Dgca Module 8 Full

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Module Eigh Eightt 1. On a swept wing aircraft if bot h wing tip sectio ns lose lift sim ultaneously the aircr aircr aft will a) roll # b) pitch nose up c) pitch nose down 2. Lift on a delta wing aircraft # a) increases with an incr eased eased angle of incidence (angle (angle of attack) b) decreases decreases with an increase in angle of inc idence (angle (angle of attack) c) does not c hange with a change in angle of inci dence (angle (angle of attack)

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3. on a straight w ing aircraft, stall co mmences at at the # a) root on a high thick ness ratio wing b) tip on a high thickn ess ratio wing c) tip on a low thic kness ratio wing 4. On a high wing aircraft i n a turn a) the up-going wing loses lift causing a de-stabilizing de-stabilizing effect # b) the down-going wing gains lift causing a stabilizing effect effect c) the down-going wing los es lift causing a de-stabilizing de-stabilizing effect 5. for the same angle angle of attack, the lift on a delta wing a) is gr eater eater than the lift on a high aspect ratio wing # b) is lower than the lift on a high aspect aspect ratio ratio wing c) is the same as as the lift on a high aspect ratio wing 6. The ISA? a) is t aken aken fr om the equator # b) is taken from 45 degrees degrees latitude c) assumes a standard day 7. at at hi gher altitud es as altitude inc reases, reases, pressure a) decreases at constant rate b) incr eases eases exponentially # c) decreases exponent ially 8. The thru st-drag couple overcomes the lift -weight -weight co uple. What What directio n of force is required to be produced by the tail of th e aircr aircr aft to maintain straight and level flight # a) upw ards b) downwards c) sid eways

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9. When When the pressure is half of that at sea level, level, what is the altitud e? a) 12,000 12,000 ft b) 8,000 ft # c) 18,000 18,000 ft 10. 10. during a turn, the stalling angle a) increases b) decreases # c) remains the same 11. If gauge press ure on a st andard day at sea level is 25 PSI, PSI, the absol ute pr essur e is a) 10.3 PSI b) 43.8 PSI # c) 39.7 PSI


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12. 12. The The C of G moves in flight . The most l ikely cause of th is is a) movement movement of passengers passengers b) movement movement of the centre of pressure # c) consum ption of fuel and oils 13. 13. The C of P is th e point w here a) all the forces on an aircraft act b) the three axis axis o f rot ation meet # c) the lift can be said to act act 14. 14. The three axis axis of an aircr aft act th rough the # a) C of G b) C of P c) stagnation stagnation poi nt 15. 15. Pressur e decreases # a) propor tionally with a decreases decreases in temperature temperature b) inversely inversely propo rti onal to temperature c) Pressure and temperature are not related 16. 16. As air gets c older, the service ceiling of an aircr aircr aft a) reduc es # b) inc reases c) remains t he same 17. 17. What is sea level pressur e? # a) 1013.2 mb b) 1012.3 mb c) 1032.2 mb

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9. When When the pressure is half of that at sea level, level, what is the altitud e? a) 12,000 12,000 ft b) 8,000 ft # c) 18,000 18,000 ft 10. 10. during a turn, the stalling angle a) increases b) decreases # c) remains the same 11. If gauge press ure on a st andard day at sea level is 25 PSI, PSI, the absol ute pr essur e is a) 10.3 PSI b) 43.8 PSI # c) 39.7 PSI


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12. 12. The The C of G moves in flight . The most l ikely cause of th is is a) movement movement of passengers passengers b) movement movement of the centre of pressure # c) consum ption of fuel and oils 13. 13. The C of P is th e point w here a) all the forces on an aircraft act b) the three axis axis o f rot ation meet # c) the lift can be said to act act 14. 14. The three axis axis of an aircr aft act th rough the # a) C of G b) C of P c) stagnation stagnation poi nt 15. 15. Pressur e decreases # a) propor tionally with a decreases decreases in temperature temperature b) inversely inversely propo rti onal to temperature c) Pressure and temperature are not related 16. 16. As air gets c older, the service ceiling of an aircr aircr aft a) reduc es # b) inc reases c) remains t he same 17. 17. What is sea level pressur e? # a) 1013.2 mb b) 1012.3 mb c) 1032.2 mb

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Page 2 - Mod Mod 8 18. 18. When When the weight of an aircraft increases, the minimum drag speed a) decreases # b) inc reases c) remains the same 19. 19. An aircr aft will have a) less glidi ng dist ance if it has more payload b) more gliding d istance if it h as more payload payload # c) the same glidin g distance if it has has more payload


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20. When an aircraft experiences induced drag # a) air flows under the wing spanwise towards the tip and on top of the wing spanwise towards the root b) air air flow s under the wing spanwise towards the root and on top o f the wing spanwise towards the tip c) Neither Neither a) a) or b) since induc ed drag does does not caused by spanwise flow 21. 21. At stall, the wingt ip stagnation poi nt # a) moves toward the lower surf ace of the wing b) moves toward the upper surf ace of th e wing c) doesn’t move 22. 22. How does IAS at the point of st all vary with height? # a) It is practically const ant b) It increases c) It decreases 23. 23. The rigging angle of inc idence of an elevator elevator is # a) the angle between between the mean mean chord line and the horizontal in the riggi ng positio n b) the angle between between the bottom surf ace of t he elevator elevator and the horizontal in the riggi ng position c) the angle betwee between n th e bottom s urface of th e eleva elevator tor and the longitu dinal datum 24. 24. What is the lapse rate with regard to temperature? temperature? o # a) 1.98 C per 1000 ft b) 1.98oF per 1000 ft c) 4 oC per 1000 ft 25. 25. What What happens to l oad factor as you d ecrease ecrease turn radius? # a) It inc reases b) It decreases c) It remains remains cons tant

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26. 26. If you st eepen eepen the angle of a banked turn wit hout increasing airspeed or angle of attack, what will the aircraft do? a) It It w ill r emain emain at the same height # b) It will sideslip with attendant attendant loss of height c) It It will s tall 27. 27. An aircr aircr aft wing tends to s tall first at a) the tip due to a higher ratio t hickness/chor d b) the tip du e to a lower ratio thic kness/chord # c) the root due to a higher ratio thic kness/chord


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28. 28. Dihedral Dihedral wings co mbat inst ability in a) pitch b) yaw # c) sideslip 29. 29. To To sto p aircraft decreasing in height d uring a sideslip , the pilot can # a) advance the thr ott le b) pull back on the control column c) adjust adjust t he rudder rudder posit ion 30. 30. What What contr ol surf ace movements will m ake an aircr aircr aft fitt ed with rudd ervators ervators yaw to the left? # a) Left ruddervator lowered, right ruddervator raised b) Right Right r uddervator lowered, left left r uddervator raised c) Both ruddervators r aised 31. When a leading edge slat opens, there is a gap between the slat and the wing. This is a) to allow it to retract back into the wing # b) to allow air air through to re-energize re-energize the boundary layer on top of the wing c) to k eep eep th e area area of the wi ng th e same 32. 32. Which Which of the followi ng is tr ue? a) Lift acts at rig ht angles to the wing chord l ine and weight acts vertic ally down # b) Lift acts at right angles angles to the relative airflow and and weight acts acts verti verti cally down c) Lift acts at right angles to the relative relative air air flow and weight acts at right angles to the aircraft centre line 33. 33. If the wing tips stall before the root on a swept win g aircraft, the aircr aircr aft will a) roll # b) pitch nose up c) pitch nose down Page 4 - Mod 8


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34. Lift on a delta wing aircraft # a) inc reases wit h an inc reased angle of incid ence (angle of att ack) b) decreases with an increase in angle of inc idence (angle of attack) c) does not c hange with a change in angle of inci dence (angle of attack) 35. On a straight win g aircraft, stall com mences at the # a) root on a high thickn ess ratio wing b) tip on a high thi ckness ratio wing c) tip on a low thic kness ratio wing 36. On a high wing aircr aft in a tur n a) the up-going wi ng loses lif t causing a de-stabilizing effect # b) the down-going wing gains lift causing a stabilizing effect c) the down-going wing los es lift causing a de-stabilizing effect


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37. For the same angle of attack, the lif t on a delta wing a) is gr eater 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 38. Standard s ea level temperat ure is a) 0 degrees Celsi us # b) 15 degrees Celsi us c) 20 degrees Celsiu s 39. As alti tude inc reases, pr essure a) decreases at constant rate b) incr eases exponentially # c) decreases exponent ially 40. The thrust-drag couple overcomes the lift-weight co uple. What directio n of force is required to be produced by the tail of the aircraft to maintain str aight and level flig ht? # a) Upwards b) Downwards c) Sideways 41. Lapse rate usually refers to a) Pressure b) Densit y # c) Temperatu re 42. During a tur n, the stalling angle a) increases b) decreases # c) remains th e same Page 5 - Mod 8



43. The vertical fin of a sing le engined aircraft is # a) parallel with both the longit udinal axis and vertical axis b) parallel with the longit udinal axis but not the vertical axis c) parallel with the vertical axis but not t he longitudi nal axis 44. Aircraft flyi ng in t he transonic range most often util ize # a) sweptback wings b) advanced supercritic al airfoi ls c) high wings 45. Which type of flap changes th e area of the wing ? # a) Fowl er b) Split c) Slotted


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46. Forward swept wi ngs tend to stall at the root f irst so the aircraft retains lateral cont rol, so why are they never used on passenger aircraft? a) Because the wing tip s wash in at high wing l oads b) Because the wing ti ps wash out at high wi ng loads # c) Because at high loads their angle of incidence increases and the loads imposed on the wing can increase until t hey destro y it 47. What happens to air flowin g at the speed of s ound wh en it enters a converging duct ? # a) Veloc ity decreases, press ure and densit y inc rease b) Velocit y inc reases, pressure and densit y decreases c) Velocit y, pressure and densit y inc rease 48. As the angle of attack of an airfoil in creases t he centre of pressure # a) mov es for ward b) moves aft c) remains s tationary 49. An aircr aft, which is lon gitudi nally stable, will t end to return to level flight after a movement about which axis? # a) Pitch b) Roll c) Yaw 50. Vapour trails f rom the wing tips of an aircraft in fl ight are caused by # a) low pressure above the wing and high pressure below the wing causing vortices b) high pressure above the wing and low pressure below the wing causing vort ices c) low pressure above the wing and high pressur e below t he wing causing a temperature rise

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51. Vortex generators on t he wing are most effective at a) high speed b) low s peed # c) high angles of attack 52. The chord li ne of a wing is a line that runs f rom # a) the centre of the leading edge of the wing to the trailing edge b) half way between th e upper and lower surf ace of the wing c) one wing tip to the other wing tip 53. The angle of inci dence of a wing is an angle form ed by lines # a) parallel to the chord line and longit udinal axis b) parallel to t he chord l ine and the lateral axis c) parallel to th e chord lin e and the vertical axis


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54. The centre of pressure of an aerofoi l is located # a) 30 - 40% of the chor d lin e back from the leading edge b) 30 - 40% of the chord line forward of the leading edge c) 50% of the chord line back fro m the leading edge 55. Compressibi lity effect i s a) drag associated with the form of an aircraft b) drag associ ated with the frict ion of the air over the surface of the aircraft # c) the incr ease in total drag of an airfoil in transonic flight due to the form ation of shock waves 56. Lateral cont rol of an aircraft at high angle of attack can be maximized by usin g a) fences # b) vortex generators c) wing slots 57. Stall strips are always a) made of m etal # b) on the leading edge of a wing c) fitted forward of the ailerons 58. Stall str ips # a) cause the wing root to stall b) cause the wing tip to st all c) cause the wings to st all symmetrically 59. Due to the interference of t he airflow o n a high wing aircraft between the fuselage and t he wings, the lateral stabilit y of the aircraft in a gusty win d situation w ill cause a) the upper wing t o incr ease its lift # b) the upper wing to decrease its lift c) the lower wing to decrease its l ift Page 7 - Mod 8



60. Slats # a) reduce the stall speed b) reduce the tendency o f t he aircr aft to Yaw c) decrease the aerofoil drag at high speeds 61. A high aspect ratio wing will g ive a) high pro file and low indu ced drag b) low profil e and high i nduced drag # c) low profi le and low induced drag 62. Aerofoi l effici ency is defined by # a) lift over drag b) drag over lift c) lift over weight


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63. An aircr aft banks i nto a t urn. No change is m ade to the airspeed or angle of attack. What will happen? # a) The aircraft enters a side slip and begins to lose altitude b) The aircr aft turns with no lo ss of height c) The aircraft yaws and slows dow n 64. The relations hip between i nduced dr ag and airspeed is a) directly pr oport ional to t he square of the speed # b) inversely propor tion al to the square of the speed c) directly proport ional to speed 65. What is the definition of Ang le of Incidence? a) The angle the underside of t he mainplane or tailplane makes wi th t he horizontal b) The angle the underside of the mainplane or tailplane makes wit h the long itudi nal datum line # c) The angle the chord of the mainplane or tailplane makes with the horizontal 66. What is Boundary Layer? a) Separated layer of air forming a boundary at the leading edge b) Turbul ent air moving f rom t he leading edge to trailing edge # c) Sluggish low energy air that stic ks to the wing surf ace and gradually gets faster until it jo in s t he f ree str eam f low of air 67. The normal axis of an aircr aft passes through # a) the centre of gravity b) a point at the center of t he wings c) at the centre of pressure

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68. on a high w inged aircraft, what effect will the fuselage have on the up-going w ing? # a) The up-go ing wing wil l have a decrease in angle of attack and therefor e a decrease in lift b) The down-going wil l have a decrease in angle of attack and therefore a decrease in lift c) The up-going wing will have an in crease in angle of attack and th erefore a decrease in lift 69. What is t he collective term for t he fin and rudder and other surf aces aft of t he centre of gravity that helps directional stability? # a) Effecti ve keel sur face b) Empennage c) Fuselage surfaces


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70. Temperatur e above 36,000 feet wi ll a) decrease exponentially # b) remain constant c) inc rease exponentially 71. A decrease in in cidence toward the wing tip may be provided to a) prevent adverse yaw in a turn b) prevent s panwise flow i n maneuvers # c) retain lateral contr ol effectiveness at high angles of attack 72. The angle of attack whic h giv es the best L/D ratio a) decreases with a decrease in density # b) in unaffected by density changes c) increases with a decrease in density 73. for a given aerofoil produc tion lift , where P = pressure and V = velocity:

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a) P1 is g reater than P2, and V1 is gr eater t han V2 b) P1 is less t han P2 and V1 is gr eater t han V2 c) P1 is greater than P2, and V1 is less than V2

74. Low wing loading a) increases stalling speed, landing speed and landin g run b) increases lif t, stalling speed and maneuverabilit y # c) decreases stalling speed, landing speed and landing run Page 9 - Mod 8



75. Due to t he change in downwash on an untapered win g (i.e. one of con stant cho rd length ) it will a) not provi de any damping effect when rolli ng # b) tend to stall firs t at the root c) not suf fer adverse yaw effects when turning 76. True stalling speed of an aircraft in creases wit h altitude a) because reduced temperature causes compr essibilit y effect # b) because air density is reduced c) because humidit y is incr eased and this i ncreases drag


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77. As a general rule, if t he aerodynamic angle of inci dence (angle of attack) of an aerofoil is slight ly incr eased, the centre of pressure will a) never m ove # b) move forw ard towards the leading edge c) move towards the tip 78. The "wi ng setting angle" i s commo nly know n as # a) angle of inc idence b) angle of attack c) angle of dihedral 79. on a very humid day, an aircraft taking of f wou ld requir e a) a shorter take off r un # b) a longer take off run c) humidity do es not affect the take off ru n 80. an aircraft is flying at 350 MPH, into a head wind of 75 MPH, what will its ground speed be? a) 175 mph # b) 275 mp h c) 200 mph 81. When does the angle of incidence change? a) When the aircr aft attit ude changes b) When the aircraft i s ascending or descending # c) It never chang es 82. as the angle of attack decreases, what happens to the centre of pressure? a) It moves f orward # b) It moves rearwards c) Centre of pressure is not affected by angle of attack decrease 83. A decrease in pressur e over the upper surf ace of a wing or aerofoil is respon sible for # a) approximately 2/3 (two thirds) of the lift obtained b) approximately 1/3 (one third ) of the lif t obt ained c) approximately 1/2 (one half) of t he lift obtained Page 10 - Mod 8



84. Which o f the four forces act on an aircraft? # a) Lift, gravity, thrus t and drag b) Weight, gravity, thrus t and drag c) Lift, weight, gravity and dr ag 85. Which o f the foll owing t ypes of dr ag increases as the aircr aft gains altitude? a) Parasite dr ag # b) Induced drag c) Interference drag 86. Correcting f or a disturbance which has caused a rolli ng moti on about the longitu dinal axis would re-establish which of the following? # a) Lateral stabi lit y b) Direction al stability c) Longitudinal stability s r e p a P n o i t s e u Q A C G D / b f @ k o o b e c a F n o s u e k i L , ) n i . s r e p a p n o i t s e u q a c g d . w w w (

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87. the layer of air over the surf ace of an aerofoi l whic h is sl ower moving, in r elation t o the rest of th e airfl ow, is known as a) camber layer # b) boundary layer c) none of the above 88. What is a contr olling f actor of turb ulence and skin fr icti on? a) Aspect ratio b) Fineness ratio # c) Counter sunk rivets used on skin exterior 89. Changes in aircraft w eight a) will not affect tot al drag since it is d ependant only u pon speed # b) cause corr esponding changes in total drag due to the associated lift change c) will only affect total drag if the lift i s kept constant 90. The aircr aft stallin g speed will # a) increase wit h an incr ease in weight b) be unaffected by aircraft w eight changes since it is dependant upon the angle of attack c) only change if the MTMA were changed 91. In a bank and tur n a) extra lift is n ot required b) extra lift i s not required if t hrust i s increased # c) extra lift is required

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92. To maintain str aight and level fli ght on t he aeroplane shown, w ith a decrease in tail-plane downl oad the mainplane lift wou ld have to

a) remain cons tant # b) decr ease c) increase


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93. To achieve the maximum distance in a glide, the recommended air speed is a) as clo se to the stall as p ractical b) as high as poss ible with VNE # c) the speed where the L/D ratio is maximum 94. If th e C of G is aft of t he Centr e of Pressur e # a) changes in lift produce a pitchi ng moment whic h acts to increase the change in lift b) when the aircr aft sideslips, the C of G causes the nose to tur n into t he sideslip thu s applying a restoring moment c) when the aircraft yaws t he aerodynamic fo rces acting f orward of the Centre of Pressure 95. Proposi ng is an oscillatory mot ion in the # a) pit ch plane b) roll plane c) yaw plane 96. Directio nal stability is m aintained a) by the mainplanes, and contr olled by the ailerons b) by the tailpl ane, and contr olled by th e elevators # c) by the keel surface and fin, and contro lled by the rudder 97. Due to the int erference effects of the fus elage, when a high win g aeroplane sideslips a) the accompanying r ollin g due to k eel sur face area is destabilizing # b) the accompanying lift changes on the wings produ ces a stabilizing effect c) the accompanyin g rolli ng due to the fin is destabilizing

Page 12 - Mod 8 98. The power required in a ho rizontal tur n # a) is greater than that for level fligh t at the same airspeed b) must be the same as that for level flight at the same airspeed c) is less t han that for level flight at the same airspeed DOWNLOAD OUR MOBILE APP FROM PLAY STORE @DGCA QUESTION PAPERS


99. A wing mou nted stall sensing d evice is located # a) usually on the under surface b) always at the wing tip c) always on the top surf ace 100. For an aircraft in a gli de a) thru st, drag, lift and weight act on t he aircraft # b) weight, lift and drag act on the aircraft c) weight and drag only act on t he aircraft 101. The upper part of the wing i n comp arison to t he lower # a) develops more lift b) develops the same lift c) develops less lif t s r e p a P n o i t s e u Q A C G D / b f @ k o o b e c a F n o s u e k i L , ) n i . s r e p a p n o i t s e u q a c g d . w w w (

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102. What effect woul d a forw ard CG have on an aircraft on landing ? # a) Increase stall ing speed b) No effect o n landing c) Reduce stalling speed 103. QNH refers to a) Quite near horizon b) setting t he altim eter to zero # c) settin g the mean sea level atmospheric pressure so an altim eter reads the aerodrome altitude above mean sea level 104. QNE refers to a) Setting an altimeter to read aerodrome altitude above sea level b) Quite new equipment # c) setting the mean sea level atmos pheric pressure in accordance with ICAO standard atmosphere i.e. 1013 millibars 105. An aspect ratio of 8 would mean # a) span 64, mean chor d 8 b) mean chor d 64 , span 8 c) span squared 64 ,chor d 8 106. If an aircraft in level fli ght l oses engine power it wi ll a) pitch n ose up # b) pitch nose down c) not change pitch w ithout d rag increasing

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107. QFE is a) sea level pr essur e # b) airfield pressure c) difference between sea level and airfield pressure 108. The lift /drag ratio at stall a) increases # b) decreases c) is unchanged 109. On a straight unswept wi ng, stall occ urs at # a) the thic k porti on at the wing root b) the thick portion at the wing tip c) the thin portion at the wing tip s r e p a P n o i t s e u Q A C G D / b f @ k o o b e c a F n o s u e k i L , ) n i . s r e p a p n o i t s e u q a c g d . w w w (

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110. During a climb from a dive a) the thrust required is greater than required for level flight # b) the thru st required is lower than for level flig ht c) the thrust r equired is the same as for level flight 111. When power is o ff, the aircraft wi ll pi tch # a) nos e dow n b) nose up c) trim l evel 112. Angle of attack on a down g oing wi ng in a roll # a) inc reases b) decreases c) unaffected 113. For any gi ven speed, a decrease in aircraft weight, t he induced dr ag will a) incr ease # b) decrease c) remain th e same 114. The amount of lift generated by a wing is # a) greatest at the root b) greatest at t he tip c) constant along th e span 115. Induc ed Drag is a) greatest tow ards the wing ro ot and downwash is greatest at the tip b) greatest towards th e wing t ip and downwash is greatest towards the root # c) greatest towards the tip and downwash decreases from tip to root

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116. Induced Drag i s a) equal to pr ofil e drag at st alling angle # b) equal to profile drag at Vmd c) never equal to prof ile drag 117. With an increase in aircraft weight a) Vmd wil l be at the same speed b) V md wil l be at a lower speed # c) Vmd will be at a higher speed 118. For a given IAS an inc rease in altit ude will result i n a) no change in the value of induced dr ag # b) an increase in induced drag c) an increase in pro file drag s r e p a P n o i t s e u Q A C G D / b f @ k o o b e c a F n o s u e k i L , ) n i . s r e p a p n o i t s e u q a c g d . w w w (

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119. As the angle of attack of a wing is inc reased in level flig ht a) the Cof G mov es aft and the Cof P f orward # b) the Cof P and transitio n point move forw ard c) the Cof P moves forw ard and the stagnation p oint aft over the upper surface 120. Stall induc ers may be fitted to a wing a) at the tip to cause the root t o stall first b) at the root t o cause the tip to st all first # c) at the root to cause the root to stall first 121. With inc reasing altitude p ressure decreases and a) temperatu re decreases at the same rate as pr essur e reduces # b) temperatu re decreases but at a low er rate than pressur e reduc es c) temperature r emains constant to 8000 ft 122. The Centr e of Pressur e is # a) the point on the chord lin e at whic h the resultant lift forc e may be said to act b) the point of maximum pr essure on the under surface of the wing c) the centre of gravity of the wing 123. If t he angle of attack is increased the Centre of Pressure wil l # a) move forw ard b) move rearward c) remain stationary 124. The optimum angle of attack of an aerofoil is the angle at whi ch a) the aerofoi l produ ces maximum lif t b) the aerofoil pr oduces zero lif t # c) the highest lift /drag ratio is produced

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Page 15 - Mod 8 125. A high aspect ratio w ing has a a) increased indu ced drag # b) decreased ind uced drag c) decreased skin f ricti on drag 126. Minimum to tal drag of an aircraft occur s a) at the stalling speed # b) when profil e drag equals induced drag c) when induced drag is least 127. If t he weight of an aircraft is increased, the induced drag at a given sp eed # a) wil l inc rease b) will decrease c) will remain t he same s r e p a P n o i t s e u Q A C G D / b f @ k o o b e c a F n o s u e k i L , ) n i . s r e p a p n o i t s e u q a c g d . w w w (

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128. The transition p oint on a wing is t he point where a) the flow separates from t he wing sur face # b) the boundary layer flow changes from laminar to turbulent c) the flow divi des to pass above and below the wing 129. The boundary layer of a bod y in a movi ng airstr eam is a) a thin layer of air ov er the surf ace where the air i s station ary b) a layer of separated flow where the air i s tur bulent # c) a layer of air over the surf ace where the airspeed is changing from f ree stream speed to zero speed 130. A laminar bou ndary layer will p roduc e a) more skin f ricti on drag than a turbulent one # b) less skin frictio n drag than a turb ulent one c) the same skin fr icti on drag as a turbulent one 131. Longit udinal stabilit y is given by a) the fin b) the wing di hedral # c) the horizontal tailplane 132. Lateral stability is given by a) the aileron s #

b) the wing dihedral c) the hori zontal tailplane

133. Stability about t he lateral axis i s gi ven by a) wing dihedral # b) the horizontal tailplane



c) the ailerons

Page 16 - Mod 8 134. Sweepback of t he wings will # a) inc rease lateral stabi lit y b) decrease lateral stability c) not affect the lateral stabilit y 135. Dutch Roll is # a) a combi ned rollin g and yawing motio n b) a type of slow r oll c) primarily a pitching instability s r e p a P n o i t s e u Q A C G D / b f @ k o o b e c a F n o s u e k i L , ) n i . s r e p a p n o i t s e u q a c g d . w w w (

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136. A high w ing posi tion gi ves # a) more lateral stabilit y than a low wing b) less lateral stability t han a low wing c) the same lateral stability as a low wing 137. On an aircraft in an unpowered steady speed descent a) the lift equals t he weight b) the weight equals the drag # c) the weight equals the resultant of the lift and drag 138. When an aircraft rolls to enter a turn and power is no t in creased a) the lift equals the weight b) the lift is greater than the weight # c) the lift is less than the weight 139. The boundary l ayer is a) thickest at the leading edge # b) thic kest at the trailing edge c) constant thick ness from leading to trailing edges 140. The amount of t hrust produc ed by a jet engine or a propeller can be calcul ated usin g a) Newton’ s 1st law # b) Newt on’ s 2nd law c) Newto n’s 3 rd law 141. An engine which pr oduces an efflux of high sp eed will b e a) more efficient # b) less efficient c) speed of efflux has no affect on the engine effic iency 142. When an aircraft w ith a C of G forw ard of t he C of P rolls, the nose of t he aircraft will a) stay level



#

b) rise c) drop

Page 17 - Mod 8 143. Directional s tability may be incr eased with a) pitch dampers b) horn balance # c) yaw dampers 144. Lateral stabilit y may b e incr eased wit h # a) inc reased lateral dih edral b) increased lateral anhedral c) increased longi tudin al dihedral s r e p a P n o i t s e u Q A C G D / b f @ k o o b e c a F n o s u e k i L , ) n i . s r e p a p n o i t s e u q a c g d . w w w (

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145. Longitudinal st ability is increased if the a) CP moves fo rward o f th e CG b) Thrust acts on a line below the total drag # c) CG is for ward of the CP 146. Wing l oading is calculated by weight # a) divided by gross wing area b) divided by lift c) multipli ed by gross wing area 147. Induced dr ag is # a) inversely propor tion al to the square of speed b) proporti onal to speed c) nothing to do with speed 148. In a bank, the weigh t is # a) inc reased b) decreased c) the same 149. L/D ratio i s a) higher at superson ic c ruise speed # b) higher at sub sonic speed c) the same 150. The power required at low altitude for a given IAS is a) the same as at high altitude b) higher # c) low er 151. If t he stall speed is 75 knots what is the same stall speed in m ph



#

a) 75 x 0.87 b) 75 / 0.87 c) 75 / 0.87 x relati ve densit y

152. As the angle of attack i ncreases th e stagnation poi nt a) moves tow ards the upper sur face # b) moves towards the lower surf ace c) does not move Page 18 - Mod 8 153. The term pitch-up is due to a) compr essibilit y effect b) ground effect # c) longit udinal instabilit y


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154. In a steady cli mb at a st eady IAS, the TAS is # a) mor e th an IAS b) less th an IAS c) the same 155. An untapered wing w ill a) have no yaw effect i n banking b) have no change in induced drag in the bank # c) stall at the root firs t 156. With t he ailerons away fr om t he neutral, induced drag is a) unchanged but pr ofile drag is hi gher b) higher on the lower wing plus pro file drag increases # c) higher on the upper wing plus profi le drag incr eases 157. The lift drag ratio i s a) higher at mach num bers above supersonic # b) higher at sub sonic mach numbers c) the same 158. The force opposi ng thr ust is # a) dr ag b) lift c) Weight 159. Directional st ability is about th e # a) nor mal axis b) longitudinal axis c) lateral axis 160. Lateral stability is about the # a) longit udinal axis b) normal axis



c) vertical axis 161. All t he lift can be said to act thr ough t he # a) centr e of press ure b) centre of gravity c) normal axis


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162. Longit udinal stabilit y is provi ded by the # a) hori zontal st abilizer b) vertical st abilizer c) mainplane Page 19 - Mod 8 163. The concept of thrust is explained by a) Newt on’ s 1st law # b) Newt on’ s 3rd law c) Bernoull i’s th eorem 164. The camber of an aerofoil section is # a) the curvatur e of the median line of the aerofo il b) the angle of inc idence towards the tip of a wing c) the angle which the aerofoil makes with the relative airfl ow 165. If th e aircraft turn s and side-slips a) the sweepback of the wing wil l corr ect the sideslip # b) the dihedral of the wing will correct the sideslip c) the keel surf ace will c orrect t he sideslip 166. Movement of an aircraft about i ts l ateral axis # a) is pitch ing b) is rolling c) is yawin g 167. Induced dr ag a) is caused by skin fric tion b) results f rom di sturbed airflow in t he region of mainplane attachments # c) is associ ated with the lift generated by an aerofoi l 168. The centre of pressure is # a) the point on the chord line through which the total resultant lift force on the aerofoi l may be said to act b) the point of maximum pr essure on the undersurface of a mainplane c) the point at which the four f orces acting on an aircraft are said to act 169. At what altitude is tropo pause a) 63,000 ft. # b) 36,000 ft . c) 57,000 ft .



170. What approxim ate percentage of oxygen is in the atmosph ere a) 12% # b) 21% c) 78% 171. Which has the greater density # a) air at low altit ude b) air at high altit ude c) it remains co nstant


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Page 20- Mod 8 172. As air f lows over the upper cambered surface of an aerofoi l, what happens to velocit y and pressure? a) Velocity decreases, pressure decreases b) Velocit y in creases, pressur e increases # c) Veloc ity inc reases, press ure decreases 173. What is t he force that tends t o pull an aircr aft down t owards th e earth? a) Drag b) Thrust # c) Weight 174. Which of the followi ng act in opposit ion to forw ard movement? a) Lift b) Gravity # c) Drag 175. The angle at whi ch th e chord li ne of the aerofoi l is presented to the airflow is kn own as # a) angle of attack b) angle of inc idence c) resultant 176. The imaginary straight line whic h passes throu gh an aerofoil section f rom l eading edge to tr ailing edge is called a) centre of pressure b) the direction of r elative airflow # c) the chord line 177. What is t he angle between the chor d line of the wing, and the longi tudin al axis of t he aircraft, known as a) angle of attack # b) angle of incid ence c) angle of dih edral 178. An aircraft dist urbed from i ts norm al flight path, and automatically return s to th at normal fligh t path, with out any action on the part of the pilot is kn own as



#

a) aircraft stabilit y b) aircraft instability c) aircraft stall

179. Directional cont rol is provi ded by a) horizontal st abilizer # b) rudder c) elevator


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Page 21 - Mod 8 180. About w hich axis of the aircr aft does a rolling mot ion t ake place? a) Norm al axis # b) Longit udinal axis c) Lateral axis 181. Which moti on happens about the lateral axis? # a) Pitch ing b) Yawing c) Rollin g 182. Wing tip vort ices create a type of drag known as a) form drag # b) induc ed drag c) profile drag 183. Which of the foll owing descri bes the “ Empennage” ? a) Nose section o f an aircr aft, including t he cockpit # b) Tail section of the aircraft, includ ing fin, rudder, tail plane and elevators c) The wings, incl uding t he ailerons 184. At what altitu de does str atosphere commence approximately? a) Sea level b) 63,000 ft # c) 36,000 ft 185. When an aircraft is in s traight and level unaccelerated flight, whic h of t he followin g is correct? # a) Lif t and weight are equal, and thr ust and drag are equal b) Lift g reater than weight, and thr ust greater than drag c) Lift gr eater than weight, and thrust is less th an drag 186. As the angle of attack is incr eased (up to the stall poin t), which of t he followin g is correct? a) Pressure difference between top and bott om of the wing i ncreases b) Lift i ncreases



#

c) Bot h a) and b) are cor rect

187. The fin gives st ability about w hich axis? a) Lateral axis # b) Normal axis c) Longitudinal axis 188. What is th e horizontal movement of t he nose of the aircraft c alled? a) Rolling movement b) Pitchi ng movement # c) Yawi ng mov ement


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Page 22 - Mod 8 189. What type of d rag, depends on t he smoothness o f th e body, and surface area over whi ch the air flows? a) Parasite dr ag b) Form drag # c) Skin fric tion drag 190. if th e nose of the aircr aft is rot ated about its lateral axis, what is its di rectional movement? a) Turning to th e left or r ight b) Rolling o r banking to the left or ri ght # c) Climbing or diving 191. When air flow velocity over an upper c ambered sur face of an aerofoil d ecreases, what takes place? # a) Pressure inc reases, lif t decreases b) Pressure increases, lif t i ncreases c) Pressure decreases, lift increases 192. When an aircraft stalls a) lift and dr ag increase b) lift increases and drag decreases # c) lift decreases and drag incr eases 193. Wing loading i s a) the maximum all up weight multi plied by th e total wing area # b) the maximum all up weight divided by the total wing area c) the ratio of t he all up weight of the aircraft t o its basic weight 194. An aircraft wi ng with an aspect ration of 6:1 is pr oporti onal so that a) the mean chor d is si x tim es the thickness # b) the wing span is six times the mean chord c) the wing area is six ti mes the span



195. Upward and outw ard incli nation of a mainplane is t ermed a) sweep # b) dih edral c) stagger 196. The functi on of an aircraft fin # a) is to provid e stabilit y about the normal axis b) is to provide directional control c) is to provide straight airflow across t he rudder 197. Movement of an aircraft about its normal axis a) is pitching b) is rolling # c) is yawing s r e p a P n o i t s e u Q A C G D / b f @ k o o b e c a F n o s u e k i L , ) n i . s r e p a p n o i t s e u q a c g d . w w w (

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Page 23 - Mod 8 198. A pressure of one atmosphere is equal to # a) 14.7 psi b) 100 millibar c) 1 inch Hg. 199. The milli bar is a uni t of a) atmos pheric temperature b) pressure altitude # c) barometric pressure 200. With an increase in altitude und er I.S.A. condi tions the temperature in th e troposp here a) increases # b) decreases c) remains c onstant 201. Which of t he followi ng forc es act on an aircraft i n level flight? a) Lift, thr ust, and weight # b) Lift, thrus t, weight, and drag c) Lift, drag, thru st 202. When an aircraft is banked, the horizontal com ponent of the lift # a) will tend to make the aircraft foll ow a circu lar path b) will oppose the tendency of t he aircraft t o follow a circular path c) will oppose the weight thus requiring more total lift in the turn 203. If, after a disturbance, an aeroplane initially return s to its equil ibriu m st ate a) it h as neutral stability # b) it has static stability and may be dynamically stable c) it is neutrally unst able



204. Stability of an aircraft i s # a) the tendency of the aircraft to return to its origin al trimm ed positi on after having been displaced b) the abilit y of t he aircr aft to rot ate about an axis c) the tendency of the aircraft to st all at low airspeeds 205. With reference to altimeters QFE is # a) setting aerodrom e atmospheric pressure so that an altimeter reads zero on landing and take off b) quite fine equipment c) the manufactur ers registered name


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206. Under the ICAO “ Q” code there are which t hree settin gs? # a) QFE, QNH, QNE b) QEF, QNH, QEN c) QE, QN, QQE Page 24 - Mod 8 207. Wing loading is # a) GROSS WEIGHT divi ded by GROSS WING AREA b) WING AREA x WING CHORD c) the ultimate tensile strength of the wing 208. The three axes conc erned with stability of an aircraft have a) normal axis thr ough C of G. Lateral axis - wing tip t o wing t ip. Longit udinal axis - nose to tail but not thr ough C of G # b) longit udinal, lateral and normal axis all passing through aircraft centre of gravity c) longitud inal axis nose to tail, lateral axis at furt hest span point, normal axis thro ugh centre of pressur e 209. A barometer indicates # a) press ure b) density c) temperature 210. If an aircraft returns to a position of equilib rium it is s aid to be a) negatively stable b) neutrally st able # c) positi vely stable 211. The pendulum effect on a high wi ng aircraft # a) inc reases lateral stabi lit y b) decreases lateral stabili ty c) has no effect on lateral stabilit y 212. The amount of w ater vapour in t he air (humidi ty ho lding capacity of t he air) is a) greater on a colder day, and lower on a hotter day



#

b) greater on a hotter day and lower on a colder day c) doesn't have a signif icant dif ference

213. Weight is equal to a) volume x gravity # b) mass x acceleration c) mass x gravit y 214. Indu ced Drag a) increases with an increase in speed b) reduces with an inc rease in angle of attack # c) increases with increase in aircraft weight


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215. Airflow o ver the upper surf ace of the wing generally # a) flows towards the root b) flows towards the tip c) flows str aight from leading edge to tr ailing edge Page 25 - Mod 8 216. with an increase in aspect ratio f or a given ISA, induced drag will a) remain cons tant b) increase # c) reduc e 217. With i ncreasing altitud e the angle at which a wing will stall # a) remains the same b) reduces c) in creases 218. If t he density of the air is in creased, the lift w ill # a) inc rease b) decr ease c) remain th e same 219. All the factors that affect th e lift pr oduced by an aerofoil are a) angle of attack, air density, velocit y, wing area b) angle of attack, air temperature, veloci ty, wi ng area # c) angle of attack, velocity, wing area, aerofoi l shape, air density 220. A wing section su itable for hig h speed would be a) thic k with hi gh camber b) thin with high camber # c) thin with little or no camber 221. The induced drag of an aircraft a) increases with increasing s peed b) increases if aspect r atio is i ncreased



#

c) decreases wit h increasing speed

222. As the speed of an aircr aft inc reases the prof ile drag # a) inc reases b) decreases c) decreases at firs t t hen increase 223. The stagnation poin t on an aerofoil is t he point wh ere a) the suct ion p ressure reaches a maximum b) the boundary layer changes from laminar to tur bulent # c) the airflow is brought completely to rest


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224. After a distur bance in pitch, an aircraft conti nues to osci llate at cons tant amplitude. It is a) longit udinally uns table # b) longi tudin ally neutrally stable c) laterally unstable

Page 26 - Mod 8 225. On an aircraft wit h an all-moving tailpl ane nose up pit ch is caused by a) increasing tailplane incidence # b) decreasing tailplane incidence c) up movement of th e trim tab 226. The stalling of an aerofoil is affected by the a) airspeed # b) angle of attack c) transition speed 227. What gives th e aircraft direction al stability? # a) Verti cal stabi lizer b) Horizontal st abilizer c) Elevators 280. The most fu el effici ent of the foll owing t ypes of engine is th e a) rocket b) turbo -jet engine # c) turb o-fan engine 229. The quietest of t he followi ng types of engine is the a) rocket b) turbo -jet engine # c) turbo -fan engine 230. Forward mot ion of a glider is prov ided by



#

a) the engine b) the weight c) the drag

231. Profil e drag consists of what drag types? # a) Form, skin fricti on and interference b) Form, induced and skin frict ion c) Form, induced and i nterference 232. An aircraft in str aight and level fligh t is subj ect to a) zero load factor # b) a load facto r of 1 c) a load factor of ½ 233. Aspect ratio i s given by th e formula s a) Mean Chord r e Span p a 2 P # b) Span n o Area i t s c) Span 2 e u Mean Chor d Q U

U

A C G D / b f @ k o o b e c a F n o s u e k i L , ) n i . s r e p a p n o i t s e u q a c g d . w w w (

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U

U

Page 27 - Mod 8 234. on a high wing aircraft in a turn a) the up goin g wing l oses lift w hich has a de-stabilizing effect # b) the down going wing gains lift causing a stabilizing effect c) the down going wing l oses lift c ausing a de-stabilizing effect 235. Which cond ition is th e actual amount of water vapour in a mixture of air and water? a) Relative hu midit y b) Dew p oint # c) Absolut e humidi ty 236. An aspect r atio of 8 means # a) the span is 8 times the mean chord b) the mean chor d is 8 tim es the span c) the area is 8 tim es the span 237. The ISA a) is t aken from the equator # b) is taken from 45 degrees latitude c) assumes a standard day 238. Which will weigh the l east? a) 98 parts of dr y air and 2 parts of w ater vapour # b) 35 parts of dry air and 65 parts of water vapour c) 50 parts of dry air and 50 parts of water vapour



239. A high aspect ratio w ing a) is st iffer than a low aspect ratio wing # b) has less induced drag than a low aspect ratio wing c) has a higher stall angle than a low aspect ratio wi ng 240. The thrust -drag couple overcomes the lif t-weight coupl e. What for ce must t he tail of t he aircraft exert to maintain the aircraft in a level attitude? a) Down # b) Up c) Sideways


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241. Induced downwash # a) reduces the effective angle of attack of the wing b) increases the effective angle of attack of the wing c) has no effect on the angle of attack of the wing 242. during a tu rn, the stalli ng angle a) increases b) decreases # c) remains the same Page 28 - Mod 8 243. Which i s the ratio of the water vapour actually present in t he atmosp here to the amount that woul d be present if t he air were saturated at the prevailin g temperature and pressur e? a) Absolut e humidity # b) Relativ e humi dit y. c) Dew p oint 244. a straight rectangular wing, witho ut any twis t, will a) have greater angle of attack at the tip b) have the same angle of attack at all point s along the span # c) have less angle of attack at the tip 245. If gauge pressu re on a standard day is 25 PSI, the absolut e pressur e is a) 10.3 PSI b) 43.8 PSI # c) 39.7 PSI 246. The C of G moves in fli ght. The most l ikely cause of this is a) movement of passengers b) movement of cargo # c) consum ption of fuel and oils 247. The speed of sound in the atmosphere a) varies accor ding to the frequency of th e sound # b) chang es wit h a change in temperatur e c) changes with a change in pressur e



248. A str aight rectangular wing, without any twist, will a) stall firs t at the tip # b) stall firs t at the root c) stall equally along t he span of the wing 249. What is s ea level pr essur e? # a) 1013.2 mb b) 1012.3 mb c) 1032.2 mb


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250. Which atmospheric c onditi ons wil l cause the true landing speed of an aircraft to be the greatest? a) Low temperature with l ow humid ity b) High temperature with low humi dity # c) High temperature with high humidi ty 251. Which condi tion is the actual amount of water vapour in a mixture of air and water? a) Relative hu midit y b) Dew point # c) Absolut e humidit y Page 29 - Mod 8 252. When the weight of an aircr aft incr eases, the minimum drag speed a) decreases # b) inc reases c) remains the same 253. Which statement concernin g heat and/or temperature is true? a) There is an inverse relationship between temperature and heat. # b) Temperature is a measure of the kinetic energy of the molecules of any substance c) Temperature is a measure of t he potential energy of the molecules of any su bstance 254. Which is the ratio of the water vapour actually present in the atmosphere to the amount that woul d be present if t he air were saturated at the prevailing temperature and pressur e? a) Absolut e humidity # b) Relative humidi ty c) Dew p oint 255. When an aircraft experiences induced drag # a) air flows under the wing spanwise towards the tip and on top of the wing spanwise towards the root b) air flow s under the wing spanwise towards the root and on top o f the wing spanwise towards the tip c) Neither a) or b) since ind uced drag does not cause spanwise flow 256. What is absolute humi dity?



a) The temperature to which humid air must be cooled at constant pressure to become saturated. # b) The actual amount of the water vapour in a mixt ure of air and water c) The ratio of the water vapour actually present in the atmosphere to th e amount that would be present if the air were saturated at the prevailing t emperature and pressure 257. Which atmospheric c ondit ions wi ll cause the true landing speed of an aircr aft to be the greatest? a) Low temperature with l ow humidi ty b) High temperature with low humi dity # c) High temperature with high humidi ty


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258. If all, or a significant part of a stall strip i s miss ing on an aeroplane wing, a likely result will be a) increased lift in t he area of installation on t he opposite wing at high angles of attack b) asymmetri cal aileron con trol at low angles of attack # c) asymmetrical aileron contro l at or near stall angles of attack

Page 30 - Mod 8 259. When a leading edge slat opens, there is a gap between the slat and the win g. This is a) to allow it to retract back into the wing # b) to allow air through to re-energize the boundary layer on top of the wing c) to k eep th e area of the win g th e same 260. An aeroplane wing is designed to pro duce lift r esulting f rom relatively a) posit ive air pressure below and above the wing's surf ace. b) negative air pressure below t he wing's surface and positi ve air pr essure above the wing's surface. # c) positive air pressure below the wing' s surface and negative air pressur e above the wing's surface 261. Aspect r atio of a wing is defined as the ratio of t he a) wing span to the wing root b) square of the chord t o the wingspan # c) wing span to the mean chord 262. Which of t he followin g is tr ue? a) Lift acts at right angles to the wing chord li ne and weight acts vertically dow n # b) Lift acts at right angles to the relative airflow and weight acts verti cally down c) Lift acts at right angles to the relative air flow and weight acts at right angles to the aircraft centre lin e 263. The temperature to w hich humid air must be cooled at const ant pressure to become saturated is c alled # a) dewpoi nt b) absolute humidity



c) relative humidi ty 264. The airflow o ver the upper surface of a cambered wing a) increases in velocity and pressure # b) increases in velocity and reduces in pressure c) reduces in velocity and inc reases in pressure 265. Which type of flap inc reases the area of the wing? a) Plain Flap # b) Fowler Flap c) All flaps


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Page 31 - Mod 8 266. If all, or a significant part of a stall strip i s miss ing on an aeroplane wing, a likely result will be a) increased lift in th e area of installation on t he opposite wing at high angles of attack b) asymmetric al aileron cont rol at low angles of attack # c) asymmetrical aileron control at or near stall angles of attack 267. With incr eased speed in l evel f light a) induced drag in creases # b) profi le drag incr eases c) profile drag remains co nstant 268. Deployment of flaps will result in # a) a decrease in stall angl e b) an increase in stall angle c) a decrease in angl e of attack 269. An aeroplane wing is designed to prod uce lift r esulting f rom relatively a) posit ive air pressure below and above the wing's surf ace. b) negative air pressure below t he wing's su rface and positi ve air pr essure above the wing's surface. # c) positive air pressure below the wing' s surface and negative air pressure above the wing's surface. 270. The angl e of attack of an aerof oil sect ion is t he angle between the # a) chord line and the relative airflow b) underside of t he wing sur face and the mean airflow c) chord l ine and the centre line of the fu selage 271. A swept win g tends to s tall fir st at the a) root



#

b) tip c) centre section

272. Krueger Flaps are normally f itted t o a) the trailing edge of t he wings b) the tips of the wings # c) the leading edge of the wing s 273. Aspect r atio of a wing is defined as the ratio of t he a) wing span to the wing r oot. b) square of the chord to the wingspan. # c) wing span to the mean chord


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274. The trailing vortex o n a point ed wing (taper r atio = 0) is # a) at the roo t b) at the tip c) equally all along the wing span Page 32 - Mod 8 275. A high wing aircr aft will b e more # a) laterally stable than a low wing aircraft b) longitudi nally stable than a low wing aircraft c) directionally st able than a low win g aircraft 276. A wing w ith a very high aspect ratio (in com parison wit h a low aspect ratio wing) will have a) increased drag at high angles of attack. # b) a hig h stall speed. c) poor cont rol qualiti es at low airspeeds. 277. The lift curve for a delta wing is a) more steep than that of a hig h aspect ratio win g # b) less steep than that of a high aspect ratio wing c) the same as that of a high aspect ratio wi ng 278. after an aircraft has been dist urbed from its st raight and level flight, it returns t o its origi nal attit ude with a small amount of decreasing oscillation. The aircraft is a) statically st able but d ynamically unst able b) statically unstable but dynamically stable # c) statically stable and dynamically stable 279. An increase in the speed at whic h an aerofoi l passes thr ough t he air i ncreases lif t because # a) the incr eased speed of the airfl ow creates a greater pressure diff erential between the upper and lower sur faces. b) the incr eased speed of the airflow creates a lesser pressur e differential between th e upper and lower sur faces. c) the increased velocit y of the relative wind inc reases th e angle of attack



280. A delta win g has # a) a higher stall angle than a straight wing b) a lower stall angle than a straight wi ng c) the same stall angle than a straight w ing 281. The Lift/Drag ratio of a wing at t he stalling angle is a) of a negative value # b) low c) high 282. The airflow o ver the upper surface of a cambered wing a) increases in velocit y and pressure # b) incr eases in veloci ty and reduces in pressure c) reduces in veloci ty and inc reases in pressure s r e p a P n o i t s e u Q A C G D / b f @ k o o b e c a F n o s u e k i L , ) n i . s r e p a p n o i t s e u q a c g d . w w w (

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Page 33 - Mod 8 283. The speed of air over a swept wing w hich co ntri butes to t he lift is # a) less than the aircraft speed b) more than the aircraft sp eed c) the same as the aircraft speed 284. For a given angle of attack induced drag is a) greater on a high aspect ratio wi ng b) greater towards the wing r oot # c) greater on a low aspect ratio wing 285. In st raight and level fligh t, the angle of attack of a swept wi ng is a) the same as the aircraft angle to the horizontal b) more than the aircraft angle to t he horizontal # c) less than the aircraft angle to the horizontal 286. Induc ed drag a) is never equal to the prof ile drag b) is equal to the profile drag at the stalling sp eed # c) is equal to the profil e drag at Vmd 287. A delta wing aircr aft fl ying at the same speed (subso nic) and angle of attack as a swept wing aircraft of si milar wing area will pr oduce a) the same lift b) more lift # c) less lift 288. The stagnation po int is # a) static pressure plus dynamic pressure



b) static pressure minus dynamic pressure c) dynamic pressure only 289. On a swept w ing aircraft, due to t he adverse pressur e gradient, the boundary layer on the upper surface of the wing tends to fl ow a) directly from leading edge to trailing edge # b) towards the tip c) towards the root 290. With incr eased speed in l evel f light a) induced drag i ncreases # b) profi le drag incr eases c) profile drag remains co nstant


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291. If a swept win g stalls at th e tips firs t, the aircr aft will # a) pitch nose up b) pitch nose down c) roll

Page 34 - Mod 8 292. The thickness/chord ratio of t he wing is also know n as a) aspect ratio b) mean chord ratio # c) fineness ratio 293. Flexure of a rearward swept wi ng wi ll a) increase the lift and hence incr ease the flexure # b) decrease the lif t and hence decrease the flexu re c) incr ease the lif t and hence decrease the fl exure 294. A High Aspect Ratio wing is a wing w ith a) long sp an, long cho rd # b) long span, short chord c) short span, long chord 295. Stall comm encing at t he root is pr eferred because a) the ailerons become ineffective # b) it provides the pilot with a warning of complete loss of lift c) it will cause the aircr aft to pitc h nose up 296. An aircraft flying in “ ground effect” will produce # a) more lift than a simil ar aircraft outsi de of ground effect b) less lift than a similar aircraft outsi de of ground effect c) the same lift as a simil ar aircraft outsi de of ground effect 297. If th e angle of attack of a wing is increased in flig ht, the



#

a) C of P will move forward b) C of G will mov e aft c) C of P will mov e aft

298. The Rams Horn Vortex on a forw ard swept wi ng wi ll be a) the same as a rearward sw ept wi ng b) more than a rearward swept wi ng # c) less than a rearward swept wing 299. When maintaining l evel f light an increase in speed will # a) cause the C of P to move aft b) cause the C of P to m ove forward c) have no affect on t he position of th e C of P


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300. For a cambered wing s ection t he zero l ift angle of attack wi ll b e a) zero b) 4 degrees # c) negative 301. Density changes with altitude at a rate a) of 2kg/m 3 per 1000ft # b) which changes with altitude c) which is const ant until 11km Page 35 - Mod 8 302. Airflow at s ubsonic speed is taken to be a) compressible # b) incom pressible c) either a or b depending on altit ude 303. Bernoull i's equation show s that a) at constant velocit y the kinetic energy of t he air ch anges with a change of height b) with a change in speed at const ant height bot h kinetic and potential energies change # c) with a change in veloci ty at const ant height the static pressure will change 304. If fluid f low t hrough a venturi i s said to b e incompressibl e, the speed of t he flow incr eases at the throat to # a) maintain a constant volume flow rate b) allow f or a reducti on in static pr essure c) allow for an increase in static pressur e 305. to produc e lift, an aerofo il mu st be a) asymmetrical b) symmetrical # c) either a or b above 306. Lift is dependent on # a) the area of the wing, the density of t he fluid medium, and the square of the velocity



b) the net area of the wing ,the density of the flui d medium and the velocity c) the frontal area of th e wing, the density o f th e fluid medium and the velocity 307. The maximum lif t/drag ratio of a wing occu rs a) at the angle of attack where the wing develops it s maximum lift b) during take off # c) at an angle below which the wing develops max lift 308. A wing develop s 10,000N of lif t at 100knots . Assumi ng the wing remain s at the same angle of attack and remains at the same altitu de, how much l ift w ill it develop at 300knot s? a) 900,000 N # b) 90,000N c) 30,000N


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309. The angle of attack i s a) related to angle of incidence b) always kept b elow 15 degrees # c) not related to the angle of incidence Page 36 - Mod 8 310. The 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 curved 311. If t he C of G is calculated after loading as withi n limi ts f or take off a) no furt her calculation is required # b) a furt her calculation is required prior to landing to allow for fuel and oil consum ption c) a furt her calculation is r equired prior to landing to allow for flap deployment 312. A stalled aerofoi l has a lif t/drag ratio a) more than the lift/drag ratio pr ior t o stall b) zero # c) less than the lift /drag ratio prior to stall 313. At low forward speed a) increased dow nwash r educes tailplane effectiveness # b) increased downwash increases tailplane effectiveness c) excessive rudd er movement may cause fin to stall 314. Helicopter rot or bl ades cr eate lift by # a) creatin g low pressure above the blades b) pushing th e air down c) working li ke a screw 315. On som e modern aircraft a stall warning will automatically



a) increase thrus t b) extend outb oard slats # c) cause a pitch nose down movement 316. above 65,800 ft temperatu re a) remains c ons tant u p to 115,000ft b) decr eases by 1.98oC up to 115000ft # c) inc reases by 0.303oC up to 115000ft 317. At sea level, ISA atmospheric pressure is # a) 14.7 PSI b) 14.7 Kpa c) 10 Bar


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318. The spanwise component o f the airflow is a) greater at hig her speeds # b) less at hig her speeds c) unaffected by sp eed Page 37 - Mod 8 319. A wing fence a) increases lateral contr ol b) acts as a lift dumpi ng device # c) reduces spanwise flow on a swept wing thus reducing induced drag 320. The highest lift /drag ratio i s gr eatest at a) low altitudes b) the point just before the stalling angle # c) the optimu m angle of attack 321. With all condit ions remaining the same, if t he aircraft speed is halved, by what factor is the lift reduced? a) Half # b) By a factor of 4 c) Remains t he same 322. The boundary layer over an aerofoil is a) a layer of air c lose to t he aerofoil t hat is st ationary # b)a layer of air close to the aerofoi l which is moving at a velocity less than free stream air c) a layer of turbu lent air close to th e aerofoil whi ch is m oving at a velocity l ess than free stream air 323. on a swept wing aircraft, t he fineness ratio of an aerofoil i s a) highest at th e root # b) highest at the tip c) equal throu ghout t he span



324. IAS for a stall w ill a) incr ease with altit ude b) decrease with altitude # c) rough ly remain the same for all altitude 325. If the radius of a turn is reduced the load factor will # a) inc rease b) decrease c) remain the same 326. Streamlini ng will reduce # a) fo rm drag b) induced drag c) skin friction drag s r e p a P n o i t s e u Q A C G D / b f @ k o o b e c a F n o s u e k i L , ) n i . s r e p a p n o i t s e u q a c g d . w w w (

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327. If an aircraft has a gross w eight of 3000 kg and i s th en subjected to a total weight of 6000 kg the load factor wil l be # a) 2G b) 3G c) 9G Page 38 - Mod 8 328. A constant r ate of climb i s determined by a) weight b) wind speed # c) excess engine pow er 329. Ice form ed on th e leading edge will cause the aircraft to a) stall at the same stall speed and AoA b) stall at a low er speed # c) st all at a hig her speed 330. With an aircraft in bank, the upper wing pr oduces mor e drag. To com pensate # a) the rud der is operated b) when bank angle is achieved th en the ailerons are operated in the oppos ite direction to cause the opposit e effect c) angle of attack is incr eased 331. on a high wi nged aircraft in a banked turn, which of the follow ing are true? a) The down-going w ing los es lift causin g a stabilizing effect # b) The up-going wing loses lift causing a stabilizing effect c) The wing dihedral causes a stabili zing effect 332. If an aircr aft true airspeed is halved, its indi cated airspeed is reduced by # a) half b) factor of four c) It is not reduced, it is d oubled



333. If t here is an incr ease of d ensity, what effect w ould there be in aerodynamic dampening? a) None b) Decreased # c) Increased 334. As Mach n umber incr eases, what is t he effect on bo undary layer? # a) Becomes more turbu lent b) Becomes less tur bulent c) Decreases i n t hickness 335. When a slat i s retr acted it m oves # a) towards the upper leading edge of the wing b)towards the low er leading edge of t he wing c) towards the center of th e leading edge of t he wing s r e p a P n o i t s e u Q A C G D / b f @ k o o b e c a F n o s u e k i L , ) n i . s r e p a p n o i t s e u q a c g d . w w w (

336. In a turn the up-going w ing causes a a) de-stabilizing effect du e to in creased AoA b) de-stabilizing effect due to decreased AoA # c) stabilizing effect due to decreased AoA Page 39 - Mod 8 337. The stagnation point consis ts of # a) dynamic and static air pressure b) static air pressure c) dynamic air pressure

g a P

342. As the angle of attack i ncreases th e centre of pr essure will a) move rearward

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338. During a glide the follow ing f orces act on an aircr aft a) lift , weight, thr ust # b) lift , drag, weight c) lift and weight only 339. Yawing is a r otation around a) the normal axis obt ained by the elevator b) the lateral axis obtained by t he rudder # c) the normal axis obtained by the rudder 340. If an aileron is moved dow nward a) the stalling angle of that wing is i ncreased # b) the stalling angle of that wing is decreased c) the stalling angle is not affected but the stalling speed is decreased 341. If the wing loading of an aircr aft were reduced the stalling speed woul d a) inc rease # b) decrease c) not be affected



#

b) remain static c) move forward

343. The lift on a wing is incr eased with # a) an incr ease in pressure b) an incr ease in humidi ty c) an increase in temperature 344. An aircr aft entering a level t urn wil l require more lif t a) only if there is an inc rease in speed b) only if there is an incr ease in angle of attack # c) in all cases


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345. Lateral stability is r educed by inc reasing # a) Anhedr al b) Dihedral c) Sweepback

Page 40 - Mod 8 346. Pulling the contro l column and rotating to the left causes a) elevator down, left aileron down # b) elevator up, left aileron up c) elevator down , left aileron up 347. Azimut h stabili ty is dependent on a) dihedral b) tailplane # c) keel and fi n 348. If the aircraft is sli pping i n turn a) the bank angle is too great # b) the bank angle is too small c) the nose of the aircraft is to o low 349. in normal flig ht con diti ons, an increase in aircraft speed a) causes the nose of t he aircr aft to dr op # b) causes the nose of the aircraft to lift c) the nose remains in the same posit ion 350. An aircr aft sideslips . What helps t o restore th e aircraft? a) Fin gives rol ling m ovement # b) Dihedral causes the aircraft to roll str aight and the fin increases the yaw rate c) Tailplane 351. For an aircraft cl imbin g at a constant IAS the Mach num ber will


Dgca Module 8 Full

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