

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LANDING GEAR CONFIGURATIONS

Wheel diameter(inch) Wheel width(inch)

A

B

1.63

0.315

0.1043

0.48



MAIN LANDING GEAR No. of wheels = 4


Wheel diameter


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A (Wm) ^B

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= 0.91m (35.95 inch)

Wheel width

= A(Wm)^B

= 0.1043(18,426)^0.48

= 0.29m (11.63inch)




NOSE LANDING GEAR

No. of wheels = 2

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Wheel width

= A (Wn) ^B = 0.1043(1652.43)^0.48 = 0.0927m (3.65inch)

These calculated values for diameter and width should be increased about 30% if the aircraft is to rough unpaved runways.


Determination of position of landing gear Unlock full access with a free trial. Download With Free Trial

Xacwb = xn-Vht at/a

Master your semester with Scribd  Read Free Forcentre 30this Days Sign up to vote on title of wing Where, xacwb = aerodynamic  & The New York Times  Useful  Not useful Special offer for students: Only $4.99/month.

body

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Vht = horizontal tail volume ratio

at/a = lift slope ratio of tail to wing

Static margin = (xn – c.g)/chord

Lets assume static margin

= 18%


xn

= 3.16*0.18+16.95 = 17.51m


From the above result, it shows that position of the landing gear is longitudinally Master your semester withstable. Scribd & The New York Times Special offer for students: Only $4.99/month.


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= 16.81m

Therefore wing is placed such that the aerodynamic centre the wing is placed at 16.81m behind the nose


full access with a free trial. To find the distance ofUnlock leading edge of the wing from nose


= 16.81 – 0.47 – 0.79 = 15.55m



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Main landing gear is placed at the centre of the wing You're Reading a Preview

Therefore,



The location of the centre of the wing = distance of the leading edge of the wing from nose + (root chord/2)

Master your semester with Scribd Read Free Foron 30this Days Sign up to vote title & The New York Times Useful  Not useful = 15.55 +4.33/2 Special offer for students: Only $4.99/month.

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it can be conveniently folded rearward and upward into the fuselage. Set the nose wheel location of 4.43m as shown.





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AIRCRAFT PERFORMANCE THRUST REQUIRED:

The aircraft to be designed is assumed to be in a stead

level flight at an altitude of 30,000ft and at the given cruise velocity. The aircraft’s power plant must produce the net thrust to overcome the drag, in a sense that the net thrust produced is equal to the drag experienced by the aircraft.

The thrust required to obtain this steady velocity is given b the equation,


Thrust Required,

TR


=

_W_


CL/CD

FORMULAE For a given value of velocity (V),

Master your semester with Scribd = 2W  CLYork Times & The New Special offer for students: Only $4.99/month.

2

ρV S


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RATE OF CLIMB



The aircraft is considered to be in steady, unaccelerated, climbing flight.

Master your semester with Scribd  Read Free Foron 30this Days Sign up to vote title  The York rate of climb is calculated from the excess & The New Times useful  Useful  NotPower Special offer for students: Only $4.99/month.

denoted in the Fig.

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34654.91 x 9.81 R/C =

14.73 m/s

or

883.9 m/min

RANGE & ENDURANCE

Range is technically defined as the total distance traversed

the aircraft on a tank of fuel. Endurance is the total time t

aircraft stays on air on a tank of fuel. One of the criti

parameters influencing range and endurance is the Thru

Specific Fuel Consumption which amount of fuel consum You're Reading a Preview

full access with a freeand trial. Endurance are fou per unit thrust per unitUnlock time. Range

Download With Free Trial using the Brequet Formula.

ENDURANCE

Master your semester E = with 1 Scribd CL ln WO Read Free Foron 30this Days Sign up to vote title & The New York Times  Useful  Not useful C C W1 t D Special offer for students: Only $4.99/month. Cancel anytime.

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E

=

___1

x 1.36 x ln 34654.91

1.9425x10

-5

34654.91 -

7894.22 =

301 min or 5.02 hrs

RANGE R

=

1/2

2

_2

CL

Ct

ρ S CD

1/2

(WO

- W1

1/2

)


R

=

5

full access a free trial. 2 xUnlock 0.2334 xwith 0.514x10 x 6.937 x 22.57


Range =

3756.6 km



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further estimation of parameters. For takeoff the pi accelerates with afterburning thrust of 60kN.

Takeoff Distance

=

1.44 W

2

g ρ S CL,max T

=

1.44 x (34654.91 x 9.81)

2

9.81 x 1.225 x 80.1 x 2 x 60000 You're Reading a Preview

Takeoff Distance

=

1440.82 m



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increase in drag. The maximum lift coefficient with flaps fu employed at touchdown is 2.4.

Landing Distance(SL)

=

1.69 W

2

g ρ S CL,max {D + μr(W-L)} where, μr

SL

-

Co-efficient of rolling friction (0.4)

= _________1.69(34654.91 x 2

9.81) __________________ 9.81 x 1.225 x 80.1 x 2.4 x (23101.5 + 0.4(34654.91 x You're Reading a Preview

9.81))



Landing Distance

=

531.45 m



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BIBLIOGRAPHY

REFERENCES: rd 1. Airplane Design by Dr. Jan Roskam, 3 edition.

2. Aircraft Design: A Conceptual Approach by Daniel P th

Raymer, 4 edition. 3. Introduction to Flight by John D. Anderson, 2

nd

edition.

4. Aircraft Performance and Design by John D. Anders nd

2 edition.


With Trial 5. Theory of wing Download sections byFree Ira.H.Abbott, Dover

edition.



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215465892-Aircraft-Design-Project-150-seater-passenger-aircraft (1).pdf

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