Part 66 Aerodynamics

Module 8

Module 8

 Aerodynamics

 Aerodynamics

1. If the If the wing tips wing tips stall before stall before the rthe root on oot on a a swept wing swept wing aircraft, the aircraft, the aircraft willaircraft will a) roll

a) roll

b) pitch nose up b) pitch nose up c)

c) pitch pitch nose nose downdown

2) ngle of attac! . 2) ngle of attac! .

a)

a) increases with an increases with an increased angle of increased angle of incidence "angle of incidence "angle of attac!)attac!) b) decreases with an increase in angle of incidence "angle of attac!) b) decreases with an increase in angle of incidence "angle of attac!) c)

c) does does not not change change with with a a change change in in angle angle of of incidence "angle incidence "angle of of attac!)attac!)

#.

#. $n $n a a straight straight wing wing aircraft, aircraft, stall stall commences commences at at thethe a) root on a high thic!ness ratio wing

a) root on a high thic!ness ratio wing b) tip on a high thic!ness ratio wing b) tip on a high thic!ness ratio wing c)

c) tip tip on on a a low low thic!ness thic!ness ratio ratio wingwing

%.

%. $n $n a a high high wing wing aircraft aircraft in in a a turnturn a)

a) the up-going wing the up-going wing loses lift causing loses lift causing a de-stabilising e&ecta de-stabilising e&ect b) the down-going wing gains lift causing a stabilising e&ect b) the down-going wing gains lift causing a stabilising e&ect c)

c) the the down-going down-going wing wing loses loses lift lift causing causing a a de-stabilisde-stabilising ing e&ecte&ect

'.

c)

c) is is the the same same as as the the lift lift on on a a high high aspect aspect ratio ratio wingwing

.

. *he *he I+I+ a)

a) is ta!en is ta!en from the from the euatoreuator

b) is ta!en from %' degrees latitude b) is ta!en from %' degrees latitude c)

c) assumes assumes a a standard standard dada

/.

/. s s altitude altitude increases, increases, pressurepressure a)

a) decreasdecreases at cones at constant ratestant rate b) increases exponentiall b) increases exponentiall c)

c) decreases decreases exponentiallexponentiall

0.

0. *he *he thrust-drag thrust-drag couple couple oercomes oercomes the the lift-weight lift-weight couple. couple. hat hat direction direction of of force force isis reuired to be produced b the tail of the aircraft to maintain straight and leel 3ight reuired to be produced b the tail of the aircraft to maintain straight and leel 3ight

a) upwards a) upwards b) downwards b) downwards c) sidewas c) sidewas 4.

4. hen hen the prthe pressure essure is is half of half of that at that at sea leel, sea leel, what is what is the altitudethe altitude a) a) 12,555 12,555 ftft b) 0,555 ft b) 0,555 ft c) c) 10,555 10,555 ftft 15.

15. 6uring a 6uring a turn, turn, the the stalling stalling angleangle a) increases

a) increases b) decreases b) decreases c)

ans819 7 b; ans819 7 b; ans829 7 a; ans829 7 a; ans8#9 7 a; ans8#9 7 a; ans8%9 7 b; ans8%9 7 b; ans8'9 7 b; ans8'9 7 b; ans89 7 b; ans89 7 b; ans8/9 7 c; ans8/9 7 c; ans809 7 a; ans809 7 a; ans849 7 c; ans849 7 c; ans8159 7 c; ans8159 7 c;

explain8197<icture a side iew of a swept wing aircraft. *he wing tips are behind the wing explain8197<icture a side iew of a swept wing aircraft. *he wing tips are behind the wing root. *hin!, therefore, of the lift on the wing tip holding the tail up.

root. *hin!, therefore, of the lift on the wing tip holding the tail up. =ose the lift on the tips and=ose the lift on the tips and what will happen;

what will happen;

explain8297*his uestion is much easier than

explain8297*his uestion is much easier than it loo!s at it loo!s at >rst read. >rst read. ll wing ll wing tpes "straight,tpes "straight, swept, delta etc.) increase lift with an increase in angle of attac! "up to the stall angle).; swept, delta etc.) increase lift with an increase in angle of attac! "up to the stall angle).; explain8#97*hic!

explain8#97*hic!ness ratio is ness ratio is a red a red herring. herring. ?ut ou ?ut ou must learn must learn the stall the stall points for points for di&erentdi&erent tpes of wing platforms - the di&er greatl.;

tpes of wing platforms - the di&er greatl.;

explain8%97*he down-going wing has an increased lift due to an increas in angle of attac! explain8%97*he down-going wing has an increased lift due to an increas in angle of attac! "due to the up

"due to the up 3ow of air). 3ow of air). *his opposes the roll which *his opposes the roll which is a stabili@ing e&ect.;is a stabili@ing e&ect.;

explain8'97 long slender wing "i.e. high spect Aatio) has a higher lift than a short stubb explain8'97 long slender wing "i.e. high spect Aatio) has a higher lift than a short stubb wing "low spect Aatio).

wing "low spect Aatio).  delta wing is about as low spect Aatio as ou  delta wing is about as low spect Aatio as ou can get "about 1:1can get "about 1:1 for concord for example).;

for concord for example).;

explain897*he properties of a standard da are related to sea leel at latitude %' degrees explain897*he properties of a standard da are related to sea leel at latitude %' degrees with absolutel dr air.;

with absolutel dr air.;

explain8/97<ressure decreases -

explain8/97<ressure decreases - sureB sureB ?ut the ?ut the rate of rate of decrease reduces with decrease reduces with altitude. altitude. tt 10555 ft, half the pressure is lost alread, and there is still another %5,555ft or so to go; 10555 ft, half the pressure is lost alread, and there is still another %5,555ft or so to go; explain8097$n most aircraft, the thrust-drag couple produces a nose up pitch moment "thin! explain8097$n most aircraft, the thrust-drag couple produces a nose up pitch moment "thin! of how low the thrust line is on a

of how low the thrust line is on a ?oeing). ?oeing). It is balanced b the Centre of =ift being It is balanced b the Centre of =ift being behind thebehind the CD.

CD. +o to corr+o to correct a nose up ect a nose up moment, what force do ou moment, what force do ou need at the tail;need at the tail;

explain8497ust one of those facts ou hae to learn - but it is uoted in Fust about eer text explain8497ust one of those facts ou hae to learn - but it is uoted in Fust about eer text boo! on the C

boo! on the C readinreading list.;g list.;

explain815976o not get cofused between stalling angle

explain815976o not get cofused between stalling angle and stalling speed. and stalling speed. In a In a turn theturn the ertical component of lift is less, so to compensate the pilot must increase speed, but the ertical component of lift is less, so to compensate the pilot must increase speed, but the stalling angle is a >xed uantit for an aerofoil, regardless of an other factor.;

777777777777

Exam Number:-2. Exam Number:-2.

1.

1. If gauge If gauge pressure on pressure on a standard a standard da at da at sea leel sea leel is 2' is 2' <+I, the <+I, the absolute pressure absolute pressure isis a) a) 15.# 15.# <+I<+I b) %#.0 <+I b) %#.0 <+I c) c) #4./ #4./ <+I<+I 2.

2. *he *he C C of of D D moes moes in in 3ight. 3ight. *he *he most most li!el li!el cause cause of of this this isis a)

a) moement moement of pasof passengerssengers

b) moement of the centre of pressure b) moement of the centre of pressure c)

c) consumption consumption of of fuel fuel and and oilsoils

#.

#. *he *he C C of of < < is is the the point point wherewhere a)

a) all the forces all the forces on an on an aircraft actaircraft act b) the three axis of rotation meet b) the three axis of rotation meet c)

c) the the lift lift can can be be said said to to actact

%.

%. *he *he three three axis axis of of an an aircraft aircraft act act through through thethe a)

a) C C of of DD b) C of < b) C of < c)

c) stagnation stagnation pointpoint

'.

'. <ressure <ressure decreasesdecreases a)

a) proportionall with proportionall with a decra decreases in eases in temperaturetemperature b) inersel proportional to temperature

b) inersel proportional to temperature c)

c) <ressure <ressure and and temperature temperature are are not not relatedrelated

.

a)

a) reducesreduces b) increases b) increases c)

c) remains remains the the samesame

/.

/. hat hat is is sea sea leel leel pressurepressure a) a) 151#.2 151#.2 mbmb b) 1512.# mb b) 1512.# mb c) c) 15#2.2 15#2.2 mbmb 0.

0. hen hen the the weight weight of of an an aircraft aircraft increases, the increases, the minimum minimum drag drag speedspeed a) decreases

a) decreases b) increases b) increases c)

c) remains remains the the samesame

4.

4. n n aircraft aircraft will will haehae a)

a) less gliding distance if less gliding distance if it has more it has more paloadpaload b) more gliding distance if it has more paload b) more gliding distance if it has more paload c)

c) the the same same gliding gliding distance distance if if it it has has more more paloadpaload

15.

15. hen hen an an aircraft aircraft experiences experiences induced induced dragdrag a)

a) air 3ows under the wing spanwise towards the tip and on top of air 3ows under the wing spanwise towards the tip and on top of the wing spanwisethe wing spanwise towards the root

towards the root

b) air 3ows under the wing spanwise towards the root and on top of the wing spanwise b) air 3ows under the wing spanwise towards the root and on top of the wing spanwise towards the tip

towards the tip c)

c) Neither Neither a) a) or or b) b) since since induced induced drag drag does does not not caused caused b b spanwise spanwise 3ow3ow 777777777777

2 ans819 7 c; ans829 7 c; ans8#9 7 c; ans8%9 7 a; ans8'9 7 b; ans89 7 b; ans8/9 7 a; ans809 7 b; ans849 7 c; ans8159 7 a;

explain8197bsolute pressure 7 gauge pressure plus atmospheric pressure. tmospheric pressure at seal leel 7 1%./ <+I.;

explain8297Gnless the fuel tan! is right on the aircraft Cof D, the consumption of fuel will alwas cause a shift in Cof D.;

explain8#97ust a de>nition; explain8%97nother de>nitionB;

explain8'97s temperature decreases, pressure increases - therefore the are inersel proportional.;

explain897s air gets colder it gets denser. =ift increases "remember the lift euation has densit) and the engines produce more thrust - so it can climb higher.;

explain8/97=earn the I+ sea leel uantities, in all units.;

explain8097+!etch the drag - speed cure, with induced, pro>le and total drag. s aircraft weight increases, it must produce more lift to support it. Hore lift 7 more induced drag. Now s!etch the induced drag cure higher, and see where the intersection with pro>le drag moes to.;

explain8497*his ma surprise ou.  glider conerts potential energ "ie height) into !inetic energ "ie speed) and thus lift. Hore weight 7 more speed 7 more lift. *he glide angles of a hea glider is exactl the same as a light glider. "?ut the increased speed means it coers the distance faster).;

explain81597*he high pressure under the wing 3ows around the tip to the low pressure on top of the wing. *he resulting ortex is what causes induced drag. +ince air is iscous it drags the

air underneath the wing towards the tip, and pushes the air on top of the wing towards the root.;

Exam Number:-#.

---1. t stall, the wingtip stagnation point

a) moes toward the lower surface of the wing b) moes toward the upper surface of the wing c) doesnt moe

2. Jow does I+ at the point of stall ar with height a) It is practicall constant

b) It increases c) It decreases

#. *he rigging angle of incidence of an eleator is

a) the angle between the mean chord line and the hori@ontal in the rigging position b) the angle between the bottom surface of the eleator and the hori@ontal in the rigging position

c) the angle between the bottom surface of the eleator and the longitudinal datum

%. hat is the lapse rate with regard to temperature a) 1.40oC per 1555 ft

b) 1.40o( per 1555 ft c) %oC per 1555 ft

'. hat happens to load factor as ou decrease turn radius a) It increases

b) It decreases

. If ou steepen the angle of a ban!ed turn without increasing airspeed or angle of attac!, what will the aircraft do

a) It will remain at the same height

b) It will sideslip with attendant loss of height c) It will stall

/. n aircraft wing tends to stall >rst at

a) the tip due to a higher ratio thic!nessKchord b) the tip due to a lower ratio thic!nessKchord c) the root due to a higher ratio thic!nessKchord

0. 6ihedral wings combat instabilit in a) pitch

b) aw c) sideslip

4. *o stop aircraft decreasing in height during a sideslip, the pilot can a) adance the throttle

b) pull bac! on the control column c) adFust the rudder position

15. hat control surface moements will ma!e an aircraft >tted with rudderators aw to the left

a) =eft rudderator lowered, right rudderator raised b) Aight rudderator lowered, left rudderator raised c) ?oth rudderators raised

ans819 7 a; ans829 7 a; ans8#9 7 a; ans8%9 7 a; ans8'9 7 b; ans89 7 b; ans8/9 7 c; ans809 7 c; ans849 7 a; ans8159 7 a;

explain8197t stall the angle of attac! is high "all along the wing) is positioned towards the lower surface of the wing..;

explain8297*he true airspeed at which an aircraft stalls increases with height due to a drop in densit. Joweer the Indicated irspeed decreases with height due to the same drop in densit. *herefore there is practicall no change in stall speed with height..;

explain8#97*he angle of incidence of an surface is measured from the mean chord line.; explain8%97*he lapse rate is approximatel 2 degrees Centigrate per 1555 feet.;

explain8'97+ince the load factor increases in a turn, if ou decrease the turn rate the load factor decreases.;

explain897Increasing the angle of a ban!ed turn without increasing the airspeed or angle of attac!, the aircraft will sideslip and lose height.;

explain8/97*he boundar laer separates at a lower angle of attac! with a higher thic!nessKchord atio. *herefore it will stall >rst at the root..;

explain8097s the aircraft sideslips, there is a greater angle of attac! on the lower wing which increases lift, straightens the aircraft and stops the sideslip.;

explain84976uring a turn, extra speed is reuired to stop the aircraft sideslipping and decreasing in height.;

explain81597*o ma!e the aircraft aw to the left, the left rudderator is lowered, the right rudderator is raised.;

Exam Number:-%.

---1. hen a leading edge slat opens, there is a gap between the slat and the wing. *his is a) to allow it to retract bac! into the wing

b) to allow air through to re-energi@e the boundar laer on top of the wing c) to !eep the area of the wing the same

2. hich of the following is true

a) =ift acts at right angles to the wing chord line and weight acts erticall down b) =ift acts at right angles to the relatie air3ow and weight acts erticall down

c) =ift acts at right angles to the relatie air 3ow and weight acts at right angles to the aircraft centre line

#. If the wing tips stall before the root on a swept wing aircraft, the aircraft will a) roll

b) pitch nose up c) pitch nose down

%. =ift on a delta wing aircraft

a) increases with an increased angle of incidence "angle of attac!) b) decreases with an increase in angle of incidence "angle of attac!)

c) does not change with a change in angle of incidence "angle of attac!)

'. $n a straight wing aircraft, stall commences at the a) root on a high thic!ness ratio wing

b) tip on a high thic!ness ratio wing c) tip on a low thic!ness ratio wing

a) the up-going wing loses lift causing a de-stabili@ing e&ect b) the down-going wing gains lift causing a stabili@ing e&ect c) the down-going wing loses lift causing a de-stabili@ing e&ect

/. (or the same angle of attac!, 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

0. *he I+

a) is ta!en from the euator

b) is ta!en from %' degrees latitude c) assumes a standard da

4. s altitude increases, pressure a) decreases at constant rate b) increases exponentiall c) decreases exponentiall

15. *he thrust-drag couple oercomes the lift-weight couple. hat direction of force is reuired to be produced b the tail of the aircraft to maintain straight and leel 3ight

a) Gpwards b) 6ownwards c) +idewas

ans819 7 b; ans829 7 b; ans8#9 7 b; ans8%9 7 a; ans8'9 7 a; ans89 7 b; ans8/9 7 b; ans809 7 b; ans849 7 c; ans8159 7 a;

explain8197*he gap between the wing and the slat is to allow air from the lower surface through to the upper surface to re-nergise it at high angles of attac!.;

explain8297=ift acts at right angles to the relatie air3ow and weight acts erticall down.; explain8#97If the tips of a swept wing aircraft stall, the lift still acting at the roots, will pull the aircraft up..;

explain8%97=ift "on an tpe of wing) increases with an increased angle of attac!.;

explain8'97+tall commences on a straight wing at the root "on an thic!ness ratio wing).; explain897*he down going wing gains lift due to the upl3ow, which stops the aircraft ban!ing. *his is the basic mechanism of dnamic stabilit.;

explain8/97(or the same angle of attac!, the lift on a delta wing is lower than the lift on a delta wing.;

explain8097*he I+ is ta!en from %' degrees latitude as an aerage of the orldLs atmospheric data.;

explain8497s altitude increases, pressure decreases exponentiall. +ince pressure is gien b densit x grait x height, both densit and height decreases "that is, height aboe the point ou are measuring) so the decrease in pressure is exponential;

explain81597+ince the thrust-drag couple is usuall a nose-up couple "on low engined aircraft) then if the thrust-drag couple oercomes the lift weight couple, the aircraft will pitch nose-up.  *he tail of the aircraft would hae to produce an upward force to counteract this..;

Exam Number:-'.

---1. hen the pressure is half of that at sea leel, what is the altitude a) 12,555 ft

b) 0,555 ft c) 10,555 ft

2. 6uring a turn, the stalling angle a) increases

b) decreases

c) remains the same

#. *he ertical >n of a single engined aircraft is

a) parallel with both the longitudinal axis and ertical axis b) parallel with the longitudinal axis but not the ertical axis c) parallel with the ertical axis but not the longitudinal axis

%. ircraft 3ing in the transonic range most often utili@e a) sweptbac! wings

b) adanced supercritical airfoils c) high wings

'. hich tpe of 3ap changes the area of the wing a) (owler

b) +plit c) +lotted

. (orward swept wings tend to stall at the root >rst so the aircraft retains lateral control, so wh are the neer 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 the destro it

/. hat happens to air 3owing at the speed of sound when it enters a conerging duct a) Melocit decreases, pressure and densit increase

b) Melocit increases, pressure and densit decreases c) Melocit, pressure and densit increase

0. s the angle of attac! of an airfoil increases the centre of pressure a) moes forward

b) moes aft

c) remains stationar

4. n aircraft, which is longitudinall stable, will tend to return to leel 3ight after a moement about which axis

a) <itch b) Aoll c) aw

15. Mapour trails from the wingtips of an aircraft in 3ight are caused b

a) low pressure aboe the wing and high pressure below the wing causing ortices b) high pressure aboe the wing and low pressure below the wing causing ortices

c) low pressure aboe the wing and high pressure below the wing causing a temperature rise

ans819 7 c; ans829 7 c; ans8#9 7 a; ans8%9 7 a; ans8'9 7 a; ans89 7 c; ans8/9 7 c; ans809 7 a; ans849 7 a; ans8159 7 a;

explain8197t 10555 feet the pressure is half of that at sea leel.;

explain82976uring a turn the stalling angle does not change. *he stalling angle neer changes proiding the wing section shape "C=) does not change. 6o not get confused with stalling +<EE6 which increases as turn rate increases.;

explain8#97*he ertical >n is parallel with the longitudinal axis "when iewed from aboe) and parallel with the ertical axis "when iewed from the front).;

explain8%97ircraft which 3 in the transonic range most often use swept bac! wings.; explain8'97*he fowler 3ap changes the area of the wing because it slides bac!wards as well as downwards.;

explain897(orward swept wings are !nown as Lstructurall diergentL. *his means when the 3ex upwards, the present more of their underside to the air3ow which causes them to 3ex up een more - untill the brea! o&.;

explain8/97ir at the speed of sound will increase in elocit and due to the compressibilit e&ect, will increase in pressure and densit also.;

explain8097s the angle of attac! of the aerofoil increases, the centre of pressure moes forward.;

explain8497=ongitudinal stabilit is around the pitch axis.;

explain81597Mapour trails are caused b wing tip ortices which are caused b low pressure aboe the wing and high pressure below the wing.;

Exam Number:-.

---1. Mortex generators on the wing are most e&ectie at a) high speed

b) low speed

c) high angles of attac!

2. *he chord line of a wing is a line that runs from

a) the centre of the leading edge of the wing to the trailing edge b) half wa between the upper and lower surface of the wing c) one wing tip to the other wing tip

#. *he angle of incidence of a wing is an angle formed b lines a) parallel to the chord line and longitudinal axis

b) parallel to the chord line and the lateral axis c) parallel to the chord line and the ertical axis

%. *he centre of pressure of an aerofoil is located

a) #5 - %5O of the chord line bac! from the leading edge b) #5 - %5O of the chord line forward of the leading edge c) '5O of the chord line bac! from the leading edge

'. Compressibilit e&ect is

a) drag associated with the form of an aircraft

b) drag associated with the friction of the air oer the surface of the aircraft

c) the increase in total drag of an airfoil in transonic 3ight due to the formation of shoc! waes

a) fences

b) ortex generators c) wing slots

/. +tall strips are alwas a) made of metal

b) on the leading edge of a wing c) >tted forward of the ailerons

0. +tall strips

a) cause the wing root to stall b) cause the wing tip to stall

c) cause the wings to stall smmetricall

4. 6ue to the interference of the air3ow on a high wing aircraft between the fuselage and the wings, the lateral stabilit of the aircraft in a gust 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

15. +lats

a) reduce the stall speed

b) reduce the tendenc of the aircraft to aw c) decrease the aerofoil drag at high speeds

ans819 7 c; ans829 7 a; ans8#9 7 a; ans8%9 7 a; ans8'9 7 c; ans89 7 b; ans8/9 7 b; ans809 7 a; ans849 7 b; ans8159 7 a;

explain8197Mortex generators on the wing are designed to re-energise the boundar laer at high angles of attac! and help preent separation of the air3ow;

explain8297*he chord line is a +*AIDJ* line which goes from the leading edge of the wing to the trailing edge of the wing.;

explain8#97*he angle of incidence is the angle between the chord line and the longitudinal axis.;

explain8%97*he centre of pressure is positioned roughl #5 - %5 O of the chord line ?CP from the leading edge.;

explain8'97Compressibilit e&ect is associated with an increase in drag during the transonic 3ight stage.;

explain897t high angles of attac!, the air3ow oer the ailerons can be separated from the surface. Mortex generators, positioned Fust forward of the ailerons, are designed to re-energise the boundar laer and help to preent this separation. *his ma!es the ailerons more e&ectie at high angles of attac!.;

explain8/97+tall strips are >tted at the leading edge of the wing to ensure that the root of the wing stalls before the tips.;

explain8097+tall strips are >tted at the leading edge of the wing to ensure that the root of the wing stalls before the tips.;

explain8497In a gust, the aircraft ma be forced to roll and sideslip awa from the gust. In such a slideslip, the fuselage shields the upper wing from some of the air3ow. *his reduces the lift on the upper wing which drops and opposes the gust.;

Exam Number:-/.

---1. hat is the temperature lapse rate for aircraft 3ing below #,555 feet altitude

a) 1QC per 1555 feet b) #QC per 1555 feet c) 2QC per 1555 feet

2. (or a pressure of 2'lbsKinR at sea leel, what is the absolute pressure a) #4./ lbsKinR

b) %4./ lbsKinR c) 15.# lbsKin

#. n aircraft ban!s into a turn. No change is made to the airspeed or angle of attac!. 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 aws and slows down

%. *he relationship between induced drag and airspeed is a) directl proportional to the suare of the speed

b) inersel proportional to the suare of the speed c) directl proportional to speed

'. hat is the de>nition of ngle of Incidence

a) *he angle the underside of the mainplane or tailplane ma!es with the hori@ontal

. hat is ?oundar =aer

a) +eparated laer of air forming a boundar at the leading edge b) *urbulent air moing from the leading edge to trailing edge

c) +luggish low energ air that stic!s to the wing surface and graduall gets faster until it  Foins the free stream 3ow of air

/. *he normal axis of an aircraft passes through a) the centre of grait

b) a point at the center of the wings c) at the centre of pressure

0. $n a high winged aircraft, what e&ect will the fuselage hae on the up-going wing

a) *he up-going wing will hae a decrease in angle of attac! and therefore a decrease in lift b) *he down-going will hae a decrease in angle of attac! and therefore a decrease in lift c) *he up-going wing will hae an increase in angle of attac! and therefore a decrease in lift

4. hat is the collectie term for the >n and rudder and other surfaces aft of the centre of grait that helps directional stabilit

a) E&ectie !eel surface b) Empennage

c) (uselage surfaces

15. *emperature aboe #,555 feet will a) decrease exponentiall

b) remain constant

c) increase exponentiall

ans819 7 c; ans829 7 a; ans8#9 7 a; ans8%9 7 b; ans8'9 7 c; ans89 7 c; ans8/9 7 a; ans809 7 a; ans849 7 a; ans8159 7 b;

explain8197*emperature lapse rate up to #,555 feet "the tropopause) is approximatel 2 degress centigrade per 1555 feet. boe the tropopause it is constant.;

explain8297bsolute pressure 7 gauge pressure S atmospheric pressure. tmospheric pressure 7 1%./ psi.;

explain8#97hen an aircraft ban!s and turns, some of the lift ector is used to turn the aircraft, therefore the aircraft will lose altitude.;

explain8%97Induced drag decreases proportionall with the suare of the speed.;

explain8'97ngle of incidence is the Lwing setting angleL. *hat is the angle of the chord of the mainplane or tailplane with the hori@ontal - or aircraft centre line when in the rigging position.; explain897*he boundar laer is the laer of air immediatel in contact with the aircraft s!in which is slowed down b the s!in friction.;

explain8/97ll the axis of the aircraft "normal, longitudinal and lateral) pass through the centre of grait.;

explain8097*he up-going wing of an aircraft in a turn or ban! has a down-3ow of air due to its moement. It therefore has a decrease in angle of attac! and a decrease in lift. *his is the basic mechanism of dnamic stabilit.;

explain8497ll the side surfaces aft of the centre of grait which aid the directional stabilit are collectiel called the E((EC*IME PEE= +GA(CE.;

explain81597*emperature lapse rate up to #,555 feet "the tropopause) is approximatel 2 degress centigrade per 1555 feet. boe the tropopause it is constant.;

Exam Number:-0.

---1.  decrease in incidence toward the wing tip ma be proided to

a) preent aderse aw in a turn b) preent spanwise 3ow in maneuers

c) retain lateral control e&ectieness at high angles of attac!

2. *he angle of attac! which gies the best =K6 ratio

a) decreases with a decrease in densit b) in una&ected b densit changes c) increases with a decrease in densit

#. (or a gien aerofoil production lift, where < 7 pressure and M 7 elocit:

a) <1 is greater than <2, and M1 is greater than M2 b) <1 is less than <2 and M1 is greater than M2 c) <1 is greater than <2, and M1 is less than M2

%. =ow wing loading

a) increases stalling speed, landing speed and landing run b) increases lift, stalling speed and maneuerabilit

c) decreases stalling speed, landing speed and landing run

'. 6ue to the change in downwash on an untapered wing "i.e. one of constant chord length) it will

a) not proide an damping e&ect when rolling b) tend to stall >rst at the root

c) not su&er aderse aw e&ects when turning

. *rue stalling speed of an aircraft increases with altitude a) because reduced temperature causes compressibilit e&ect b) because air densit is reduced

c) because humidit is increased and this increases drag

/. s a general rule, if the aerodnamic angle of incidence "angle of attac!) of an aerofoil is slightl increased, the centre of pressure will

a) neer moe

b) moe forward towards the leading edge c) moe towards the tip

0. *he wing setting angle is commonl !nown as a) angle of incidence

b) angle of attac! c) angle of dihedral

4. $n a er humid da, an aircraft ta!ing o& would reuire a) a shorter ta!e o& run

b) a longer ta!e o& run

a) 1/' mph b) 2/' mph c) 255 mph

ans819 7 c; ans829 7 b; ans8#9 7 c; ans8%9 7 c; ans8'9 7 b; ans89 7 b; ans8/9 7 b; ans809 7 a; ans849 7 b; ans8159 7 b;

explain8197 decrease in incidence towards the wingtip "!nown as washout) causes the wing root to stall before the wing tip. +o, een after the wing roots hae stalled, the wing tips are still 3ing and full aileron control is proided.;

explain8297+ince the lift formula both contain densit, =K6 is una&ected with a change in densit.;

explain8#97?ernoulliLs principle applies.;

explain8%97ing loading is aircraft weight diided b wing area, therefore an aircraft with a low wing loading will reuire less landing speed, less landing run and hae a decreased stalling speed.;

explain8'97*he change in downwash is referring to downwash which causes the root of the wing to stall before the tip.;

explain897+ince lift proided b the wing reduces with densit, the stalling speed increases with altitude due to the decrease in altitude with densit.;

explain8/97s the angle of attac! increases the centre of pressure moes towards the leading edge.;

explain8097*he wing setting angle is commonl !nown as the Langle of incidenceL.;

explain8497+ince water apour wighs less than dr air, and it displaces dr air, the densit on a humid da is less, and an aircraft reuires a longer ta!e-o& run.;

Exam Number:-4.

---1. hen does the angle of incidence change

a) hen the aircraft attitude changes

b) hen the aircraft is ascending or descending c) It neer changes

2. s the angle of attac! decreases, what happens to the centre of pressure

a) It moes forward b) It moes rearwards

c) Centre of pressure is not a&ected b angle of attac! decrease

#.  decrease in pressure oer the upper surface of a wing or aerofoil is responsible for

a) approximatel 2K# "two thirds) of the lift obtained b) approximatel 1K# "one third) of the lift obtained c) approximatel 1K2 "one half) of the lift obtained

%. hich of the four forces act on an aircraft

a) =ift, grait, thrust and drag b) eight, grait, thrust and drag c) =ift, weight, grait and drag

a) <arasite drag b) Induced drag c) Interference drag

. Correcting for a disturbance which has caused a rolling motion about the longitudinal axis would re-establish which of the following

a) =ateral stabilit b) 6irectional stabilit c) =ongitudinal stabilit

/. *he laer of air oer the surface of an aerofoil which is slower moing, in relation to the rest of the air3ow, is !nown as

a) camber laer b) boundar laer c) none of the aboe

0. hat is a controlling factor of turbulence and s!in friction a) spect ratio

b) (ineness ratio

c) Counter sun! riets used on s!in exterior

4. Changes in aircraft weight

a) will not a&ect total drag since it is dependant onl upon speed

b) cause corresponding changes in total drag due to the associated lift change c) will onl a&ect total drag if the lift is !ept constant

b) be una&ected b aircraft weight changes since it is dependant upon the angle of attac! c) onl change if the H*H were changed

ans819 7 c; ans829 7 b; ans8#9 7 a; ans8%9 7 a; ans8'9 7 b; ans89 7 a; ans8/9 7 b; ans809 7 c; ans849 7 b; ans8159 7 a;

explain8197*he angle of incidence is the angle at which the wing is LsetL into the fuselage. It neer changes.;

explain8297*he centre of pressure moes ($AA6+ with an INCAE+E in angle of attac!.  *herefore it moes AEAA6+ with a 6ECAE+E in angle of attac!.;

explain8#97=oo! at a diagram of the lift distributions on the top and bottom surfaces of a wing. 2K#rds of the lift is proided b the top surface.;

explain8%97*he four forces on an aircaft are lift, weight "grait), thrust and drag.;

explain8'97s densit decreases with altitude, the lift must be compensated b increasing speed. Induced drag increases with the suare of the speed, therefore induced drag increases with altitude.;

explain897*he aircraftLs response to rolling is lateral stabilit.;

explain8/97*he boundar is the laer of air in immediate contact with the s!in of the aircraft which is slowed down b s!in friction.;

explain8097Countersun! riets reduce s!in friction and turbulence.;

explain8497 change in aircraft weight will reuire a change in lift. Increasing aircraft lift increases aircraft drag "lift dependant drag). *otal drag is induced drag plus parasite drag.; explain81597ith an increase in aircraft weight, the aircraft must 3 with a greater angle of attac!. *herefore it will stall at a higher speed.;

Exam Number:-15.

---1. In a ban! and turn

a) extra lift is not reuired

b) extra lift is not reuired if thrust is increased c) extra lift is reuired

2. *o maintain straight and leel 3ight on the aeroplane shown, with a decrease in tail-plane download the mainplane lift would hae to

a) remain constant b) decrease

c) increase

#. *o achiee the maximum distance in a glide, the recommended air speed is

a) as close to the stall as practical b) as high as possible with MNE

c) the speed where the =K6 ratio is maximum

%. If the C of D is aft of the Centre of <ressure

a) changes in lift produce a pitching moment which acts to increase the change in lift b) when the aircraft sideslips, the C of D causes the nose to turn into the sideslip thus appling a restoring moment

'.

'. <orpoising <orpoising is is an an oscillator oscillator motion motion in in thethe

a)

a) pitch pitch planeplane b) roll plane b) roll plane c)

c) aw aw planeplane

.

. 6irectional 6irectional stabilit stabilit is is maintainedmaintained

a)

a) b the b the mainplanes, and controlled b mainplanes, and controlled b the aileronsthe ailerons b) b the tailplane, and controlled b the eleators b) b the tailplane, and controlled b the eleators c)

c) b b the the !eel !eel surface surface and and >n, >n, and and controlled controlled b b the the rudderrudder

/.

/. 6ue 6ue to to the the interference e&ects interference e&ects of of the the fuselage, when fuselage, when a a high high wing wing aeroplane sideslipsaeroplane sideslips

a)

a) the accompaning rolling the accompaning rolling due to due to !eel surface area !eel surface area is destabili@ingis destabili@ing b) the accompaning lift changes on the wings produces a stabili@ing e&ect b) the accompaning lift changes on the wings produces a stabili@ing e&ect c)

c) the the accompaning accompaning rolling rolling due due to to the the >n >n is is destabili@ingdestabili@ing

0.

0. *he *he power power reuired reuired in in a a hori@ontal hori@ontal turnturn a)

a) is greateis greater than that for leel 3ighr than that for leel 3ight at the same airspeedt at the same airspeed b) must be the same as that for leel 3ight at

b) must be the same as that for leel 3ight at the same airspeedthe same airspeed c)

c) is is less less than than that that for for leel leel 3ight 3ight at at the the same same airspeedairspeed

4.

4.   wing wing mounted mounted stall stall sensing sensing deice deice is is locatedlocated a)

a) usuall on usuall on the under the under surfacesurface b) alwas at the wing tip

b) alwas at the wing tip c)

a)

a) thrust, thrust, drag, drag, lift lift and and weight weight act act on on the the aircraftaircraft b) weight, lift and drag act on the aircraft

b) weight, lift and drag act on the aircraft c)

c) weight weight and and drag drag onl onl act act on on the the aircraftaircraft 777777777777

ans819 7 c; ans819 7 c; ans829 7 b; ans829 7 b; ans8#9 7 c; ans8#9 7 c; ans8%9 7 a; ans8%9 7 a; ans8'9 7 a; ans8'9 7 a; ans89 7 c; ans89 7 c; ans8/9 7 b; ans8/9 7 b; ans809 7 a; ans809 7 a; ans849 7 a; ans849 7 a; ans8159 7 b; ans8159 7 b;

explain8197In a ban! and turn, extra lift is reuired and this is usuall proided b increasing explain8197In a ban! and turn, extra lift is reuired and this is usuall proided b increasing the thrust.;

the thrust.; explain8297*

explain8297*otal lift is mainplane lift minus otal lift is mainplane lift minus tailplane download. tailplane download. If the tailplane downloadIf the tailplane download decreases, the total lift increases.

decreases, the total lift increases. *herefore to maintain *herefore to maintain straight and leel 3ight straight and leel 3ight the mainplanethe mainplane lift would hae to decrease.;

lift would hae to decrease.;

explain8#97*he most eTcient angle of attac! is when the =K6

explain8#97*he most eTcient angle of attac! is when the =K6 ratio is a maximum. ratio is a maximum. *his is*his is usuall around % degrees.;

usuall around % degrees.;

explain8%97If the C of D is aft of the centre of pressure, an increase in lift will pitch the aircraft explain8%97If the C of D is aft of the centre of pressure, an increase in lift will pitch the aircraft nose-up, which will increase the lift een further etc. etc.;

nose-up, which will increase the lift een further etc. etc.;

explain8'97<orpoising is an oscillator motion in the pitch plane.; explain8'97<orpoising is an oscillator motion in the pitch plane.;

explain8976irectional stabilit is maintained b the !eel surface and the >n and controlled b explain8976irectional stabilit is maintained b the !eel surface and the >n and controlled b the rudder.;

the rudder.;

explain8/97hen a high wing aircraft sideslips, the upper wing is shielded from some of the explain8/97hen a high wing aircraft sideslips, the upper wing is shielded from some of the air3ow b the fuselage.

air3ow b the fuselage. *he upper wingLs lift *he upper wingLs lift reduces, it drops and reduces, it drops and the aircraft opposes thethe aircraft opposes the sideslip.;

sideslip.;

explain8097+ince some of the lift ector is used to turn the aircraft, there will be a tendanc to explain8097+ince some of the lift ector is used to turn the aircraft, there will be a tendanc to reduce height.

reduce height. **o maintain height, power must be incro maintain height, power must be increased to compensate.;eased to compensate.;

explain8497 wing mounted stall sensing deice is mounted Fust underneath the wing leading explain8497 wing mounted stall sensing deice is mounted Fust underneath the wing leading edge.;

Exam Number:-11.

---1. *he upper part of the wing in comparison to the lower

a) deelops more lift b) deelops the same lift c) deelops less lift

2. hat e&ect would a forward CD hae on an aircraft on landing

a) Increase stalling speed b) No e&ect on landing c) Aeduce stalling speed

#. UNJ refers to

a) Uuite near hori@on

b) setting the altimeter to @ero

c) setting the mean sea leel atmospheric pressure so an altimeter reads the aerodrome altitude aboe mean sea leel

%. UNE refers to

a) +etting an altimeter to read aerodrome altitude aboe sea leel b) Uuite new euipment

c) setting the mean sea leel atmospheric pressure in accordance with IC$ standard atmosphere i.e. 151# millibars

a) span %, mean chord 0 b) mean chord % , span 0 c) span suared % ,chord 0

. If an aircraft in leel 3ight loses engine power it will

a) pitch nose up b) pitch nose down

c) not change pitch without drag increasing

/. U(E is

a) sea leel pressure b) air>eld pressure

c) di&erence between sea leel and air>eld pressure

0. *he lift Kdrag ratio at stall a) increases

b) decreases c) is unchanged

4. $n a straight unswept wing, stall occurs at a) the thic! portion at the wing root

b) the thic! portion at the wing tip c) the thin portion at the wing tip

15. 6uring a climb from a die

b) the thrust reuired is lower than for leel 3ight c) the thrust reuired is the same as for leel 3ight

ans819 7 a; ans829 7 a; ans8#9 7 c; ans8%9 7 a; ans8'9 7 a; ans89 7 b; ans8/9 7 b; ans809 7 b; ans849 7 a; ans8159 7 b;

explain8197=oo! at the lift distribution diagram of an aerofoil and see how approximatel 2K#rds of the lift is deried from the top surface.;

explain8297 forward CD would reuire the tail of the aircraft to exert more download to !eep the nose leel. *his will increase the wing loading and thus the aircraft would stall at a higher speed.;

explain8#97LUL is the mathematical smbol for pressure. LNJL stands for Nautical Jeight. UNJ refers to the setting of the mean sea leel atmospheric pressure "i.e. 151#mb) so the altimeter indicates the altitude aboe mean sea leel.;

explain8%97LUL is the mathematical smbol for pressure. LNEL stands for Nautical Eleation. UNE refers to the setting of sea leel atmospheric pressure so the altimeter indicates the actual altitude aboe sea leel of the non-standard da.;

explain8'97spect Aatio is the ratio of the span to the chord.;

explain897ssuming that the thrust-drag couple is a pitch-up couple "as it would be on a low engined aircraft) then losing engine power will lose the pitch up moment so the aircraft will pitch nose down.;

explain8/97LUL is the mathematical smbol for pressure. L(EL stands for (ield Eleation. U(E refers to setting air>eld pressure so the altimeter indicates @ero on the runwa.;

explain8097t stall the lift drops drasticall and drag increases. *herefore the liftKdrag ratio decreases.;

explain8497$n a straight unswept wing, the stall alwas occurs at the root. *his is the preferred stall characteristic.;

explain815976ue to the speed and momentum gained during the die, the aircraft will initiall climb with less reuired thrust.;

Exam Number:-12. Exam Number:-12.

---1.

1. hen hen power power is is o&, o&, the the aircraft aircraft will will pitchpitch

a)

a) nose nose downdown b) nose up b) nose up c)

c) trim trim leelleel

2.

2. ngle ngle of of attac! on attac! on a a down down going going wing wing in in a a rollroll a) increases a) increases b) decreases b) decreases c) una&ected c) una&ected #.

#. (or (or an an gien gien speed, a speed, a decrease decrease in in aircraft aircraft weight, the weight, the induced induced drag drag willwill

a) increase a) increase b) decrease b) decrease c)

c) remain remain the the samesame

%.

%. *he *he amount amount of of lift lift generated generated b b a a wing wing isis a) greatest

a) greatest at at the the rootroot b) greatest at the tip b) greatest at the tip c)

c) constant constant along along the the spanspan

'.

'. Induced Induced 6rag 6rag isis

a)

a) greatest towards the wing root greatest towards the wing root and downwash is and downwash is greatest at the tipgreatest at the tip b) greatest towards the wing tip and downwash is greatest towards the root b) greatest towards the wing tip and downwash is greatest towards the root c)

.

. Induced Induced 6rag 6rag isis

a)

a) eual to eual to pro>le drag pro>le drag at stalling angleat stalling angle b) eual to pro>le drag at Mmd

b) eual to pro>le drag at Mmd c)

c) neer neer eual eual to to pro>le pro>le dragdrag

/.

/. ith ith an an increase increase in in aircraft aircraft weightweight

a)

a) Mmd will Mmd will be at be at the same speedthe same speed b) Mmd will be at a lower speed b) Mmd will be at a lower speed c)

c) Mmd Mmd will will be be at at a a higher higher speedspeed

0.

0. (or (or a a gien gien I+ I+ an an increase increase in in altitude will altitude will result result inin

a)

a) no change no change in the in the alue of induced alue of induced dragdrag b) an increase in induced drag

b) an increase in induced drag c)

c) an an increase increase in in pro>le pro>le dragdrag

4.

4. s s the the angle oangle of f attac! of attac! of a a wing wing is is increased in increased in leel 3ightleel 3ight

a)

a) the Cof D the Cof D moes aft and the moes aft and the Cof < forwardCof < forward b) the Cof < and transition point moe forward b) the Cof < and transition point moe forward c)

c) the Cof the Cof < < moes forward moes forward and and the stagnation the stagnation point point aft aft oer the oer the upper upper surfacesurface

15.

c)

c) at at the the root root to to cause cause the the root root to to stall stall >rst>rst 777777777777

ans819 7 a; ans829 7 a; ans8#9 7 b; ans8%9 7 a; ans8'9 7 c; ans89 7 b; ans8/9 7 c; ans809 7 b; ans849 7 b; ans8159 7 c;

explain8197ssuming that the thrust-drag couple is a pitch-up couple "as it would be on a low engined aircraft) then losing engine power will lose the pitch up moment so the aircraft will pitch nose down.;

explain8297*he downgoing wing experiences an up3ow of air. *his increases angle of attac! and lift and thus opposes the role. *hs is the basic mechanism of dnamic stabilit.;

explain8#97Induced drag is Llift dependant dragL. =ess lift and there will be less induced drag. 6ecreasing the lift decreases the induced drag.;

explain8%97+ee a diagram of the lift distribution of the wing "iewed from the front) and ou will see it is parabolic. *he wing tip ortices decrease the lift at the tips.;

explain8'97Induced drag is associated with wintip ortices. *he greater the ortices at the tip, the greater is the induced drag.;

explain897+!etch the drag cures "drag against speed). Induced drag decreases

exponentiall with speed. <ro>le drag increases exponentiall with speed. Mmd "minimum drag speed) is where the meet.;

explain8/97+!etch the drag cures "drag against speed). Induced drag decreases

exponentiall with speed. <ro>le drag increases exponentiall with speed. *he induced drag is eleated with weight "since it is lift dependant) and so cuts the pro>le drag further to the right "higher Mmd);

explain8097*he lift reuired when an aircraft increases altitude is the same, so with a decrease in densit the aircraft must 3 with a greater angle of attac! "C=). Induced drag is dependant upon C= therefore induced drag increases with altitude..;

explain81597+tall inducers "or stall strips) are placed at the root of the wing to trip up the air3ow Fust before full stall to ensure the wing stalls >rst at the root "and maintains the aileron authorit een with a partiall stalled wing).;

Exam Number:-1#.

---1. ith increasing altitude pressure decreases and

a) temperature decreases at the same rate as pressure reduces b) temperature decreases but at a lower rate than pressure reduces c) temperature remains constant to 0555 ft

2. *he Centre of <ressure is

a) the point on the chord line at which the resultant lift force ma be said to act b) the point of maximum pressure on the under surface of the wing

c) the centre of grait of the wing

#. If the angle of attac! is increased the Centre of <ressure will a) moe forward

b) moe rearward c) remain stationar

%. *he optimum angle of attac! of an aerofoil is the angle at which

a) the aerofoil produces maximum lift b) the aerofoil produces @ero lift

c) the highest liftKdrag ratio is produced

'.  high aspect ratio wing has a

. Hinimum total drag of an aircraft occurs

a) at the stalling speed

b) when pro>le drag euals induced drag c) when induced drag is least

/. If the weight of an aircraft is increased, the induced drag at a gien speed

a) will increase b) will decrease

c) will remain the same

0. *he transition point on a wing is the point where

a) the 3ow separates from the wing surface

b) the boundar laer 3ow changes from laminar to turbulent c) the 3ow diides to pass aboe and below the wing

4. *he boundar laer of a bod in a moing airstream is

a) a thin laer of air oer the surface where the air is stationar b) a laer of separated 3ow where the air is turbulent

c) a laer of air oer the surface where the airspeed is changing from free stream speed to @ero speed

15.  laminar boundar laer will produce

a) more s!in friction drag than a turbulent one b) less s!in friction drag than a turbulent one

c) the same s!in friction drag as a turbulent one

ans819 7 b; ans829 7 a; ans8#9 7 a; ans8%9 7 c; ans8'9 7 b; ans89 7 a; ans8/9 7 a; ans809 7 b; ans849 7 a; ans8159 7 b;

explain8197+ee a graph of pressure against altitude and temperature against altitude. <ressure decreases faster than temperature therefore pressure has a greater e&ect upon the performance of the aircraft.;

explain8297*he centre of <ressure is the point on the chord line at which the resultant lift force is said to act.;

explain8#97If the angle of attac! is increased the centre of pressure will moe forwards.; explain8%97*he optimum angle of attac! is the angle at which the highest liftKdrag ratio is produced.;

explain8'97Induced drag decreases with increasing aspect ratio.;

explain897+!etch the drag cures "drag against speed). Induced drag decreases

exponentiall with speed. <ro>le drag increases exponentiall with speed. Mmd "minimum drag speed) is where the meet.;

explain8/97If weight is increased, for a gien speed the aircraft must 3 at a greater angle of attac! "C=). Induced drag increases with increased C=.;

explain8097*he transition point is a point on the surface of the wing where the boundar laer changes from laminar to turbulent.;

explain8497*he boundar laer is a thin laer of stationar air in contact with the surface of the s!in.;

explain81597+!in friction drag is greater in a turbulent boundar laer than in a laminar boundar laer.;

Exam Number:-1%.

---1. =ongitudinal stabilit is gien b

a) the >n

b) the wing dihedral

c) the hori@ontal tailplane

2. =ateral stabilit is gien b a) the ailerons

b) the wing dihedral

c) the hori@ontal tailplane

#. +tabilit about the lateral axis is gien b

a) wing dihedral

b) the hori@ontal tailplane c) the ailerons

%. +weepbac! of the wings will

a) increase lateral stabilit b) decrease lateral stabilit

c) not a&ect the lateral stabilit

c) primaril a pitching instabilit

.  high wing position gies

a) more lateral stabilit than a low wing b) less lateral stabilit than a low wing c) the same lateral stabilit as a low wing

/. $n an aircraft in an unpowered stead speed descent

a) the lift euals the weight b) the weight euals the drag

c) the weight euals the resultant of the lift and drag

0. hen an aircraft rolls to enter a turn and power is not increased a) the lift euals the weight

b) the lift is greater than the weight c) the lift is less than the weight

4. *he boundar laer is

a) thic!est at the leading edge b) thic!est at the trailing edge

c) constant thic!ness from leading to trailing edges

15. *he amount of thrust produced b a Fet engine or a propeller can be calculated using

a) Newtons 1st law b) Newtons 2nd law c) Newtons #rd law

ans819 7 c; ans829 7 b; ans8#9 7 b; ans8%9 7 a; ans8'9 7 a; ans89 7 a; ans8/9 7 c; ans809 7 c; ans849 7 b; ans8159 7 b;

explain8197*he hori@ontal stabili@er "tailplane) proides longitudinal stabilit.; explain8297*he wing dihedral proides lateral stabilit.;

explain8#97+tabilit about the lateral axis is longitudinal stabilit. *he hori@ontal stabili@er "tailplane) proides longitudinal stabilit.;

explain8%97ing sweepbac! increases the Le&ectieL dihedral of the wing "15 degrees of sweepbac! has the same e&ect as 1 degree of dihedral) and therefore increases lateral stabilit.;

explain8'976utch role is a combination of role and aw.;

explain897*he pendulum e&ect produced b the fuselage of a high wing aircraft proides more lateral stabilit.;

explain8/97In an unpowerd descent, the weight euals the resultant of the lift and the drag.; explain8097hen an aircraft roles into a turn and power is not increased, the lift is greater than the weight and the aircraft will begin to descend.;

explain8497*he boundar laer is thic!est at the trailing edge.; explain81597NewtonLs second law is (orce 7 Hass x cceleration.;

Exam Number:-1'.

---1. n engine which produces an eVux of high speed will be

a) more eTcient b) less eTcient

c) speed of eVux has no a&ect on the engine eTcienc

2. hen an aircraft with a Cof D forward of the Cof < rolls, the nose of the aircraft will

a) sta leel b) raise c) drop

#. 6irectional stabilit ma be increased with

a) pitch dampers b) horn balance c) aw dampers

%. =ateral stabilit ma be increased with

a) increased lateral dihedral b) increased lateral anhedral

a) C< moes forward of the CD

b) *hrust acts on a line below the total drag c) CD is forward of the C<

. ing loading is calculated b weight

a) diided b gross wing area b) diided b lift

c) multiplied b gross wing area

/. Induced drag is

a) inersel proportional to the suare of speed b) proportional to speed

c) nothing to do with speed

0. In a ban!, the weight is

a) increased b) decreased c) the same

4. =K6 ratio is

a) higher at supersonic cruise speed b) higher at sub sonic speed

c) the same

a) the same as at high altitude b) higher

c) lower

ans819 7 b; ans829 7 c; ans8#9 7 c; ans8%9 7 a; ans8'9 7 c; ans89 7 a; ans8/9 7 a; ans809 7 c; ans849 7 b; ans8159 7 a;

explain8197 pure turboFet accelerates a low mass of air at a high rate and is less eTcient than a turbo fan or turbo prop.;

explain8297+ince the weight-lift couple is a nose down moment, a reduction of the lift "when the aircraft roles some of the lift ector is used to turn the aircraft) will cause the nose to rise.; explain8#97aw dampers increase directional stabilit.;

explain8%97=ateral dihedral increases lateral stabilit. "?*: =ongitudinal stabilit is the di&erence between mainplane and tailplane angles of incidence);

explain8'97If the CD is forward of the C< it will hae a nose-down tendanc which ma!es the aircraft less li!el to stall and therefore it will hae more longitudinal stabilit.;

explain897ing loading is weight diided b wing area and measured in Newtons per suare metre.;

explain8/97Induced drag is inersel proportional to the suare of the speed - i.e. it reduces with the suare of the speed.;

explain8097*he weight is not changed unless ou throw something out of the aircraft.; explain8497?ecause drag increases in thew supersonic range the liftKdrag ratio will be higher at subsonic speed.;

explain81597+ince drag is the same at all altitudes , the power reuired is the same at all altitudes.;

Exam Number:-1.

---1. If the stall speed is /' !nots what is the same stall speed in mph

a) /' x 5.0/ b) /' K 5.0/

c) /' K 5.0/ x relatie densit

2. s the angle of attac! increases the stagnation point

a) moes towards the upper surface b) moes towards the lower surface c) does not moe

#. *he term pitch-up is due to

a) compressibilit e&ect b) ground e&ect

c) longitudinal instabilit

%. In a stead climb at a stead I+, the *+ is

a) more than I+ b) less than I+ c) the same

a) hae no aw e&ect in ban!ing

b) hae no change in induced drag in the ban! c) stall at the root >rst

. ith the ailerons awa from the neutral, induced drag is

a) unchanged but pro>le drag is higher

b) higher on the lower wing plus pro>le drag increases c) higher on the upper wing plus pro>le drag increases

/. *he lift drag ratio is

a) higher at mach numbers aboe supersonic b) higher at sub sonic mach numbers

c) the same

0. *he force opposing thrust is

a) drag b) lift

c) eight

4. 6irectional stabilit is about the

a) normal axis b) longitudinal axis c) lateral axis

a) longitudinal axis b) normal axis c) ertical axis

ans819 7 b; ans829 7 b; ans8#9 7 a; ans8%9 7 a; ans8'9 7 c; ans89 7 c; ans8/9 7 b; ans809 7 a; ans849 7 a; ans8159 7 a;

explain8197H<J 7 PnotsK5.0/ and Pnots 7 H<J x 1.1'.;

explain8297*he stagnation point is the stationar air at the leading edge of the wing. s the angle of attac! increases the stagnation point moes towards the lower surface.;

explain8#97L<itch-upL is a term gien to the instabilit caused b the compressibilit e&ect in the transonic range.;

explain8%97I+ is a function of densit. If densit reduces with altitude, the *+ must increase if the aircraft maintntains a stead I+.;

explain8'97*he straight wing will alwas stall at the root >rst. *his is the desired stall characteristic.;

explain897Induced drag is Llift dependant dragL. *he upper wing has more lift and hence more induced drag. It also has more pro>le drag due to the aileronLs protrusion into the air3ow.;

explain8/97+ince drag is higher in supersonic 3ight, the =iftK6rag ratio will be higher at sub-sonic speeds.;

explain8097*he force opposing thrust is drag.;

explain84976irectional stabilit is stabilit about the normal axis.; explain81597=ateral stabilit is stabilit about the longitudinal axis.;

Exam Number:-1/.

---1. ll the lift can be said to act through the

a) centre of pressure b) centre of grait c) normal axis

2. =ongitudinal stabilit is proided b the

a) hori@ontal stabili@er b) ertical stabili@er c) mainplane

#. *he concept of thrust is explained b

a) Newtons 1st law b) Newtons #rd law c) ?ernoullis theorem

%. *he camber of an aerofoil section is

a) the curature of the median line of the aerofoil b) the angle of incidence towards the tip of a wing

a) the sweepbac! of the wing will correct the sideslip b) the dihedral of the wing will correct the sideslip c) the !eel surface will correct the sideslip

. Hoement of an aircraft about its lateral axis

a) is pitching b) is rolling c) is awing

/. Induced drag

a) is caused b s!in friction

b) results from disturbed air3ow in the region of mainplane attachments c) is associated with the lift generated b an aerofoil

0. *he centre of pressure is

a) the point on the chord line through which the total resultant lift force on the aerofoil ma be said to act

b) the point of maximum pressure on the undersurface of a mainplane c) the point at which the four forces acting on an aircraft are said to act

4. t what altitude is tropopause

a) #,555 ft. b) #,555 ft. c) '/,555 ft.

a) 12O b) 21O c) /0O

ans819 7 a; ans829 7 a; ans8#9 7 b; ans8%9 7 a; ans8'9 7 b; ans89 7 a; ans8/9 7 c; ans809 7 a; ans849 7 b; ans8159 7 b;

explain8197ll the lift is said to act through the centre of pressure.;

explain8297=ongitudinal stabilit is proided b the hori@ontal stabiliser "tailplane).; explain8#97NewtonLs *hird =aw states LEer action has an eual and opposite reactionL.; explain8%97erofoil camber is the curature of the median line of the aerofoil.;

explain8'97s the aircraft turns and sideslips the dihedral of the wing will correct the sideslip due to the increased lift on the downgoing wing.;

explain897Hoement of an aircraft about its lateral axis is LpitchingL.;

explain8/97Induced drag is often called Llift dependant dragL because it increases with increasing lift.;

explain8097*he C of < is the point at which the sum of all the forces on the aircraft can be said to act.;

explain8497*he tropopause is #,555 ft. boe the tropopause is the troposphere.; explain8159721O oxgen, /0O nitrogen, 1O other gases.;

Exam Number:-10.

---1. hich has the greater densit

a) air at low altitude b) air at high altitude c) it remains constant

2. s air 3ows oer the upper cambered surface of an aerofoil, what happens to elocit and pressure

a) Melocit decreases, pressure decreases b) Melocit increases, pressure increases c) Melocit increases, pressure decreases

#. hat is the force that tends to pull an aircraft down towards the earth

a) 6rag b) *hrust c) eight

%. hich of the following act in opposition to forward moement

a) =ift b) Drait c) 6rag

a) angle of attac! b) angle of incidence c) resultant

. *he imaginar straight line which passes through an aerofoil section from leading edge to trailing edge is called

a) centre of pressure

b) the direction of relatie air3ow c) the chord line

/. hat is the angle between the chord line of the wing, and the longitudinal axis of the aircraft, !nown as

a) angle of attac! b) angle of incidence c) angle of dihedral

0. n aircraft disturbed from its normal 3ight path, and automaticall returns to that normal 3ight path, without an action on the part of the pilot is !nown as

a) aircraft stabilit b) aircraft instabilit c) aircraft stall

4. 6irectional control is proided b

a) hori@ontal stabili@er b) rudder

c) eleator