Module 8 – Basic Aerodynamics Sample Questions
Module 8 Basic Aerodynamics 1. On a swe swept pt win wing g air aircr craf aftt if both both wing wing tip tip sec secti tion ons s los lose e lif liftt simultaneously the aircraft will a) roll b) pi pitc tch h nos nose e up up c) pitc pitch h nos nose e dow down n 2.
Lift on a delta wing aircraft a) incre increases ases with with an increased increased angle angle of inciden incidence ce (angle (angle of attack) attack) b) decreases decreases with with an increase increase in angle angle of incidenc incidence e (angle of of attack) attack) c) does not not change with with a change change in angle of incide incidence nce (angle (angle of attack) attack)
3.
On a str strai aigh ghtt win wing g air aircr craf aft, t, stal stalll com comme menc nces es at the the a) roo roott on a high high thickne thickness ss ratio ratio wing wing b) tip on on a high high thickn thickness ess ratio ratio wing wing c) tip on on a low low thick thicknes ness s ratio ratio wing wing
.
On a high wing aircraft in a turn a) the up!going up!going wing wing loses lift lift causing causing a de!stabili de!stabilising sing effect effect b) the down!goin down!going g wing gains gains lift causing causing a stabilisi stabilising ng effect effect c) the down!goin down!going g wing loses loses lift causing causing a de!stab de!stabilisin ilising g effect effect
".
#or #or the the same same angl angle e of of att attac ack, k, the the lif liftt on on a delt delta a win wing g a) is greater greater than than the lift lift on a high aspec aspectt ratio wing b) is lower lower than the lift lift on a high high aspect aspect ratio ratio wing wing c) is the same as the the lift on a high aspect aspect ratio ratio wing wing
$.
%he &' a) is take taken n from from the the e*uato e*uatorr b) is taken taken from from " " degree degrees s latitu latitude de c) as assu sume mes s a stan standa dard rd day day
+.
t high higher er alti altitu tude des s as as alt altit itud ude e inc incre reas ases es,, pre press ssur ure e a) decrea decreases ses at const constant ant rate rate b) increa increases ses epone eponenti ntiall ally y c) dec decrea reases ses e epon ponent ential ially ly
-. %he %he thru thrust st!d !dra rag g cou coupl ple e oe oerc rcom omes es the the lift lift!w !wei eigh ghtt coup couple. le. /hat /hat dire direct ctio ion n of force is re*uired to be produced by the tail of the aircraft to maintain straight and leel flight a) upwards b) dow downwar nwards ds c) sideway eways s
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Module 8 – Basic Aerodynamics Sample Questions
0.
/hen /hen the the pres pressu sure re is half half of that that at sea sea le leel el,, wha whatt is the the alti altitu tude de a) 12, 12, ft b) -, ft c) 1-, ft ft
1. 1.
ur uring ing a tu turn, rn, the the stal stalli ling ng angle ngle a) incr increa eas ses b) dec decreas rease es c) re rema main ins s the the same same
11. &f gau gauge ge pressu pressure re on a stan standar dard d day day at sea leel leel is 2" '&, '&, the the absolute pressure is a) 1.3 '& b) 3.- '& c) 30.+ ' '& 12. 12.
%he %he 4 of 5 mo moes es in flig flight ht.. %he %he most most like likely ly caus cause e of of thi this s is is a) moeme moement nt of passen passenger gers s b) moeme moement nt of the the centre centre of pres pressur sure e c) con consum sumpti ption on of of fuel fuel and and oils oils
13.
%he 4 of is the po point int wh where a) all the the forces forces on on an aircr aircraft aft act act b) the thre three e ais ais of rota rotatio tion n meet meet c) the lif liftt can can be be said said to act act
1. 1.
%he %he thr three ee ais ais of an airc aircra raft ft act act thr throu ough gh the the a) 4 of 5 b) 4 of c) stag stagna nati tion on poin pointt
1".
ressure decreases a) propo proportiona rtionally lly with with a decrea decrease se in temp temperatu erature re b) inersely inersely proportiona proportionall to temperatur temperature e c) ressure ressure and temperatur temperature e are are not not relate related d
1$. 1$.
s air air get gets s cold colder er,, the the ser seri ice ce cei ceilin ling g of an an airc aircra raft ft a) red reduces b) in incr crea eas ses c) rema remain ins s the the same same
1+. 1+.
/ha /hat is sea lee eel pre press ssur ure e a) 1 11 13.2 mb b) 11 112.3 mb c) 132.2 mb mb
1-.
/hen /hen the the weight weight of an aircra aircraft ft increa increases ses,, the the mini minimum mum drag drag spee speed d a) dec decreas rease es b) in incr crea eas ses c) rema remain ins s the the same same
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Module 8 – Basic Aerodynamics Sample Questions
0.
/hen /hen the the pres pressu sure re is half half of that that at sea sea le leel el,, wha whatt is the the alti altitu tude de a) 12, 12, ft b) -, ft c) 1-, ft ft
1. 1.
ur uring ing a tu turn, rn, the the stal stalli ling ng angle ngle a) incr increa eas ses b) dec decreas rease es c) re rema main ins s the the same same
11. &f gau gauge ge pressu pressure re on a stan standar dard d day day at sea leel leel is 2" '&, '&, the the absolute pressure is a) 1.3 '& b) 3.- '& c) 30.+ ' '& 12. 12.
%he %he 4 of 5 mo moes es in flig flight ht.. %he %he most most like likely ly caus cause e of of thi this s is is a) moeme moement nt of passen passenger gers s b) moeme moement nt of the the centre centre of pres pressur sure e c) con consum sumpti ption on of of fuel fuel and and oils oils
13.
%he 4 of is the po point int wh where a) all the the forces forces on on an aircr aircraft aft act act b) the thre three e ais ais of rota rotatio tion n meet meet c) the lif liftt can can be be said said to act act
1. 1.
%he %he thr three ee ais ais of an airc aircra raft ft act act thr throu ough gh the the a) 4 of 5 b) 4 of c) stag stagna nati tion on poin pointt
1".
ressure decreases a) propo proportiona rtionally lly with with a decrea decrease se in temp temperatu erature re b) inersely inersely proportiona proportionall to temperatur temperature e c) ressure ressure and temperatur temperature e are are not not relate related d
1$. 1$.
s air air get gets s cold colder er,, the the ser seri ice ce cei ceilin ling g of an an airc aircra raft ft a) red reduces b) in incr crea eas ses c) rema remain ins s the the same same
1+. 1+.
/ha /hat is sea lee eel pre press ssur ure e a) 1 11 13.2 mb b) 11 112.3 mb c) 132.2 mb mb
1-.
/hen /hen the the weight weight of an aircra aircraft ft increa increases ses,, the the mini minimum mum drag drag spee speed d a) dec decreas rease es b) in incr crea eas ses c) rema remain ins s the the same same
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Module 8 – Basic Aerodynamics Sample Questions
10.
n aircraft wi will ha hae a) less gliding gliding distanc distance e if it has more paylo payload ad b) more gliding gliding distance distance if it has has more more payload payload c) the same same glidin gliding g distance distance if it has has more more payloa payload d
2. 2.
/hen /hen an airc aircra raft ft epe eperie rienc nces es indu induce ced d drag drag a) air flows flows under the the wing wing spanwise spanwise towards towards the the tip and on on top of the the wing spanwise towards the root b) air flows under the wing spanwise towards the root and on top of the wing spanwise towards the tip c) 6either a) or b) since induced drag does not caused by spanwise flow
21. 21.
t stal stall, l, the the win wingt gtip ip stag stagna nati tion on poin pointt a) moes towa toward rd the lowe lowerr surface surface of the wing wing b) moes toward toward the upper upper surface surface of the wing c) does doesn7 n7tt moe moe
22. 22.
8ow 8ow doe does s &' &' at the the poi point nt of stal stalll ary ary with with heig height ht a) &t is pra practi ctical cally ly cons constan tantt b) &t incr increa ease ses s c) &t decr decrea ease ses s
23. 23.
%he %he rig riggi ging ng angl angle e of of inc incid iden ence ce of an ele eleat ator or is a) the angle angle between between the mean mean chord line line and the hori9on hori9ontal tal in the rigging rigging position b) the angle angle between between the bottom bottom surface surface of the eleat eleator or and the hori9on hori9ontal tal in the rigging position c) the angle angle between between the bottom bottom surfac surface e of the eleat eleator or and the the longitudinal datum
2. 2.
/hat /hat is is the the laps lapse e rat rate e with with rega regard rd to temp temper erat atur ure e o a) 1.0- 4 per 1 ft b) 1.0-o# per 1 ft c) o4 per 1 ft
2". 2".
/hat /hat happ happen ens s to loa load d fact factor or as as you you dec decre reas ase e turn turn rad radius ius a) &t incr increa ease ses s b) &t de decr crea ease ses s c) &t rem remai ains ns cons consta tant nt
2$. &f you you stee steepe pen n the the angle angle of a banke banked d turn turn witho without ut incr increas easing ing airspe airspeed ed or angle of attack, what will the aircraft do a) &t will will remai remain n at the the same same heig height ht b) &t will will sideslip sideslip with with attenda attendant nt loss loss of heig height ht c) &t will ill sta stall ll 2+. 2+.
n airc aircra raft ft wing ing ten tends ds to stal stalll fir first st at a) the tip tip due to a higher higher ratio thickness thickness:chor :chord d b) the tip tip due to a lower lower ratio ratio thickne thickness:c ss:chord hord c) the root root due due to a high higher er ratio ratio thicknes thickness:cho s:chord rd
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Module 8 – Basic Aerodynamics Sample Questions
2-. 2-.
ihe ihedr dral al wing wings s com comba batt ins insta tabi bili lity ty in a) pitch b) yaw c) sidesli lip p
20.
%o stop stop aircr aircraft aft decr decreas easing ing in heig height ht duri during ng a sidesl sideslip, ip, the pilot pilot can can a) ad ada anc nce e the thro thrott ttle le b) pull pull back back on the the contr control ol colum column n c) ad;ust ad;ust the rudder rudder positi position on
3. /hat /hat cont control rol surfac surface e moe moemen ments ts will will make make an aircra aircraft ft fitte fitted d with with rudderators yaw to the left a) Left rudder rudderator ator lowere lowered, d, right rudder rudderato atorr raised raised b)
/hic /hich h of of th the fo follo llowing ing is is tru true e a) Lift acts at at right angles angles to the wing wing chord chord line and weight weight acts acts ertically ertically down b) Lift acts at at right angles angles to the relati relatie e airflow and and weight weight acts ertically ertically down c) Lift acts acts at right right angles angles to the relati relatie e airflow and weight weight acts acts at right right angles to the aircraft centre line
33. will
&f the the wing wing tips tips stall stall befo before re the the root root on a swept swept wing wing aircr aircraft aft,, the aircra aircraft ft a) roll b) pi pitc tch h nos nose eu up p c) pitc pitch h nos nose e dow down n
3. 3.
Lift Lift on a delta elta wing ing air aircr craf aftt a) incre increases ases with with an increase increase angle angle of incidenc incidence e (angle of attack attack)) b) decreases with an increase in angle of incidence (angle of attack) c) does not change with a change in angle of incidence (angle of attack)
3". 3".
On a stra straig ight ht wing wing airc aircra raft ft,, sta stall ll comm commen ence ces s at at the the a) roo roott on a high high thickne thickness ss ratio ratio wing wing b) tip on on a high high thickn thickness ess ratio ratio wing wing c) tip on on a low low thick thicknes ness s ratio ratio wing wing
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Module 8 – Basic Aerodynamics Sample Questions
3$.
On a high wing aircraft in a turn a) the up!going wing loses lift causing a de!stabili9ing effect b) the down!going wing gains lift causing a stabili9ing effect c) the down!going wing loses lift causing a de!stabili9ing effect
3+.
#or the same angle of attack, the lift on a delta wing a) is greater than the lift on a high aspect ratio wing b) is lower than the lift on a high aspect ratio wing c) is the same as the lift on a high aspect ratio wing
3-.
%he &' a) is taken from the e*uator b) is taken from " degrees latitude c) assumes a standard day
30.
s altitude increases, pressure a) decreases at constant rate b) increases eponentially c) decreases eponentially
. %he thrust!drag couple oercomes the lift!weight couple. /hat direction of force is re*uired to be produced by the tail of the aircraft to maintain straight and leel flight a) >pwards b) ownwards c) 'ideways 1.
/hen the pressure is half of that at sea leel, what is the altitude a) 12, ft b) -, ft c) 1-, ft
2. a) b) c)
uring a turn, the stalling angle increases decreases remains the same
3. a) b) c)
%he ertical fin of a single engined aircraft is parallel with both the longitudinal ais and ertical ais parallel with the longitudinal ais but not the ertical ais parallel with the ertical ais but not the longitudinal ais
. a) b) c)
ircraft flying in the transonic range most often utili9e sweptback wings adanced supercritical airfoils high wings
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Module 8 – Basic Aerodynamics Sample Questions
". a) b) c)
/hich type of flap changes the area of the wing #owler 'plit 'lotted
$. #orward swept wings tend to stall at the root first so the aircraft retains lateral control, so why are they neer used on passenger aircraft a) =ecause the wing tips wash in at high wing loads b) =ecause the wing tips wash out at high wing loads c) =ecause at high loads their angle of incidence increases and the loads imposed on the wing can increase until they destroy it +. /hat happens to air flowing at the speed of sound when it enters a conerging duct a) ?elocity decreases, pressure and density increase b) ?elocity increases, pressure and density decreases c) ?elocity, pressure and density increase -. a) b) c)
s the angle of attack of an airfoil increases the centre of pressure moes forward moes aft remains stationary
0. n aircraft, which is longitudinally stable, will tend to return to leel flight after a moement about which ais a) itch b)
?orte generators on the wing are most effectie at high speed low speed high angles of attack
"2. a) b) c)
%he chord line of a wing is a line that runs from the centre of the leading edge of the wing to the trailing edge half way between the upper and lower surface of the wing one wing tip to the other wing tip
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Module 8 – Basic Aerodynamics Sample Questions
"3. a) b) c)
%he angle of incidence of a wing is an angle formed by lines parallel to the chord line and longitudinal ais parallel to the chord line and the lateral ais parallel to the chord line and the ertical ais
". a) b) c)
%he centre of pressure of an aerofoil is located 3 ! A of the chord line back from the leading edge 3 ! A of the chord line forward of the leading edge "A of the chord line back from the leading edge
"". a) b) c)
4ompressibility effect is drag associated with the form of an aircraft drag associated with the friction of the air oer the surface of the aircraft the increase in total drag of an airfoil in transonic flight due to the formation of shock waes
"$. Lateral control of an aircraft at high angle of attack can be maimised by using a) fences b) orte generators c) wing slots "+. a) b) c)
'tall strips are always made of metal on the leading edge of a wing fitted forward of the ailerons
"-. a) b) c)
'tall strips cause the wing root to stall cause the wing tip to stall cause the wings to stall symmetrically
"0. ue to the interference of the airflow on a high wing aircraft between the fuselage and the wings, the lateral stability of the aircraft in a gusty wind situation will cause a) the upper wing to increase its lift b) the upper wing to decrease its lift c) the lower wing to decrease its lift $. a) b) c)
'lats reduce the stall speed reduce the tendency of the aircraft to @aw decrease the aerofoil drag at high speeds
$1. /hat is the temperature lapse rate for aircraft flying below 3$, feet altitude a) 1B4 per 1 feet b) 3B4 per 1 feet c) 2B4 per 1 feet
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Module 8 – Basic Aerodynamics Sample Questions
$2. a) b) c)
#or a pressure of 2"lbs:inC at sea leel, what is the absolute pressure 30.+ lbs:inC 0.+ lbs:inC 1.3 lbs:in
$3. n aircraft banks into a turn. 6o change is made to the airspeed or angle of attack. /hat will happen a) %he aircraft enters a side slip and begins to lose altitude b) %he aircraft turns with no loss of height c) %he aircraft yaws and slows down $. a) b) c)
%he relationship between induced drag and airspeed is directly proportional to the s*uare of the speed inersely proportional to the s*uare of the speed directly proportional to speed
$". /hat is the definition of ngle of &ncidence a) %he angle the underside of the mainplane or tailplane makes with the hori9ontal b) %he angle the underside of the mainplane or tailplane makes with the longitudinal datum line c) %he angle the chord of the mainplane or tailplane makes with the hori9ontal $$. a) b) c)
/hat is =oundary Layer 'eparated layer of air forming a boundary at the leading edge %urbulent air moing from the leading edge to trailing edge 'luggish low energy air that sticks to the wing surface and gradually gets faster until it ;oins the free stream flow of air
$+. a) b) c)
%he normal ais of an aircraft passes through the centre of graity a point at the center of the wings at the centre of pressure
$-. On a high winged aircraft, what effect will the fuselage hae on the up! going wing a) %he up!going wing will hae a decrease in angle of attack and therefore a decrease in lift b) %he down!going will hae a decrease in angle of attack and therefore a decrease in lift c) %he up!going wing will hae an increase in angle of attack and therefore a decrease in lift $0. /hat is the collectie term for the fin and rudder and other surfaces aft of the centre of graity that helps directional stability a) Dffectie keel surface b) Dmpennage c) #uselage surfaces
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Module 8 – Basic Aerodynamics Sample Questions
+. a) b) c)
%emperature aboe 3$, feet will decrease eponentially remain constant increase eponentially
+1. a) b) c)
decrease in incidence toward the wing tip may be proided to preent aderse yaw in a turn preent spanwise flow in maneuers retain lateral control effectieness at high angles of attack
+2. a) b) c)
%he angle of attack which gies the best L: ratio decreases with a decrease in density in unaffected by density changes increases with a decrease in density
+3.
#or a gien aerofoil production lift, where E pressure and ? E elocityF
a) 1 is greater than 2, and ?1 is greater than ?2 b) 1 is less than 2 and ?1 is greater than ?2 c) 1 is greater than 2, and ?1 is less than ?2 +. a) b) c)
Low wing loading increases stalling speed, landing speed and landing run increases lift, stalling speed and maneuerability decreases stalling speed, landing speed and landing run
+". ue to the change in downwash on an untapered wing (i.e. one of constant chord length) it will a) not proide any damping effect when rolling b) tend to stall first at the root c) not suffer aderse yaw effects when turning +$. a) b) c)
%rue stalling speed of an aircraft increases with altitude because reduced temperature causes compressibility effect because air density is reduced because humidity is increased and this increases drag
++. s a general rule, if the aerodynamic angle of incidence (angle of attack) of an aerofoil is slightly increased, the centre of pressure will a) neer moe b) moe forward towards the leading edge c) moe towards the tip Page !
Module 8 – Basic Aerodynamics Sample Questions
+-. a) b) c)
%he Gwing setting angleG is commonly known as angle of incidence angle of attack angle of dihedral
+0. a) b) c)
On a ery humid day, an aircraft taking off would re*uire a shorter take off run a longer take off run humidity does not affect the take off run
-. n aircraft is flying at 3" H8, into a head wind of +" H8, what will its ground speed be a) 1+" mph b) 2+" mph c) 2 mph -1. a) b) c)
/hen does the angle of incidence change /hen the aircraft attitude changes /hen the aircraft is ascending or descending &t neer changes
-2. s the angle of attack decreases, what happens to the centre of pressure a) &t moes forward b) &t moes rearwards c) 4entre of pressure is not affected by angle of attack decrease -3. decrease in pressure oer the upper surface of a wing or aerofoil is responsible for a) approimately 2:3 (two thirds) of the lift obtained b) approimately 1:3 (one third) of the lift obtained c) approimately 1:2 (one half) of the lift obtained -. a) b) c)
/hich of the four forces act on an aircraft Lift, graity, thrust and drag /eight, graity, thrust and drag Lift, weight, graity and drag
-". /hich of the following types of drag increases as the aircraft gains altitude a) arasite drag b) &nduced drag c) &nterference drag -$. 4orrecting for a disturbance which has caused a rolling motion about the longitudinal ais would re!establish which of the following a) Lateral stability b) irectional stability c) Longitudinal stability
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Module 8 – Basic Aerodynamics Sample Questions
-+. %he layer of air oer the surface of an aerofoil which is slower moing, in relation to the rest of the airflow, is known as a) camber layer b) boundary layer c) none of the aboe --. a) b) c)
/hat is a controlling factor of turbulence and skin friction spect ratio #ineness ratio 4ounter sunk riets used on skin eterior
-0. 4hanges in aircraft weight a) will not affect total drag since it is dependant only upon speed b) cause corresponding changes in total drag due to the associated lift change c) will only affect total drag if the lift is kept constant 0. %he aircraft stalling speed will a) increase with an increase in weight b) be unaffected by aircraft weight changes since it is dependant upon the angle of attack c) only change if the H%H were changed 01. a) b) c)
&n a bank and turn etra lift is not re*uired etra lift is not re*uired if thrust is increased etra lift is re*uired
02. %o maintain straight and leel flight on the aeroplane shown, with a decrease in tail!plane download the mainplane lift would hae to
a) remain constant b) decrease c) increase 03. %o achiee the maimum distance in a glide, the recommended air speed is a) as close to the stall as practical b) as high as possible with ?6D c) the speed where the L: ratio is maimum
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Module 8 – Basic Aerodynamics Sample Questions
0. &f the 4 of 5 is aft of the 4entre of ressure a) changes in lift produce a pitching moment which acts to increase the change in lift b) when the aircraft sideslips, the 4 of 5 causes the nose to turn into the sideslip thus applying a restoring moment c) when the aircraft yaws the aerodynamic forces acting forward of the 4entre of ressure 0". a) b) c)
orpoising is an oscillatory motion in the pitch plane roll plane yaw plane
0$. a) b) c)
irectional stability is maintained by the mainplanes, and controlled by the ailerons by the tailplane, and controlled by the eleators by the keel surface and fin, and controlled by the rudder
0+. ue to the interference effects of the fuselage, when a high wing aeroplane sideslips a) the accompanying rolling due to keel surface area is destabili9ing b) the accompanying lift changes on the wings produces a stabili9ing effect c) the accompanying rolling due to the fin is destabili9ing 0-. a) b) c)
%he power re*uired in a hori9ontal turn is greater than that for leel flight at the same airspeed must be the same as that for leel flight at the same airspeed is less than that for leel flight at the same airspeed
00. a) b) c)
wing mounted stall sensing deice is located usually on the under surface always at the wing tip always on the top surface
1. a) b) c)
#or an aircraft in a glide thrust, drag, lift and weight act on the aircraft weight, lift and drag act on the aircraft weight and drag only act on the aircraft
11. a) b) c)
%he upper part of the wing in comparison to the lower deelops more lift deelops the same lift deelops less lift
12. a) b) c)
/hat effect would a forward 45 hae on an aircraft on landing &ncrease stalling speed 6o effect on landing
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Module 8 – Basic Aerodynamics Sample Questions
13. a) b) c)
I68 refers to Iuite near hori9on setting the altimeter to 9ero setting the mean sea leel atmospheric pressure so an altimeter reads the aerodrome altitude aboe mean sea leel
1. a) b) c)
I6D refers to 'etting an altimeter to read aerodrome altitude aboe sea leel Iuite new e*uipment setting the mean sea leel atmospheric pressure in accordance with &4O standard atmosphere i.e. 113 millibars
1". a) b) c)
n aspect ratio of - would mean span $, mean chord mean chord $ , span span s*uared $ ,chord -
1$. a) b) c)
&f an aircraft in leel flight loses engine power it will pitch nose up pitch nose down not change pitch without drag increasing
1+. a) b) c)
I#D is sea leel pressure airfield pressure difference between sea leel and airfield pressure
1-. a) b) c)
%he lift :drag ratio at stall increases decreases is unchanged
10. a) b) c)
On a straight unswept wing, stall occurs at the thick portion at the wing root the thick portion at the wing tip the thin portion at the wing tip
11. a) b) c)
uring a climb from a die the thrust re*uired is greater than re*uired for leel flight the thrust re*uired is lower than for leel flight the thrust re*uired is the same as for leel flight
111. a) b) c)
/hen power is off, the aircraft will pitch nose down nose up trim leel
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Module 8 – Basic Aerodynamics Sample Questions
112. a) b) c)
ngle of attack on a down going wing in a roll increases decreases unaffected
113. will a) b) c)
#or any gien speed, a decrease in aircraft weight, the induced drag increase decrease remain the same
11. a) b) c)
%he amount of lift generated by a wing is greatest at the root greatest at the tip constant along the span
11". &nduced rag is a) greatest towards the wing root and downwash is greatest at the tip b) greatest towards the wing tip and downwash is greatest towards the root c) greatest towards the tip and downwash decreases from tip to root 11$. a) b) c)
&nduced rag is e*ual to profile drag at stalling angle e*ual to profile drag at ?md neer e*ual to profile drag
11+. a) b) c)
/ith an increase in aircraft weight ?md will be at the same speed ?md will be at a lower speed ?md will be at a higher speed
11-. a) b) c)
#or a gien &' an increase in altitude will result in no change in the alue of induced drag an increase in induced drag an increase in profile drag
110. a) b) c)
s the angle of attack of a wing is increased in leel flight the 4 of 5 moes aft and the 4 of forward the 4 of and transition point moe forward the 4 of moes forward and the stagnation point aft oer the upper surface
12. a) b) c)
'tall inducers may be fitted to a wing at the tip to cause the root to stall first at the root to cause the tip to stall first at the root to cause the root to stall first
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Module 8 – Basic Aerodynamics Sample Questions
121. a) b) c)
/ith increasing altitude pressure decreases and temperature decreases at the same rate as pressure reduces temperature decreases but at a lower rate than pressure reduces temperature remains constant to - ft
122. %he 4entre of ressure is a) the point on the chord line at which the resultant lift force may be said to act b) the point of maimum pressure on the under surface of the wing c) the centre of graity of the wing 123. a) b) c)
&f the angle of attack is increased the 4entre of ressure will moe forward moe rearward remain stationary
12. a) b) c)
%he optimum angle of attack of an aerofoil is the angle at which the aerofoil produces maimum lift the aerofoil produces 9ero lift the highest lift:drag ratio is produced
12". a) b) c)
high aspect ratio wing has a increased induced drag decreased induced drag decreased skin friction drag
12$. a) b) c)
Hinimum total drag of an aircraft occurs at the stalling speed when profile drag e*uals induced drag when induced drag is least
12+. &f the weight of an aircraft is increased, the induced drag at a gien speed a) will increase b) will decrease c) will remain the same 12-. a) b) c)
%he transition point on a wing is the point where the flow separates from the wing surface the boundary layer flow changes from laminar to turbulent the flow diides to pass aboe and below the wing
120. a) b) c)
%he boundary layer of a body in a moing airstream is a thin layer of air oer the surface where the air is stationary a layer of separated flow where the air is turbulent a layer of air oer the surface where the airspeed is changing from free stream speed to 9ero speed
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Module 8 – Basic Aerodynamics Sample Questions
13. a) b) c)
laminar boundary layer will produce more skin friction drag than a turbulent one less skin friction drag than a turbulent one the same skin friction drag as a turbulent one
131. a) b) c)
Longitudinal stability is gien by the fin the wing dihedral the hori9ontal tailplane
132. a) b) c)
Lateral stability is gien by the ailerons the wing dihedral the hori9ontal tailplane
133. a) b) c)
'tability about the lateral ais is gien by wing dihedral the hori9ontal tailplane the ailerons
13. a) b) c)
'weepback of the wings will increase lateral stability decrease lateral stability not affect the lateral stability
13". a) b) c)
utch
13$. a) b) c)
high wing position gies more lateral stability than a low wing less lateral stability than a low wing the same lateral stability as a low wing
13+. a) b) c)
On an aircraft in an unpowered steady speed descent the lift e*uals the weight the weight e*uals the drag the weight e*uals the resultant of the lift and drag
13-. a) b) c)
/hen an aircraft rolls to enter a turn and power is not increased the lift e*uals the weight the lift is greater than the weight the lift is less than the weight
130. a) b) c)
%he boundary layer is thickest at the leading edge thickest at the trailing edge constant thickness from leading to trailing edges
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Module 8 – Basic Aerodynamics Sample Questions
1. %he amount of thrust produced by a ;et engine or a propeller can be calculated using a) 6ewton7s 1st law b) 6ewton7s 2nd law c) 6ewton7s 3rd law 11. a) b) c)
n engine which produces an efflu of high speed will be more efficient less efficient speed of efflu has no affect on the engine efficiency
12. /hen an aircraft with a 4 of 5 forward of the 4 of rolls, the nose of the aircraft will a) stay leel b) rise c) drop 13. a) b) c)
irectional stability may be increased with pitch dampers horn balance yaw dampers
1. a) b) c)
Lateral stability may be increased with increased lateral dihedral increased lateral anhedral increased longitudinal dihedral
1". a) b) c)
Longitudinal stability is increased if the 4 moes forward of the 45 %hrust acts on a line below the total drag 45 is forward of the 4
1$. a) b) c)
/ing loading is calculated by weight diided by gross wing area diided by lift multiplied by gross wing area
1+. a) b) c)
&nduced drag is inersely proportional to the s*uare of speed proportional to speed nothing to do with speed
1-. a) b) c)
&n a bank, the weight is increased decreased the same
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Module 8 – Basic Aerodynamics Sample Questions
10. a) b) c)
L: ratio is higher at supersonic cruise speed higher at sub sonic speed the same
1". a) b) c)
%he power re*uired at low altitude for a gien &' is the same as at high altitude higher lower
1"1. a) b) c)
&f the stall speed is +" knots what is the same stall speed in mph +" .-+ +" : .-+ +" : .-+ relatie density
1"2. a) b) c)
s the angle of attack increases the stagnation point moes towards the upper surface moes towards the lower surface does not moe
1"3. a) b) c)
%he term pitch!up is due to compressibility effect ground effect longitudinal instability
1". a) b) c)
&n a steady climb at a steady &', the %' is more than &' less than &' the same
1"". a) b) c)
n untapered wing will hae no yaw effect in banking hae no change in induced drag in the bank stall at the root first
1"$. a) b) c)
/ith the ailerons away from the neutral, induced drag is unchanged but profile drag is higher higher on the lower wing plus profile drag increases higher on the upper wing plus profile drag increases
1"+. a) b) c)
%he lift drag ratio is higher at mach numbers aboe supersonic higher at sub sonic mach numbers the same
1"-. a) b) c)
%he force opposing thrust is drag lift /eight
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Module 8 – Basic Aerodynamics Sample Questions
1"0. a) b) c)
irectional stability is about the normal ais longitudinal ais lateral ais
1$. a) b) c)
Lateral stability is about the longitudinal ais normal ais ertical ais
1$1. a) b) c)
ll the lift can be said to act through the centre of pressure centre of graity normal ais
1$2. a) b) c)
Longitudinal stability is proided by the hori9ontal stabili9er ertical stabili9er mainplane
1$3. a) b) c)
%he concept of thrust is eplained by 6ewton7s 1st law 6ewton7s 3rd law =ernoulli7s theorem
1$. a) b) c)
%he camber of an aerofoil section is the curature of the median line of the aerofoil the angle of incidence towards the tip of a wing the angle which the aerofoil makes with the relatie airflow
1$". a) b) c)
&f the aircraft turns and side!slips the sweepback of the wing will correct the sideslip the dihedral of the wing will correct the sideslip the keel surface will correct the sideslip
1$$. a) b) c)
Hoement of an aircraft about its lateral ais is pitching is rolling is yawing
1$+. a) b) c)
&nduced drag is caused by skin friction results from disturbed airflow in the region of mainplane attachments is associated with the lift generated by an aerofoil
1$-. %he centre of pressure is a) the point on the chord line through which the total resultant lift force on the aerofoil may be said to act b) the point of maimum pressure on the undersurface of a mainplane c) the point at which the four forces acting on an aircraft are said to act
Page 1!
Module 8 – Basic Aerodynamics Sample Questions
1$0. a) b) c)
t what altitude is tropopause $3, ft. 3$, ft. "+, ft.
1+. a) b) c)
/hat approimate percentage of oygen is in the atmosphere 12A 21A +-A
1+1. a) b) c)
/hich has the greater density air at low altitude air at high altitude it remains constant
1+2. s air flows oer the upper cambered surface of an aerofoil, what happens to elocity and pressure a) ?elocity decreases, pressure decreases b) ?elocity increases, pressure increases c) ?elocity increases, pressure decreases 1+3. a) b) c)
/hat is the force that tends to pull an aircraft down towards the earth rag %hrust /eight
1+. a) b) c)
/hich of the following act in opposition to forward moement Lift 5raity rag
1+". %he angle at which the chord line of the aerofoil is presented to the airflow is known as a) angle of attack b) angle of incidence c) resultant 1+$. %he imaginary straight line which passes through an aerofoil section from leading edge to trailing edge is called a) centre of pressure b) the direction of relatie airflow c) the chord line 1++. /hat is the angle between the chord line of the wing, and the longitudinal ais of the aircraft, known as a) angle of attack b) angle of incidence c) angle of dihedral
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Module 8 – Basic Aerodynamics Sample Questions
1+-. n aircraft disturbed from its normal flight path, and automatically returns to that normal flight path, without any action on the part of the pilot is known as a) aircraft stability b) aircraft instability c) aircraft stall 1+0. a) b) c)
irectional control is proided by hori9ontal stabili9er rudder eleator
1-. a) b) c)
bout which ais of the aircraft does a rolling motion take place 6ormal ais Longitudinal ais Lateral ais
1-1. a) b) c)
/hich motion happens about the lateral ais itching @awing
1-2. a) b) c)
/ing tip ortices create a type of drag known as form drag induced drag profile drag
1-3. a) b) c)
/hich of the following describes the JDmpennageK 6ose section of an aircraft, including the cockpit %ail section of the aircraft, including fin, rudder, tail plane and eleators %he wings, including the ailerons
1-. a) b) c)
t what altitude does stratosphere commence approimately 'ea leel $3, ft 3$, ft
1-". /hen an aircraft is in straight and leel unaccelerated flight, which of the following is correct a) Lift and weight are e*ual, and thrust and drag are e*ual b) Lift greater than weight, and thrust greater than drag c) Lift greater than weight, and thrust is less than drag 1-$. s the angle of attack is increased (up to the stall point), which of the following is correct a) ressure difference between top and bottom of the wing increases b) Lift increases c) =oth a) and b) are correct
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Module 8 – Basic Aerodynamics Sample Questions
1-+. a) b) c)
%he fin gies stability about which ais Lateral ais 6ormal ais Longitudinal ais
1--. a) b) c)
/hat is the hori9ontal moement of the nose of the aircraft called
1-0. /hat type of drag, depends on the smoothness of the body, and surface area oer which the air flows a) arasite drag b) #orm drag c) 'kin friction drag 10. &f the nose of the aircraft is rotated about its lateral ais, what is its directional moement a) %urning to the left or right b)
/hen an aircraft stalls lift and drag increase lift increases and drag decreases lift decreases and drag increases
103. a) b) c)
/ing loading is the maimum all up weight multiplied by the total wing area the maimum all up weight diided by the total wing area the ratio of the all up weight of the aircraft to its basic weight
10. a) b) c)
n aircraft wing with an aspect ration of $F1 is proportional so that the mean chord is si times the thickness the wing span is si times the mean chord the wing area is si times the span
10". a) b) c)
>pward and outward inclination of a mainplane is termed sweep dihedral stagger
Page 22
Module 8 – Basic Aerodynamics Sample Questions
10$. a) b) c)
%he function of an aircraft fin is to proide stability about the normal ais is to proide directional control is to proide straight airflow across the rudder
10+. a) b) c)
Hoement of an aircraft about its normal ais is pitching is rolling is yawing
10-. a) b) c)
pressure of one atmosphere is e*ual to 1.+ psi 1 millibar 1 inch 8g.
100. a) b) c)
%he millibar is a unit of atmospheric temperature pressure altitude barometric pressure
2. /ith an increase in altitude under &.'.. conditions the temperature in the troposphere a) increases b) decreases c) remains constant 21. a) b) c)
/hich of the following forces act on an aircraft in leel flight Lift, thrust, and weight Lift, thrust, weight, and drag Lift, drag, thrust
22. a) b) c)
/hen an aircraft is banked, the hori9ontal component of the lift will tend to make the aircraft follow a circular path will oppose the tendency of the aircraft to follow a circular path will oppose the weight thus re*uiring more total lift in the turn
23. state a) b) c)
&f, after a disturbance, an aeroplane initially returns to its e*uilibrium it has neutral stability it has static stability and may be dynamically stable it is neutrally unstable
2. 'tability of an aircraft is a) the tendency of the aircraft to return to its original trimmed position after haing been displaced b) the ability of the aircraft to rotate about an ais c) the tendency of the aircraft to stall at low airspeeds
Page 23
Module 8 – Basic Aerodynamics Sample Questions
2". /ith reference to altimeters I#D is a) setting aerodrome atmospheric pressure so that an altimeter reads 9ero on landing and take off b) *uite fine e*uipment c) the manufacturers registered name 2$. a) b) c)
>nder the &4O JIK code there are which three settings I#D , I68 , I6D b)ID# , I68 , ID6 c) ID , I6 , IID
2+. a) b) c)
/ing loading is 5
2-. %he three aes concerned with stability of an aircraft hae a) 6ormal ais through 4 of 5. Lateral ais ! wing tip to wing tip. Longitudinal ais ! nose to tail but not through 4 of 5 b) longitudinal, lateral and normal ais all passing through aircraft centre of graity c) longitudinal ais nose to tail, lateral ais at furthest span point, normal ais through centre of pressure 20. a) b) c)
barometer indicates pressure density temperature
21. a) b) c)
&f an aircraft returns to a position of e*uilibrium it is said to be negatiely stable neutrally stable positiely stable
211. a) b) c)
%he pendulum effect on a high wing aircraft increases lateral stability decreases lateral stability has no effect on lateral stability
212. air) is a) b) c)
%he amount of water apour in the air (humidity holding capacity of the greater on a colder day, and lower on a hotter day greater on a hotter day and lower on a colder day doesnt hae a significant difference
213. a) b) c)
/eight is e*ual to olume graity mass acceleration mass graity
Page 24
Module 8 – Basic Aerodynamics Sample Questions
21. a) b) c)
&nduced rag increases with an increase in speed reduces with an increase in angle of attack increases with increase in aircraft weight
21". a) b) c)
irflow oer the upper surface of the wing generally flows towards the root flows towards the tip flows straight from leading edge to trailing edge
21$. a) b) c)
/ith an increase in aspect ratio for a gien &', induced drag will remain constant increase reduce
21+. a) b) c)
/ith increasing altitude the angle at which a wing will stall remains the same reduces increases
21-. a) b) c)
&f the density of the air is increased, the lift will increase decrease remain the same
210. a) b) c)
ll the factors that affect the lift produced by an aerofoil are angle of attack, air density, elocity, wing area angle of attack, air temperature, elocity, wing area angle of attack, elocity, wing area, aerofoil shape, air density
22. a) b) c)
wing section suitable for high speed would be thick with high camber thin with high camber thin with little or no camber
221. a) b) c)
%he induced drag of an aircraft increases with increasing speed increases if aspect ratio is increased decreases with increasing speed
222. a) b) c)
s the speed of an aircraft increases the profile drag increases decreases decreases at first then increase
223. a) b) c)
%he stagnation point on an aerofoil is the point where the suction pressure reaches a maimum the boundary layer changes from laminar to turbulent the airflow is brought completely to rest
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Module 8 – Basic Aerodynamics Sample Questions
22. fter a disturbance in pitch, an aircraft continues to oscillate at constant amplitude. &t is a) longitudinally unstable b) longitudinally neutrally stable c) laterally unstable 22". a) b) c)
On an aircraft with an all!moing tailplane nose up pitch is caused by increasing tailplane incidence decreasing tailplane incidence up moement of the trim tab
22$. a) b) c)
%he stalling of an aerofoil is affected by the airspeed angle of attack transition speed
22+. a) b) c)
/hat gies the aircraft directional stability ?ertical stabiliser 8ori9ontal stabiliser Dleators
2-. a) b) c)
%he most fuel efficient of the following types of engine is the rocket turbo!;et engine turbo!fan engine
220. a) b) c)
%he *uietest of the following types of engine is the rocket turbo!;et engine turbo!fan engine
23. a) b) c)
#orward motion of a glider is proided by the engine the weight the drag
231. a) b) c)
rofile drag consists of what drag types #orm, skin friction and interference #orm, induced and skin friction #orm, induced and interference
232. a) b) c)
n aircraft in straight and leel flight is sub;ect to 9ero load factor a load factor of 1 a load factor of M
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Module 8 – Basic Aerodynamics Sample Questions
233. spect ratio is gien by the formula a) Hean 4hord 'pan b) 'pan2 rea c) 'pan2 . Hean 4hord 23. a) b) c)
On a high wing aircraft in a turn the up going wing loses lift which has a de!stabili9ing effect the down going wing gains lift causing a stabili9ing effect the down going wing loses lift causing a de!stabili9ing effect
23". /hich condition is the actual amount of water apour in a miture of air and water a)
n aspect ratio of - means the span is - times the mean chord the mean chord is - times the span the area is - times the span
23+. a) b) c)
%he &' is taken from the e*uator is taken from " degrees latitude assumes a standard day
23-. a) b) c)
/hich will weigh the least 0- parts of dry air and 2 parts of water apour 3" parts of dry air and $" parts of water apour " parts of dry air and " parts of water apour
230. a) b) c)
high aspect ratio wing is stiffer than a low aspect ratio wing has less induced drag than a low aspect ratio wing has a higher stall angle than a low aspect ratio wing
2. %he thrust!drag couple oercomes the lift!weight couple. /hat force must the tail of the aircraft eert to maintain the aircraft in a leel attitude a) own b) >p c) 'ideways 21. a) b) c)
&nduced downwash reduces the effectie angle of attack of the wing increases the effectie angle of attack of the wing has no effect on the angle of attack of the wing
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Module 8 – Basic Aerodynamics Sample Questions
22. a) b) c)
during a turn, the stalling angle increases decreases remains the same
23. /hich is the ratio of the water apour actually present in the atmosphere to the amount that would be present if the air were saturated at the preailing temperature and pressure a) bsolute humidity b)
straight rectangular wing, without any twist, will hae greater angle of attack at the tip hae the same angle of attack at all points along the span hae less angle of attack at the tip
2". a) b) c)
&f gauge pressure on a standard day is 2" '&, the absolute pressure is 1.3 '& 3.- '& 30.+ '&
2$. a) b) c)
%he 4 of 5 moes in flight. %he most likely cause of this is moement of passengers moement of cargo consumption of fuel and oils
2+. a) b) c)
%he speed of sound in the atmosphere aries according to the fre*uency of the sound changes with a change in temperature changes with a change in pressure
2-. a) b) c)
straight rectangular wing, without any twist, will stall first at the tip stall first at the root stall e*ually along the span of the wing
20. a) b) c)
/hat is sea leel pressure 113.2 mb 112.3 mb 132.2 mb
2". /hich atmospheric conditions will cause the true landing speed of an aircraft to be the greatest a) Low temperature with low humidity b) 8igh temperature with low humidity c) 8igh temperature with high humidity
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Module 8 – Basic Aerodynamics Sample Questions
2"1. /hich condition is the actual amount of water apour in a miture of air and water a)
/hen the weight of an aircraft increases, the minimum drag speed decreases increases remains the same
2"3. /hich statement concerning heat and:or temperature is true a) %here is an inerse relationship between temperature and heat. b) %emperature is a measure of the kinetic energy of the molecules of any substance c) %emperature is a measure of the potential energy of the molecules of any substance 2". /hich is the ratio of the water apour actually present in the atmosphere to the amount that would be present if the air were saturated at the preailing temperature and pressure a) bsolute humidity b)
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Module 8 – Basic Aerodynamics Sample Questions
2"-. &f all, or a significant part of a stall strip is missing on an aeroplane wing, a likely result will be a) increased lift in the area of installation on the opposite wing at high angles of attack b) asymmetrical aileron control at low angles of attack c) asymmetrical aileron control at or near stall angles of attack 2"0. /hen a leading edge slat opens, there is a gap between the slat and the wing. %his is a) to allow it to retract back into the wing b) to allow air through to re!energi9e the boundary layer on top of the wing c) to keep the area of the wing the same 2$. n aeroplane wing is designed to produce lift resulting from relatiely a) positie air pressure below and aboe the wings surface. b) negatie air pressure below the wings surface and positie air pressure aboe the wings surface. c) positie air pressure below the wings surface and negatie air pressure aboe the wings surface 2$1. a) b) c)
spect ratio of a wing is defined as the ratio of the wingspan to the wing root s*uare of the chord to the wingspan wingspan to the mean chord
2$2. /hich of the following is true a) Lift acts at right angles to the wing chord line and weight acts ertically down b) Lift acts at right angles to the relatie airflow and weight acts ertically down c) Lift acts at right angles to the relatie air flow and weight acts at right angles to the aircraft centre line 2$3. %he temperature to which humid air must be cooled at constant pressure to become saturated is called a) dewpoint b) absolute humidity c) relatie humidity 2$. a) b) c)
%he airflow oer the upper surface of a cambered wing increases in elocity and pressure increases in elocity and reduces in pressure reduces in elocity and increases in pressure
2$". a) b) c)
/hich type of flap increases the area of the wing lain #lap #owler #lap ll flaps
Page 3"
Module 8 – Basic Aerodynamics Sample Questions
2$$. &f all, or a significant part of a stall strip is missing on an aeroplane wing, a likely result will be a) increased lift in the area of installation on the opposite wing at high angles of attack b) asymmetrical aileron control at low angles of attack c) asymmetrical aileron control at or near stall angles of attack 2$+. a) b) c)
/ith increased speed in leel flight induced drag increases profile drag increases profile drag remains constant
2$-. a) b) c)
eployment of flaps will result in a decrease in stall angle an increase in stall angle a decrease in angle of attack
2$0. n aeroplane wing is designed to produce lift resulting from relatiely a) ositie air pressure below and aboe the wings surface. b) 6egatie air pressure below the wings surface and positie air pressure aboe the wings surface. c) ositie air pressure below the wings surface and negatie air pressure aboe the wings surface. 2+. a) b) c)
%he angle of attack of an aerofoil section is the angle between the chord line and the relatie airflow underside of the wing surface and the mean airflow chord line and the centre line of the fuselage
2+1. a) b) c)
swept wing tends to stall first at the root tip centre section
2+2. a) b) c)
Nreuger #laps are normally fitted to the trailing edge of the wings the tips of the wings the leading edge of the wings
2+3. a) b) c)
spect ratio of a wing is defined as the ratio of the wingspan to the wing root. s*uare of the chord to the wingspan. wingspan to the mean chord
2+. a) b) c)
%he trailing orte on a pointed wing (taper ratio E ) is at the root at the tip e*ually all along the wing span
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Module 8 – Basic Aerodynamics Sample Questions
2+". a) b) c)
high wing aircraft will be more laterally stable than a low wing aircraft longitudinally stable than a low wing aircraft directionally stable than a low wing aircraft
2+$. wing with a ery high aspect ratio (in comparison with a low aspect ratio wing) will hae a) increased drag at high angles of attack. b) a low stall speed. c) poor control *ualities at low airspeeds. 2++. a) b) c)
%he lift cure for a delta wing is more steep than that of a high aspect ratio wing less steep than that of a high aspect ratio wing the same as that of a high aspect ratio wing
2+-. fter an aircraft has been disturbed from its straight and leel flight, it returns to its original attitude with a small amount of decreasing oscillation. %he aircraft is a) statically stable but dynamically unstable b) statically unstable but dynamically stable c) statically stable and dynamically stable 2+0. n increase in the speed at which an aerofoil passes through the air increases lift because a) the increased speed of the airflow creates a greater pressure differential between the upper and lower surfaces. b) the increased speed of the airflow creates a lesser pressure differential between the upper and lower surfaces. c) the increased elocity of the relatie wind increases the angle of attack 2-. a) b) c)
delta wing has a higher stall angle than a straight wing a lower stall angle than a straight wing the same stall angle than a straight wing
2-1. a) b) c)
%he Lift:rag ratio of a wing at the stalling angle is of a negatie alue low high
2-2. a) b) c)
%he airflow oer the upper surface of a cambered wing increases in elocity and pressure increases in elocity and reduces in pressure reduces in elocity and increases in pressure
2-3. a) b) c)
%he speed of air oer a swept wing which contributes to the lift is less than the aircraft speed more than the aircraft speed the same as the aircraft speed
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Module 8 – Basic Aerodynamics Sample Questions
2-. a) b) c)
#or a gien angle of attack induced drag is greater on a high aspect ratio wing greater towards the wing root greater on a low aspect ratio wing
2-". a) b) c)
&n straight and leel flight, the angle of attack of a swept wing is the same as the aircraft angle to the hori9ontal more than the aircraft angle to the hori9ontal less than the aircraft angle to the hori9ontal
2-$. a) b) c)
&nduced drag is neer e*ual to the profile drag is e*ual to the profile drag at the stalling speed is e*ual to the profile drag at ?md
2-+. delta wing aircraft flying at the same speed (subsonic) and angle of attack as a swept wing aircraft of similar wing area will produce a) the same lift b) more lift c) less lift 2--. a) b) c)
%he stagnation point is static pressure plus dynamic pressure static pressure minus dynamic pressure dynamic pressure only
2-0. On a swept wing aircraft, due to the aderse pressure gradient, the boundary layer on the upper surface of the wing tends to flow a) directly from leading edge to trailing edge b) towards the tip c) towards the root 20. a) b) c)
/ith increased speed in leel flight induced drag increases profile drag increases profile drag remains constant
201. a) b) c)
&f a swept wing stalls at the tips first, the aircraft will pitch nose up pitch nose down roll
202. a) b) c)
%he thickness:chord ratio of the wing is also known as aspect ratio mean chord ratio fineness ratio
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Module 8 – Basic Aerodynamics Sample Questions
203. a) b) c)
#leure of a rearward swept wing will increase the lift and hence increase the fleure decrease the lift and hence decrease the fleure increase the lift and hence decrease the fleure
20. a) b) c)
8igh spect
20". a) b) c)
'tall commencing at the root is preferred because the ailerons become ineffectie it proides the pilot with a warning of complete loss of lift it will cause the aircraft to pitch nose up
20$. a) b) c)
n aircraft flying in Jground effectK will produce more lift than a similar aircraft outside of ground effect less lift than a similar aircraft outside of ground effect the same lift as a similar aircraft outside of ground effect
20+. a) b) c)
&f the angle of attack of a wing is increased in flight, the 4 of will moe forward 4 of 5 will moe aft 4 of will moe aft
20-. a) b) c)
%he
200. a) b) c)
/hen maintaining leel flight an increase in speed will cause the 4 of to moe aft cause the 4 of to moe forward hae no affect on the position of the 4 of
3. a) b) c)
#or a cambered wing section the 9ero lift angle of attack will be 9ero degrees negatie
31. a) b) c)
ensity changes with altitude at a rate of 2kg:m3 per 1ft which changes with altitude which is constant until 11km
32. a) b) c)
irflow at subsonic speed is taken to be compressible incompressible either a or b depending on altitude
Page 34
Module 8 – Basic Aerodynamics Sample Questions
33. =ernoullis e*uation shows that a) at constant elocity the kinetic energy of the air changes with a change of height b) with a change in speed at constant height both kinetic and potential energies change c) with a change in elocity at constant height the static pressure will change 3. &f fluid flow through a enturi is said to be incompressible, the speed of the flow increases at the throat to a) maintain a constant olume flow rate b) allow for a reduction in static pressure c) allow for an increase in static pressure 3". a) b) c)
%o produce lift, an aerofoil must be asymmetrical symmetrical either a or b aboe
3$. Lift is dependent on a) the area of the wing, the density of the fluid medium, and the s*uare of the elocity b) the net area of the wing ,the density of the fluid medium and the elocity c) the frontal area of the wing, the density of the fluid medium and the elocity 3+. a) b) c)
%he maimum lift:drag ratio of a wing occurs at the angle of attack where the wing deelops its maimum lift during take off at an angle below which the wing deelops ma lift
3-. wing deelops 1,6 of lift at 1knots. ssuming the wing remains at the same angle of attack and remains at the same altitude, how much lift will it deelop at 3knots a) 0, 6 b) 0,6 c) 3,6 30. a) b) c)
%he angle of attack is related to angle of incidence always kept below 1" degrees not related to the angle of incidence
31. %he difference between the mean camber line and the chord line of an aerofoil is a) one is always straight and the other may be straight b) neither are straight c) they both may be cured
Page 35
Module 8 – Basic Aerodynamics Sample Questions
311. &f the 4 of 5 is calculated after loading as within limits for take off a) no further calculation is re*uired b) a further calculation is re*uired prior to landing to allow for fuel and oil consumption c) a further calculation is re*uired prior to landing to allow for flap deployment 312. a) b) c)
stalled aerofoil has a lift:drag ratio more than the lift:drag ratio prior to stall 9ero less than the lift:drag ratio prior to stall
313. a) b) c)
t low forward speed increased downwash reduces tailplane effectieness increased downwash increases tailplane effectieness ecessie rudder moement may cause fin to stall
31. a) b) c)
8elicopter rotor blades create lift by creating low pressure aboe the blades pushing the air down working like a screw
31". a) b) c)
On some modern aircraft a stall warning will automatically increase thrust etend outboard slats cause a pitch nose down moement
31$. a) b) c)
aboe $",- ft temperature remains constant up to 11",ft decreases by 1.0-o4 up to 11"ft increases by .33o4 up to 11"ft
31+. a) b) c)
t sea leel, &' atmospheric pressure is 1.+ '& 1.+ Npa 1 =ar
31-. a) b) c)
%he spanwise component of the airflow is greater at higher speeds less at higher speeds unaffected by speed
310. a) b) c)
wing fence increases lateral control acts as a lift dumping deice reduces spanwise flow on a swept wing thus reducing induced drag
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Module 8 – Basic Aerodynamics Sample Questions
32. a) b) c)
%he highest lift:drag ratio is greatest at low altitudes the point ;ust before the stalling angle the optimum angle of attack
321. /ith all conditions remaining the same, if the aircraft speed is haled, by what factor is the lift reduced a) 8alf b) =y a factor of c)
On a swept wing aircraft, the fineness ratio of an aerofoil is highest at the root highest at the tip e*ual throughout the span
32. a) b) c)
&' for a stall will increase with altitude decrease with altitude roughly remain the same for all altitude
32". a) b) c)
&f the radius of a turn is reduced the load factor will increase decrease remain the same
32$. a) b) c)
'treamlining will reduce form drag induced drag skin friction drag
32+. &f an aircraft has a gross weight of 3 kg and is then sub;ected to a total weight of $ kg the load factor will be a) 25 b) 35 c) 05 32-. a) b) c)
constant rate of climb is determined by weight wind speed ecess engine power
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Module 8 – Basic Aerodynamics Sample Questions
320. a) b) c)
&ce formed on the leading edge will cause the aircraft to stall at the same stall speed and o stall at a lower speed stall at a higher speed
33. /ith an aircraft in bank, the upper wing produces more drag. %o compensate a) the rudder is operated b) b)when bank angle is achieed then the ailerons are operated in the opposite direction to cause the opposite effect c) angle of attack is increased 331. true a) b) c) 332. by a) b) c)
On a high winged aircraft in a banked turn, which of the following are %he down!going wing loses lift causing a stabili9ing effect %he up!going wing loses lift causing a stabili9ing effect %he wing dihedral causes a stabili9ing effect &f an aircraft true airspeed is haled, its indicated airspeed is reduced half factor of four &t is not reduced, it is doubled
333. &f there is an increase of density, what effect would there be in aerodynamic dampening a) 6one b) ecreased c) &ncreased 33. a) b) c)
s Hach number increases, what is the effect on boundary layer =ecomes more turbulent =ecomes less turbulent ecreases in thickness
33". a) b) c)
/hen a slat is retracted it moes towards the upper leading edge of the wing towards the lower leading edge of the wing towards the center of the leading edge of the wing
33$. a) b) c)
&n a turn the up!going wing causes a de!stabili9ing effect due to increased o de!stabili9ing effect due to decreased o stabili9ing effect due to decreased o
33+. a) b) c)
%he stagnation point consists of dynamic and static air pressure static air pressure dynamic air pressure
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Module 8 – Basic Aerodynamics Sample Questions
33-. a) b) c)
uring a glide the following forces act on an aircraft lift, weight, thrust lift, drag, weight lift and weight only
330. a) b) c)
@awing is a rotation around the normal ais obtained by the eleator the lateral ais obtained by the rudder the normal ais obtained by the rudder
3. a) b) c)
&f an aileron is moed downward the stalling angle of that wing is increased the stalling angle of that wing is decreased the stalling angle is not affected but the stalling speed is decreased
31. a) b) c)
&f the wing loading of an aircraft were reduced the stalling speed would increase decrease not be affected
32. a) b) c)
s the angle of attack increases the centre of pressure will moe rearward remain static moe forward
33. a) b) c)
%he lift on a wing is increased with an increase in pressure an increase in humidity an increase in temperature
3. a) b) c)
n aircraft entering a leel turn will re*uire more lift only if there is an increase in speed only if there is an increase in angle of attack in all cases
3". a) b) c)
Lateral stability is reduced by increasing nhedral ihedral 'weepback
3$. a) b) c)
ulling the control column and rotating to the left causes eleator down, left aileron down eleator up, left aileron up eleator down, left aileron up
3+. a) b) c)
9imuth stability is dependent on dihedral tailplane keel and fin
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Module 8 – Basic Aerodynamics Sample Questions
3-. a) b) c)
&f the aircraft is slipping in turn the bank angle is too great the bank angle is too small the nose of the aircraft is too low
30. a) b) c)
&n normal flight conditions, an increase in aircraft speed causes the nose of the aircraft to drop causes the nose of the aircraft to lift the nose remains in the same position
3". n aircraft sideslips. /hat helps to restore the aircraft a) #in gies rolling moement b) ihedral causes the aircraft to roll straight and the fin increases the yaw rate c) %ailplane 3"1. a) b) c)
#or an aircraft climbing at a constant &' the Hach number will increase decrease remain constant
3"2. a) b) c)
%he airflow behind a normal shockwae will always be subsonic and in the same direction as the original airflow always be supersonic and in the same direction as the original airflow always be subsonic and deflected from the direction of the original airflow
3"3. a) b) c)
'weepback of the wings will not affect lateral stability increase lateral stability at high speeds only increase lateral stability at all speeds
3". a) b) c)
/ith the flaps lowered, the stalling speed will increase decrease remain the same
3"". /hen flying close to the stall speed a pilot applies left rudder the aircraft will a) pitch nose up b) roll to the left c) stall the left wing 3"$. /hen an aircraft is in a bank, the upper wing produces more drag. %o compensate a) the rudder is operated b) when bank angle is achieed then the ailerons are operated in the opposite direction to cause the opposite effect c) angle of attack is increased (pitch up)
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