STALLING AND STALLING SPEED – Air – DGCA Question Bank For Politics

#1. What % of CL max would a wing produce when flying at 1.3 Vs?

77%

59%

120%

98%

#2. What is the relationship in straight and level flight between the CL at any given speed and CL Max?

CL = 100% Cl Max

CL = CL Max (1/(V/VS)) x 100%.

CL = CL Max (Vs²/V²) x 100%.

CL = CL Max (V/VS) x 100%.

#3. If the C of G is moved forward what will be the effect on stalling speed?

No effect

Increase

Decrease

Increase or decrease depending on aircraft weight

#4. If the C of G of an aircraft is moved forward what will be the effect on longitudinal, directional and lateral stability?

No effect on longitudinal, increase lateral and directional.

Increase longitudinal and lateral, no effect on directional.

Decrease lateral, increase directional and longitudinal.

Increase longitudinal and directional, no effect on lateral.

#5. If the C of G is moved forward what will be the effect on longitudinal, directional and lateral manoeuvrability.

No effect on any.

Increase lateral, decrease longitudinal and directional.

Decrease lateral and directional, increase longitudinal.

Decrease longitudinal and directional, no effect on lateral.

#6. If the weight of an aircraft is doubled what will be the effect on its stalling speed?

It will be doubled.

It will be halved.

It will be increased by approximately 41 %.

It will be increased by approximately 50%.

#7. A JAR certificated commercial passenger aircraft is flying in straight and level flight when the stall warning system activates the stick shaker. What will be its CL as a percentage of CL Max?

81%

85%

91%

95%

#8. Which of the following statements are true of an aircraft as it climbs to high altitude at constant IAS?

Its TAS will increase as a proportion to its IAS until it reaches Merit

Its indicated stalling speed will increase throughout most of the climb then reduce as it reaches Merit

Its indicated stalling speed will decrease throughout most of the climb then increase as it reaches Merit

Its indicated stalling speed will remain constant throughout most of the climb then increase as it reaches Merit

#9. The sketch below represents a typical whole aircraft L:D polar diagram. Which of the points marked on it correspond to the low speed stall condition?

A

B

C

D

#10. The sketch below represents a typical whole aircraft L:D polar diagram. Which of the points marked on it correspond to the best L:D ratio and at what speed does this occur?

A

B

C

D

#11. Which of the following represents the relationsltip between the design manoeuvre speed (VA) and the straight and level lg stalling speed (Vs1g)?

VA = Vs1g (N limit).

Vs1g = VA (n Limit)

VA = Vs1g (n Limit)

Vs1g = VA (n Limit)

#12. If the zero lift angle of attack and stalling angle of attack for a particular aerofoil section are -4 degrees and 16 degrees respectively, what will be its CL as a percentage of CLM ~ w, hen the angle of attack is 6 degrees?

70%

60%

50%

40%

#13. In straight and level flight the CL of an aerofoil is 0.44. If a 1 degree increase in angle of attack gives an increase of 0.06 in CL what will be the load factor when subjected to an angle of attack increase of 5 degrees?

1.58

1.68

1.78

1.98

#14. An JAR certificated passenger aircraft has a CL Max of 2 and a lg (straight and level) stalling speed of 100 Kts. What will be its 2.5g stalling speed?

138 Kts

148 Kts

158 Kts

168 Kts

#15. Which of the following best defines VA for a JAR certified passenger aircraft?

The Design Manoeuvre Speed which is the maximum EAS at which full nose up control deflection can be employed without exceeding a load factor of 2.5.

The Design Manoeuvre Speed which is the maximum TAS at which full nose up control deflection can be employed without exceeding a load factor of 3.75.

The Design Manoeuvre Speed which is the maximum EAS at which a load factor of 2.5 can be achieved without stalling the aircraft

The Design Manoeuvre Speed which is the minimum EAS at which full nose up control deflection can be employed without exceeding a load factor of 2.5.

#16. What will be the effect of increasing altitude on the TAS at which an aircraft will stall assuming weight and load factor remain unchanged?

Increases

Remains unchanged provided speed does not approach Merit.

Remains unchanged regardless of actual speed.

Decreases.

#17. Which of the following will give the smoothest ride in gusty conditions?

Low aspect ratio straight wing with flaps down.

High aspect ratio straight wing with flaps down.

Low aspect ratio swept wing flaps up.

High aspect ratio swept wing with flaps up.

#18. Which of the following configurations is best suited to flight in gusty conditions?

Flaps up.

Flaps in landing configuration.

Flaps and landing gear down.

Flaps up and landing gear down.

#19. If an aircraft stalls at 200 kts in a 3g pull up what will its stalling speed be in straight and level flight?

67 Kts.

77 Kts

115 Kts.

125 Kts

#20. If CL = 2.5, CD1 = 0.35, What is the aspect ratio?

2.27.

4.27.

5.7.

6.7.

#21. If CDl = 0.6, A = 4, What is CL?

1.75.

2.75.

3.75.

4.75.

#22. If aircraft weight is doubled by what % will stalling speed increase?

41%

141%

241%

341%

#23. If stalling speed in a 3g pull up is 100 Kts what is the maximum bank angle in level flight at 100 Kts?

50.5 Degrees.

60.5 Degrees.

70.5 Degrees.

80.5 Degrees.

#24. What angle of bank will produce limiting load factor in a JAR certificated passenger aircraft?

46 Degrees.

56 Degrees.

66 Degrees.

76 Degrees.

#25. If Vs at a weight of 20000 Kg is 100 Kts what will Vs be at a weight of 60000 Kg?

143 Kts.

153 Kts.

163 Kts.

173 Kts.

#26. If stalling speed in straight and level flight is 100 Kts what will it be in a 30 degree banked level turn?

97 Kts.

107 Kts.

117 Kts.

127 Kts.

#27. Which of the following aircraft is most likely to suffer wing drop in the event of a single engine failure?

A twin propeller aircraft in the climb out.

A four engine propeller aircraft in the cruise.

A twin jet in the climb out.

A four engine jet in the cruise.

#28. What effect does propeller slipstream have on the stalling speed of an aircraft? 1. By increasing airspeed over the wing it decreases stalling speed. 2. By providing the same effect as a boundary layer control system it increases the value of CLMax.

1 only is true.

1 and 2 are true.

2 only is true.

Neither 1 nor 2 are true.

#29. If stalling speed in a 15° bank is 100 Kts what will it be in a 60° bank?

119 Kts.

129 Kts.

139 Kts.

149 Kts.

#30. What causes a swept wing to pitch up at the stall?

Turbulent boundary layer.

Flaps and slats.

Tip stall.

Chordwise flow.

#31. Correct stall and spin recovery action is?

Minimum power, use ailerons to arrest roll, and stick forward to bring the nose down.

Maximum power, use ailerons to arrest roll, and stick forward to bring the nose down.

Maximum power, stick in laterally neutral and fully forward, maximum opposite rudder to arrest yaw.

Maximum power, Stick longitudinally neutral and full lateral deflection to arrest roll and yaw.

#32. What happens to the C of P of a swept back wing and a straight wing respectively in a stall?

Moves aft and forward respectively.

Both move aft.

Both move forward.

Moves forward and aft respectively.

#33. Iiow does fuel burn affect the low speed buffet?

Increases speed.

Decreases speed.

No change in speed.

Increase or decrease depending on angle of attack.

#34. What is the highest permitted speed for the commencement of low speed buffet in a JAR certificated passenger aircraft?

VS.

1.05 Vs.

1.2 vs

1.3Vs.

#35. What is the stalling speed in a 1.5g banked turn?

Vslg √ (l.5).

VsI.sg √ ( COSAOB).

VsI.sg √ ( 1/COSAOB).

VsIg √ (1/1.5).

#36. An aircraft weight 24000 N stalls at 150 Kts. At what speed will it stall at a weight of 48000 N?

212 Kts.

222 Kts.

232 Kts.

242 Kts.

#37. How is VA calculated from Vslg?

VA = VsIg √ ( n Limit).

VA = VsIg ( n).

VA = Vs2.5g √ ( 1/n Limit).

VA = Vs2.5g √ ( n ).

#38. Deep stall is most probable with?

Ventral fin.

Canards.

High tailplane.

Swept back wings.

#39. Deep stall is most probable with?

Ventral fin.

Canards.

High tailplane.

Low tailplane.

#40. In a constant IAS climb?

Stalling TAS is constant.

Stalling IAS is constant.

Stalling TAS is constant before decreasing at high altitude.

Stalling IAS is constant before increasing at high altitude.

#41. C of G on the aft limit will?

Increases stalling speed but leave stalling angle unchanged.

Decrease stalling speed but leave stalling angle unchanged.

Increase stalling angle but leave stalling speed unchanged.

Leave both stalling angle and stalling speed unchanged.

#42. Deployment of trailing edge flaps?

Increases stalling speed and angle.

Decreases stalling speed and angle.

Decreases stalling speed but leaves stalling angle unchanged.

Decreases stalling angle but leaves stalling speed unchanged.

#43. At the stall?

Tips of swept back wings stall first, moving C of P inwards and forwards.

Roots of swept back wings stall first, moving C of P outwards and rearwards.

Straight wing tips stall first, moving C of P inwards and forwards.

Straight wing roots stall first, moving C of P aft.

#44. Vortex generators?

Prevent tip stall.

Energise spanwise flow.

Energise shock waves.

Minimise shock induced separation.

#45. Stalling speed is increased by?

Weak longitudinal stability.

Strong longitudinal stability.

Tailplane lift.

Aft C of G.

#46. Canards?

Increase stall speed.

Decrease stall speed.

Do not affect stall speed.

Increase or decrease stall speed depending on C of G position.

#47. With a low thrust line?

Power decreases decrease stalling speed.

Power increases increase stalling speed.

Thrust increases increase stalling speed.

Thrust increases decrease stalling speed.

#48. Turning stalling speed is proportional to?

Load factor.

The angle of bank.

The square root of the load factor.

The square root of the cosine of the angle of bank.

#49. Flaps down in turbulence will?

Increases risk of stall.

Decrease risk of stall.

Not affect risk of stall.

Decrease risk of exceeding limiting load factor.

#50. As flight progresses?

Stalling speed increases.

Stalling speed decreases.

Stalling speed is constant.

Stalling speed increases or decreases with changing C of G position.

#51. If Vs in straight and level flight is 75 Kts what will it be in a 45° bank?

96 Kts.

89 Kts.

116 Kts.

126 Kts.

#52. The stalling speed in the landing configuration is. ..... ?

V MCL.

V SO.

V S1g.

V MCA

#53. If Vsl, is 175 Kts at a weight of 75000 N what will it be at 100000 N?

202 Kts.

222 Kts.

232 Kts.

242 Kts.

#54. If Vs1g, is 175 Kts what will Vs be in a 47 degree level banked turn?

201 Kts.

211 Kts.

221 Kts.

231 Kts.

#55. If Vs in a 47 degree level banked turn is 200 Kts what will it be in a 65 degree level banked turn?

224 Kts.

234 Kts.

254 Kts.

264 Kts.

#56. If Vs1g, is 180 Kts at a weight of 80000 N what wilI it be at 40000 N?

97 KTS.

107 Kts.

117 Kts.

127 Kts.

#57. If VS is 450 Kts at 7g what will Vs1g be?

170 Kts.

180 Kts.

190 Kts.

200 Kts.

#58. If Vs1g is 100 Kts the stick shaker will activate at .........

100 Kts.

105 Kts.

110 Kts.

115 Kts.

#59. If an aircraft stalls in 3g flight at 100 Kts it will stall at ........ in straight and level flight?

48 Kts.

58 Kts.

68 Kts.

78 Kts.

#60. In autorotation the CD of the ....... Wing increases and its CL ........ ?

Up-going Decreases.

Down-going Decreases.

Up-going Increases.

Down-going Increases.

#61. In autorotation the yaw is caused by dissymmetry of drag as the CD of the upgoing wing ....... And that of the down-going wing ....... ?

Increases Decreases.

Increases Increases more.

Decreases Increases.

Decreases Decreases. More.

#62. In autorotation the roll is caused by dissymmetry of lift as the CL of the up-going wing ....... And that of the down-going wing ....... ?

Increases Decreases.

Increases Increases more.

Decreases Increases.

Decreases Decreases more.

#63. In autorotation the ......... wing becomes more stalled whilst the ....... Becomes less so?

Inner Inner.

Inner Outer.

Outer Outer.

Outer Inner.

#64. VA is ........... Vs1g?

138%

148%

158%

168%

#65. Stalling speed in a maximum g manoeuvre at the maximum operating altitude is.......... VS?

94 %

104%

114%

124%

#66. Vso is?

Stalling IAS in take-off configuration.

Stalling EAS in landing configuration.

Stalling TAS in take-off configuration.

Stalling CAS in landing configuration.

#67. The minimum CAS at which an aircraft can develop a lift force equal to its weight at an angle of attack which is not greater than its stalling angle is ..... ?

Vso

Vs1g

V A

V MBE

#68. Which of the following is the lowest flying speed?

Vso.

Vs.

Vs1g.

V AT.

#69. If Vs1g is 175 Kts VA will be ..... ?

246.7 Kts.

256.7 Kts

266.7 Kts.

276.7 Kts

#70. At the aerodynamic ceiling maximum attainable load factor is ... ?

1.

1.3.

1.5.

2.5.

#71. In a climbing turn the ...... wing is likely to stall ..... causing the aircraft to ...... and yaw ..... the turn?

Outer first roll out of.

Outer last pitch in to.

Inner first roll in to.

Inner last pitch out of.

#72. In a descending turn the ...... wing is likely to stall ..... causing the aircraft to ...... and yaw ..... the turn?