STALLING – Air – DGCA Question Bank For Politics

#1. An aeroplane will stall at the same:

angle of attack and attitude with relation to the horizon

airspeed regardless of the attitude with relation to the horizon

angle of attack regardless of the attitude with relation to the horizon

indicated airspeed regardless of altitude, bank angle and load factor

#2. A typical stalling angle of attack for a wing without sweepback is:

4°

16°

30°

45°

#3. If the aircraft weight is increased without change of C of G position, the stalling angle of attack will:

remain the same.

decrease.

increase.

the position of the CG does not affect the stall speed.

#4. If the angle of attack is increased above the stalling angle:

lift and drag will both decrease.

lift will decrease and drag will increase.

lift will increase and drag will decrease.

lift and drag will both increase.

#5. The angle of attack at which an aeroplane stalls:

will occur at smaller angles of attack flying downwind than when flying upwind

is dependent upon the speed of the airflow over the wing

is a function of speed and density altitude

will remain constant regardless of gross weight

#6. An aircraft whose weight is 237402 N stalls at 132 kt. At a weight of 356,103 N it would stall at:

88 kt

162 kt

108 kt

172 kt

#7. For an aircraft with a 1 g stalling speed of 60 kt IAS, the stalling speed in a steady 60° turn would be:

43 kt

60 kt

84 kt

120 kt

#8. For an aircraft in a steady turn the stalling speed would be:

the same as in level flight

at a lower speed than in level flight

at a higher speed than in level flight, and a lower angle of attack

at a higher speed than in level flight and at the same angle of attack

#9. Formation of ice on the wing leading edge will:

not affect the stalling speed.

cause the aircraft to stall at a higher speed and a higher angle of attack.

cause the aircraft to stall at a higher speed and a lower angel of attack.

cause the aircraft to stall at a lower speed.

#10. Dividing lift by weight gives:

wing loading

lift/drag ratio

aspect ratio

load factor

#11. The stalling speed of an aeroplane is most affected by:

changes in air density

variations in aeroplane loading

variations in flight altitude

changes in pitch attitude

#12. Stalling may be delayed to a higher angle of attack by:

increasing the adverse pressure gradient

increasing the surface roughness of the wing top surface

distortion of the leading edge by ice build-up

increasing the kinetic energy of the boundary layer

#13. A stall inducer strip will:

cause the wing to stall first at the root

cause the wing to stall at the tip first

delay wing root stall

re-energise the boundary layer at the wing root

#14. On a highly tapered wing without wing twist the stall will commence:

simultaneously across the whole span.

at the centre of the span.

at the root.

at the tip.

#15. Sweepback on a wing will:

reduce induced drag at low speed.

increase the tendency to tip stall.

reduce the tendency to tip stall.

cause the stall to occur at a lower angle of attack.

#16. The purpose of a boundary layer fence on a swept wing is:

to re-energise the boundary layer and prevent separation.

to control spanwise flow and delay tip stall.

to generate a vortex over the upper surface of the wing.

to maintain a laminar boundary layer.

#17. A wing with washout would have:

the tip chord less than the root chord.

the tip incidence less than the root incidence.

the tip incidence greater than the root incidence.

the tip camber less than the root camber.

#18. On an untapered wing without twist the downwash:

increases from root to tip.

increases from tip to root.

is constant across the span.

is greatest at centre span, less at root and tip.

#19. A wing of constant thickness which is not swept back:

will stall at the tip first due to the increase in spanwise flow.

could drop a wing at the stall due to the lack of any particular stall inducing characteristics.

will pitch nose down approaching the stall due to the forward movement of the centre of pressure.

will stall evenly across the span.

#20. Slots increase the stalling angle of attack by:

Increasing leading edge camber.

delaying separation.

Reducing the effective angle of attack.

Reducing span-wise flow.

#21. A rectangular wing, when compared to other wing planforms, has a tendency to stall first at the:

wing root providing adequate stall warning

wingtip providing inadequate stall warning

wingtip providing adequate stall warning

leading edge, where the wing root joins the fuselage

#22. Vortex generators are used:

to reduce boundary layer separation

to reduce induced drag

to induce a root stall

to counteract the effect of the wing-tip vortices.

#23. A stick shaker is:

an overspeed warning device that operates at high Mach numbers.

an artificial stability device.

a device to vibrate the control column to give a stall warning.

a device to prevent a stall by giving a pitch down.

#24. A stall warning device must be set to operate:

at the stalling speed.

at a speed just below the stalling speed.

at a speed about 5% to 10% above the stalling speed.

at a speed about 20% above the stalling speed.

#25. Just before the stall the wing leading edge stagnation point is positioned:

above the stall warning vane

below the stall warning vane

on top of the stall warning vane

on top of the leading edge because of the extremely high angle of attack.

#26. A wing mounted stall warning detector vane would be situated:

on the upper surface at about mid chord.

on the lower surface at about mid chord.

at the leading edge on the lower surface.

at the leading edge on the upper surface.

#27. The input data to a stall warning device (e.g. stick shaker) system is:

angle of attack only.

angle of attack, and in some systems rate of change of angle of attack.

airspeed only.

airspeed and sometimes rate of change of airspeed.

#28. A stick pusher is:

a device to prevent an aircraft from stalling.

a type of trim system.

a device to assist the pilot to move the controls at high speed.

a device which automatically compensates for pitch changes at high speed.

#29. In a developed spin:

the angle of attack of both wings will be positive

the angle of attack of both wings will be negative

the angle of attack of one wing will be positive and the other will be negative

the down going wing will be stalled and the up going wing will not be stalled

#30. To recover from a spin, the elevators should be:

moved up to increase the angle of attack

moved down to reduce the angle of attack

set to neutral

allowed to float

#31. High speed buffet (shock stall) is caused by:

the boundary layer separating in front of a shockwave at high angles of attack

the boundary layer separating immediately behind the shock wave

the shock wave striking the tail of the aircraft

the shock wave striking the fuselage

#32. In a 30° bank level turn, the stall speed will be increased by:

7%

30%

1.07%

15%

#33. Heavy rain can increase the stall speed of an aircraft for which of the following reasons?

Water increases the viscosity of air

Heavy rain can block the pitot tube, giving false airspeed indications

The extra weight and distortion of the aerodynamic surfaces by the film of water

The impact of heavy rain will slow the aircraft

#34. If the tailplane is supplying a download and stalls due to contamination by ice:

the wing will stall and the aircraft will pitch-up due to the weight of the ice behind the aircraft CG

the increased weight on the tailplane due to the ice formation will pitch the aircraft nose up, which will stall the wing

because it was supplying a download the aircraft will pitch nose up

the aircraft will pitch nose down

#35. Indications of an icing-induced stall can be:

An artificial stall warning device

Airspeed close to the normal stall speed

Violent roll oscillations

Airframe buffet

#36. If a light single engine propeller aircraft is stalled, power-on, in a climbing turn to the left, which of the following is the preferred recovery action?

elevator stick forward, ailerons stick neutral, rudder to prevent wing drop.

elevator stick neutral, rudder neutral, ailerons to prevent wing drop, power to idle.

elevator stick neutral, rudder neutral, ailerons stick neutral, power to idle.

#37. If the stick shaker activates on a swept wing jet transport aircraft immediately after take-off while turning, which of the following statements contains the preferred course of action?

Decrease the angle of attack

Increase thrust

Monitor the instruments to ensure it is not a spurious warning

Decrease the bank angle

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