90.In recovery from a spin:

A. Ailerons should be kept neutral.

C. Ailerons are used to stop the spin.

D. Rudder and ailerons are used against the direction of spin rotation.

91.Stall speed in a turn is proportional to:

C. The square root of the load factor.

92.Stalling speed increases when:

A. Recovering from a steep dive.

B. The aircraft is subjected to minor altitude changes, i.e. 0 to 10 000 ft.

C. The aircraft weight decreases.

93.The angle of attack at the stall:

D. Is not affected by changes in weight.

C. Decreases with decrease in weight.

94.The CP on a swept wing aircraft will move forward due to:

A. Boundary layer fences and spanwise flow.

C. Flow separation at the root due to spanwise flow.

D. Change in wing angle of incidence.

95.The IAS of a stall:

B. May increase with increasing altitude, especially high altitude; forward CG and icing.

A. Increases with high altitude; more flaps; slats.

C. Decreases with forward CG and increasing altitude.

D. Altitude never affects stall speed IAS.

96.Vortex generators:

D. Use free stream flow to increase energy in the turbulent boundary layer.

A. Take energy from the laminar flow to induce boundary layer separation.

B. Use free stream flow to induce laminar flow.

97.What causes a swept wing aircraft to pitch-up at the stall?

A. Negative camber at the root.

B. Separated airflow at the root.

D. Rearward movement of the CP.

98.What causes deep stall in a swept-back wing?

D. Spanwise flow from tip to root on wing upper surface.

99.What does a stick pusher do?

B. Activate at a certain angle of attack and push the stick forward.

A. Activate at a certain angle of attack and pull the control column backwards.

C. Activate at a certain IAS and vibrate the stick.

D. Activate at a certain IAS and push the stick forward.

100.What effect on stall speed do the following have?

D. Decreasing sweep angle decreases stall speed.

A. Increased anhedral increases stall speed.

B. Fitting a ‘T’ tail will reduce stall speed.

C. Increasing sweepback decreases stall speed.

102.What influence does the CG being on the forward limit have on VS and the stall angle?

A. VS increases, stall angle remains constant.

B. VS increases, stall angle increases.

C. VS decreases, stall angle remains constant.

D. VS decreases, stall angle decreases.

103.What is a high speed stall?

C. A stall due to decreasing CLMAX at speeds above M 0.4.

A. Separation of the airflow due to shock wave formation.

B. A stall caused by increasing the load factor (g) during a manoeuvre.

D. Excessive dynamic pressure causing airflow separation.

106.What is the standard stall recovery for a light aircraft?

A. Pitch down, stick neutral roll, correct for bank with rudder.

B. Pitch down, stick neutral roll, correct for bank with aileron.

C. Pitch down, stick neutral, wait for neutral tendency.

D. Pitch down, stick neutral roll, do not correct for bank.

108.When an aircraft wing stalls:

D. A swept-back wing will stall from the tip and the CP will move forward.

A. A swept-back wing will stall from the root and the CP will move aft.

B. A non-swept rectangular wing will stall from the root and the CP will move forwards.

C. A non-swept rectangular wing will tend to stall from the tip and the CP will move backwards.

109.When entering a stall, the CP of a straight rectangular wing (i) and a strongly swept wing (ii) will:

A. (i) move aft (ii) move forward.

110.Which is the most critical phase regarding ice on a wing leading edge?

C. Climb with all engines operating.

D. All phases are equally important.

112.Which of the following aircraft designs would be most prone to super stall?

D. Pod mounted engines beneath the wing.

113.Which of the following combination of characteristics would be most likely make an aircraft susceptible to deep stall?

B. Swept wing and ‘T’ tail.

A. Swept wing and wing mounted engines.

C. Straight wing and wing mounted engines.

D. Straight wing and ‘T’ tail.

117.Which of the following is used to activate a stall warning device?

C. Movement of the stagnation point.

D. A reduction in dynamic pressure.

118.Which of the following would indicate an impending stall?

D. Stick shaker and angle of attack indicator.

A. Stall strip and stick shaker.

B. Stall strip and angle of attack indicator.

C. Airspeed indicator and stick shaker.

119.Which stall has the greatest angle of attack?

B. High speed stall (shock stall).

120.With a swept wing the nose-up phenomena is caused by:

A. Deploying lift augmentation devices.

C. Wing sweep prevents the nose-up phenomena.

121.A slat on an aerofoil:

D. Increases the energy of the boundary layer and increases the maximum angle of attack.

A. Increases the energy of the boundary layer and decreases the critical angle of attack.

B. Increases the wing leading edge radius by rotating forward and down from its stowed position on the bottom side of the wing leading edge.

C. Deploys automatically under the influence of increased stagnation pressure at high angles of attack / low IAS.

122.After take-off why are the slats (if installed) always retracted later than the trailing edge flaps?

D. Because slats extended gives a large decrease in stall speed with relatively less drag.

A. Because VMCA with slats extended is more favourable compared to the flaps extended position.

B. Because flaps extended gives a large decrease in stall speed with relatively less drag.

C. Because slats extended provides a better view from the cockpit than flaps extended.

124.Extending the flaps while maintaining a constant angle of attack (all other factors constant):

A. The aircraft will sink suddenly.

125.For an aircraft flying straight and level at constant IAS, when flaps are deployed the induced drag:

C. Increases or decreases depending on the aircraft.

129.If the angle of attack is maintained constant, what happens to the coefficient of lift when flaps are deployed?

C. Changes with the square of IAS.

D. Remains constant because angle of attack remains the same.

130.In order to maintain straight and level flight when trailing edge flaps are retracted, the angle of attack must:

A. Be increased or decreased depending on type of flap.

D. Stay the same because the lift requirement will be the same.

131.On a highly swept back wing with leading edge flaps and leading edge slats, which device would be fitted in the following possible locations?

B. Slats outboard, leading edge flaps inboard.

A. Slats inboard, leading edge flaps outboard.

C. Alternate leading edge flaps and slats along the wing leading edge.

D. There is no preferred position for these two devices.

POF part 2

Authored by Quang Đinh

World Languages

1st - 5th Grade

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69 questions

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MULTIPLE CHOICE QUESTION

30 sec • 1 pt

81.A jet aircraft flying at high altitude encounters severe turbulence without encountering high speed buffet. If the aircraft decelerates, what type of stall could occur first?

A. Low speed stall.

B. Accelerated stall.

C. Deep stall.

D. Shock stall.

MULTIPLE CHOICE QUESTION

30 sec • 1 pt

82.A swept wing aircraft stalls and the wake contacts the horizontal tail. What would be the stall behaviour?

A. Nose down.

B. Nose up and/or elevator ineffectiveness.

C. Tendency to increase speed after stall.

D. Nose up.

MULTIPLE CHOICE QUESTION

30 sec • 1 pt

83.An aircraft at low subsonic speed will never stall:

A. As long as the CAS is kept above the power-on stall speed.

B. As long as the IAS is kept above the power-on stall speed.

C. As long as the maximum angle of attack is not exceeded.

D. As long as the pitch angle is negative.

MULTIPLE CHOICE QUESTION

30 sec • 1 pt

84.At high angle of attack, where does airflow separation begin?

A. Upper surface, towards the leading edge.

B. Lower surface, towards the trailing edge.

C. Upper surface, towards the trailing edge.

D. Lower surface, towards the leading edge.

MULTIPLE CHOICE QUESTION

30 sec • 1 pt

85.At the point of stall:

A. Lift decreases, drag decreases.

B. Lift constant, drag increases.

C. Lift decreases, drag increases.

D. Lift decreases, drag constant.

MULTIPLE CHOICE QUESTION

30 sec • 1 pt

86.Force on the tail and its effect on VS due to CG movement:

A. If rearward movement of the CG gives a reduced down-force on the tail, VS will be higher.

B. If forward movement of the CG gives a reduced down-force on the tail, VS will be higher.

C. If rearward movement of the CG gives a reduced down-force on the tail, VS will be reduced.

D. If rearward movement of the CG gives an increased down-force on the tail, VS will be reduced.

MULTIPLE CHOICE QUESTION

30 sec • 1 pt

87.How do vortex generators work?

A. Re-direct spanwise flow.

B. Take energy from free stream and introduce it into the boundary layer.

C. Reduce kinetic energy to delay separation.

D. Reduce the adverse pressure gradient.

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POF part 2

81.A jet aircraft flying at high altitude encounters severe turbulence without encountering high speed buffet. If the aircraft decelerates, what type of stall could occur first?

82.A swept wing aircraft stalls and the wake contacts the horizontal tail. What would be the stall behaviour?

83.An aircraft at low subsonic speed will never stall:

84.At high angle of attack, where does airflow separation begin?

85.At the point of stall:

86.Force on the tail and its effect on VS due to CG movement:

87.How do vortex generators work?

88.If the stalling speed in a 15 degree bank turn is 60 kt, what would the stall speed be in a 45 degree bank?

89.If the straight and level stall speed is 100 kt, what will be the stall speed in a 1·5g turn?

90.In recovery from a spin:

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