Test Results

1.How does stalling speed vary with load factor?

Your Answer:It decreases inversely with the square root of the load factorINCORRECT

Correct Answer:It increases proportionally with the square root of the load factor

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2. When maintaining level flight an increase in speed willYour Answer: cause the C of P to move aft CORRECTThis question has been asked 2331 times with a success rate of only 43 percent.Comment/Reference:

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If the aircraft is to remain in level flight whilst increasing speed, then the AofA must decrease to keep lift the same. This will cause the CofP to move aft.

3.What factors determine the distance travelled over the ground of an aeroplane in a glide?

Your Answer:The wind and the lift/drag ratio, which changes with angle of attack CORRECT

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4.The wing of an aeroplane will never stall at low subsonic speeds as long as

Your Answer: there is a nose-down attitude INCORRECT

Correct Answer:the angle of attack is smaller than the value at which the stall occurs

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5.The load factor isYour Answer: the ratio of lift to drag INCORRECT

Correct Answer: the ratio of lift to weightThis question has been asked 2341 times with a success rate of 84 percent.Comment/Reference:

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6. The input to a stick shaker comes from

Your Answer:the airspeed, and sometimes the rate of change in airspeedINCORRECT

Correct Answer:angle of attack, and sometimes the rate of change in angle of attack

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7.Stick pushers must be installed in aeroplanes with dangerous stall characteristics. Dangerous stall characteristics include:

Your Answer: pitch down and minor wing drop INCORRECTCorrect Answer: excessive wing drop and deep stallThis question has been asked 2394 times with a success rate of 82 percent.Comment/Reference:

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8.The sensor of a stall warning system can be activated by a change in the location of the

Your Answer: centre of lift INCORRECTCorrect Answer: stagnation pointThis question has been asked 2371 times with a success rate of 77 percent.Comment/Reference:

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9.Which type of stall has the largest associated angle of attack?

Your Answer: Shock stall INCORRECTCorrect Answer: Deep stallThis question has been asked 2403 times with a success rate of 79 percent.Comment/Reference:

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10. The maximum lift/drag ratio of a wing occurs

Your Answer:at the angle of attack where the wing develops its maximum liftINCORRECT

Correct Answer: at an angle below which the wing develops max liftThis question has been asked 2348 times with a success rate of only 39 percent.Comment/Reference:

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Mechanics of Flight, Kermode Page 89

241-250

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Test Results

1. A slotted flap will increase the CLmax by

Your Answer:increasing the camber of the aerofoil and improving the boundary layer CORRECT

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2. When a trailing edge flap is lowered fullyYour Answer: the C of P moves to the rear and lift/drag ratio is increasedINCORRECTCorrect Answer: the C of P moves to the rear and lift/drag ratio is decreasedThis question has been asked 2522 times with a success rate of only 43 percent.Comment/Reference:

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3.Which statement is correct?

Your Answer:Extension of flaps will increase (CL/CD)max, causing the minimum rate of descent to decrease INCORRECT

Correct Answer:Extension of flaps causes a reduction of the stall speed, the maximum glide distance also reduces

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4. A stalled aerofoil has a lift/drag ratioYour Answer: zero INCORRECTCorrect Answer: less than the lift/drag ratio prior to stallThis question has been asked 2112 times with a success rate of 68 percent.Comment/Reference:

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See the graph of lift/drag ratio. Highest at around 4 degrees, then downhill from there with a rapid decrease after stall.

5.What is the most effective flap system?Your Answer: Fowler flap CORRECTThis question has been asked 2368 times with a success rate of 88 percent.Comment/Reference:

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6.At low forward speedYour Answer: increased downwash reduces tailplane effectivenessINCORRECTCorrect Answer: increased downwash increases tailplane effectivenessThis question has been asked 2219 times with a success rate of 64 percent.Comment/Reference:

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At low speed, the aircraft must fly at high AofA and therefore the downwash is great. This produces a high NEGATIVE angle of attack on the tailplane and increase its down-force (and hence effectiveness - assuming it is a down-force which is required i.e. general case - CG forward of CP).

7.An aeroplane with swept back wings is equipped with slats and/or leading edge (L.E.) flaps. One possible efficient way to arrange the leading edge devices on the wings is

Your Answer: Wing roots: slats Wing tips: L.E. flaps INCORRECTCorrect Answer: Wing roots: L.E. flaps Wing tips: slatsThis question has been asked 2416 times with a success rate of 66 percent.Comment/Reference:

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8.Which of the following statements about the difference between Krueger flaps and slats is correct?

Your Answer:Deploying a slat will form a slot deploying a Krueger flap does not CORRECT

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9.On some modern aircraft a stall warning will automaticallyYour Answer: increase thrust INCORRECTCorrect Answer: cause a pitch nose down movementThis question has been asked 2235 times with a success rate of 66 percent.Comment/Reference:

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Some aircraft have an hydraulic 'stick pusher' which activates after the stall warning. Also, if stall commences at the root, the turbulent air hits the tailplane and causes buffet, and reduces the download on the tail, which allows the aircraft to pitch-down. Some aircraft have auto-slat extend prior to stall but not as a 'stall-warning'

10.During the extension of the flaps at a constant angle of attack the aeroplane starts to: (all other factors of importance being constant)

Your Answer: climb CORRECTThis question has been asked 2340 times with a success rate of 84 percent.Comment/Reference:

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251-260

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1. Deploying a Fowler flap, the flap willYour Answer: just move aft INCORRECTCorrect Answer: move aft, then turn downThis question has been asked 2376 times with a success rate of 85 percent.Comment/Reference:

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2.An aeroplane has the following flap settings: 0°, 15°, 30° and 45°. Slats can be selected too. Which of the above selections will produce the greatest negative influence on the CL/CD ratio?

Your Answer: Flaps from 0° to 15° INCORRECTCorrect Answer: Flaps from 30° to 45°This question has been asked 2398 times with a success rate of 74 percent.Comment/Reference:

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3.The highest lift/drag ratio is atYour Answer: the optimum angle of attack CORRECTThis question has been asked 2106 times with a success rate of 73 percent.Comment/Reference:

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Normally 4-6 degrees.

4.When flaps are extended in a straight and level flight at constant IAS, the lift coefficient will eventually

Your Answer: decrease INCORRECTCorrect Answer: remain the sameThis question has been asked 2598 times with a success rate of only 34 percent.Comment/Reference:

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5. When spoilers are used as speed brakesYour Answer: they do not affect wheel braking action during landingINCORRECTCorrect Answer: at same angle of attack, CD is increased and CL is decreasedThis question has been asked 2424 times with a success rate of 83 percent.Comment/Reference:

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6.When a trailing edge flap is lowered during flight from take-off position to fully down position, one will experience

Your Answer: a small increase in lift and a large increase in drag CORRECTThis question has been asked 2426 times with a success rate of 59 percent.Comment/Reference:

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7. IAS for a stall willYour Answer: increase with altitude INCORRECTCorrect Answer: roughly remain the same for all altitudesThis question has been asked 2173 times with a success rate of 72 percent.Comment/Reference:

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IAS is not corrected for density, therefore the aircraft will stall at a constant IAS regardless of height (density). TAS at stall however, increases with height.

8. What is the purpose of an auto-slat system?Your Answer: Extend automatically when a certain value of angle of attack is

exceeded CORRECTThis question has been asked 2362 times with a success rate of 81 percent.Comment/Reference:

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9. If the radius of a turn is reduced, the load factor willYour Answer: increase CORRECTThis question has been asked 2170 times with a success rate of 70 percent.Comment/Reference:

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Increased lift is required as the turning radius is decreased therefore load factor increases

10.Which of the following series of configurations has an increasing critical angle of attack?

Your Answer: flaps only extended, clean wing, slats only extended CORRECTThis question has been asked 2214 times with a success rate of 68 percent.Comment/Reference:

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261-270

Test Results

1.If the flaps are lowered but the airspeed is kept constant, to maintain level flight

Your Answer: the nose must be pitched up INCORRECTCorrect Answer: the nose must be pitched downThis question has been asked 2366 times with a success rate of 65 percent.Comment/Reference:

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2. A constant rate of climb is determined byYour Answer: excess engine power CORRECTThis question has been asked 2187 times with a success rate of 70 percent.Comment/Reference:

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Climb rate is a function of available power minus required power (i.e. excess power).

3.The effects of leading edge slats

Your Answer:increase boundary layer energy, move suction peak on to slat and increase CLmax angle of attack INCORRECT

Correct Answer:increase boundary layer energy, increase suction peak on main wing section, move CLmax to a higher angle of attack

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4. Flaps are used in order to

Your Answer:decrease stalling speed and reduce max angle of attack thereby achieving a more nose down attitude near and at stalling speedCORRECT

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5. If both wings lose lift the aircraftYour Answer: glides on a horizontal plane INCORRECTCorrect Answer: pitches nose downThis question has been asked 2222 times with a success rate of 70 percent.Comment/Reference:

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At stall, the lift vector (what is left of it) moves back rapidly, bringing the nose down and the aircraft increases speed, recovering from the stall.

6. Deployment of leading edge flaps willYour Answer: decrease CLmax INCORRECTCorrect Answer: increase critical angle of attackThis question has been asked 2406 times with a success rate of 80 percent.Comment/Reference:

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7.During flap down selection in a continuous straight and level flight at constant IAS and weight

Your Answer: the centre of pressure moves aft CORRECTThis question has been asked 2603 times with a success rate of only 40 percent.Comment/Reference:

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8. CLmax may be increased by the use ofYour Answer: both flaps and slats CORRECTThis question has been asked 2380 times with a success rate of 83 percent.Comment/Reference:

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9.Compared with the flap up configuration the maximum angle of attack for the flaps down configuration is

Your Answer: larger INCORRECT

Correct Answer: smallerThis question has been asked 2428 times with a success rate of 57 percent.Comment/Reference:

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10. When a slat is retracted, it movesYour Answer: towards the lower leading edge of the wing INCORRECTCorrect Answer: towards the upper leading edge of the wingThis question has been asked 2370 times with a success rate of 64 percent.Comment/Reference:

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A slat increases the wing camber at the leading edge. When it retracts, it retracts to the top of the leading edge. Unlike a Krueger Flap which retracts to the lower leading edge.

271-280

Test Results

1.Compared with the flap down configuration the maximum angle of attack for the flaps up configuration is

Your Answer: larger CORRECTThis question has been asked 2419 times with a success rate of 58 percent.Comment/Reference:

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2. In a turn, the up-going wing causes aYour Answer: stabilising effect due to decreased AoA CORRECTThis question has been asked 2143 times with a success rate of 60 percent.Comment/Reference: (No Comment/Reference Available)

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3.How is the pitching moment affected if flaps are deployed in straight and level flight?

Your Answer: Depends on wing position CORRECTThis question has been asked 2502 times with a success rate of only 35 percent.Comment/Reference:

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4.What is the effect of lowering leading edge and trailing edge flaps in flight?

Your Answer:Cl increases, Cd remains the same and the stalling angle of attack increases. INCORRECT

Correct Answer:Cl increases, Cd increases and the stalling angle of attack increases

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5.Lowering the inboard flaps causes the wing Centre of PressureYour Answer: to move forward INCORRECTCorrect Answer: to move inboard towards the wing rootThis question has been asked 2470 times with a success rate of 56 percent.Comment/Reference:

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6. Slats

Your Answer:re-energise the boundary layer thereby increasing the stalling angle of attack CORRECT

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7.When deploying the flaps the effective angle of attack

Your Answer: remains the same INCORRECTCorrect Answer: increasesThis question has been asked 2526 times with a success rate of 62 percent.Comment/Reference:

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8. An aircraft entering a level turn will require more liftYour Answer: only if there is an increase in angle of attack INCORRECTCorrect Answer: in all casesThis question has been asked 2371 times with a success rate of 77 percent.Comment/Reference:

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Some of the lift is required to turn the aircraft, so lift must be increased in all cases, to counter weight, and maintain level flight.

9.After take-off the slats (when installed) are always retracted later than the flaps. Why?

Your Answer:Because SLATS EXTENDED provides a better view from the cockpit than FLAPS EXTENDED INCORRECT

Correct Answer:Because SLATS EXTENDED gives a large decrease in stall speed with relatively less drag

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10.In order to maintain straight and level flight at a constant airspeed, whilst the flaps are being retracted, the angle of attack will

Your Answer: increase CORRECTThis question has been asked 2463 times with a success rate of 56 percent.Comment/Reference:

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281-290

Test Results

1.Pulling the control column and rotating to the left causes

Your Answer: elevator down, left aileron up INCORRECTCorrect Answer: elevator up, left aileron upThis question has been asked 2356 times with a success rate of 73 percent.Comment/Reference:

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Know your controls and their effects

2.If flaps are deployed at constant IAS in straight and level flight, the magnitude of tip vortices will eventually: (flap span less than wing span)

Your Answer: remain the same INCORRECTCorrect Answer: decreaseThis question has been asked 2423 times with a success rate of 50 percent.Comment/Reference:

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3. The trailing edge flaps, when extendedYour Answer: improve the best angle of glide INCORRECTCorrect Answer: worsen the best angle of glideThis question has been asked 2460 times with a success rate of only 45 percent.Comment/Reference:

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4. One of the main purposes of using flaps during approach and

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landing is toYour Answer: shift the centre of gravity aft INCORRECTCorrect Answer: increase the angle of descent without increasing the airspeedThis question has been asked 2347 times with a success rate of 64 percent.Comment/Reference:

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5. If the aircraft is slipping in a turnYour Answer: the bank angle is too great CORRECTThis question has been asked 2156 times with a success rate of 64 percent.Comment/Reference:

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In a coordinated turn the ac will neither slip or skid, however increase of bank angle during this coordinated turn will cause the aircraft to slip as the vertical component of lift will be too small to oppose the weight of the aircraft

6.The use of a slot in the leading edge of the wing enables the aeroplane to fly at a slower speed because

Your Answer: it changes the camber of the wing INCORRECTCorrect Answer: it delays the stall to a higher angle of attackThis question has been asked 2435 times with a success rate of 61 percent.Comment/Reference:

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7. In normal flight conditions, an increase in aircraft speedYour Answer: the nose remains in the same position INCORRECTCorrect Answer: causes the nose of the aircraft to liftThis question has been asked 2112 times with a success rate of 74 percent.Comment/Reference:

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An aircraft cannot increase in speed and stay level. It must climb.

8.What is the effect of deploying leading edge flaps?

Your Answer: Not affect the critical angle of attack INCORRECTCorrect Answer: Increase the critical angle of attackThis question has been asked 2381 times with a success rate of 77 percent.Comment/Reference:

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9.An aircraft sideslips. What helps to restore the aircraft?

Your Answer: Tailplane INCORRECT

Correct Answer:Dihedral causes the aircraft to roll straight and the fin increases the yaw rate

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If the aircraft rolls then sideslips, the leading wing has more lift (due to dihedral) so it rolls straight and the fin provides the weather vane effect

10. For an aircraft climbing at a constant IAS, the Mach number willYour Answer: increase CORRECTThis question has been asked 2165 times with a success rate of 62 percent.Comment/Reference:

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Speed of sound decreases with altitude (due only to the drop in temperature). Mach number is TAS/local speed of sound. So Mach number increases with altitude, more so as TAS is increasingly greater than IAS

291-300

Test Results

1. Upon extension of a spoiler on a wing

Your Answer:only CL is decreased (CD remains unaffected) INCORRECT

Correct Answer: CD is increased and CL is decreasedThis question has been asked 2088 times with a success rate of 85 percent.Comment/Reference:

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2.If the weight of an aircraft is increased, the maximum lift-to-drag ratio will

Your Answer: not be affected CORRECTThis question has been asked 2152 times with a success rate of 50 percent.Comment/Reference:

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3.With the flaps lowered, the stalling speed willYour Answer: decrease CORRECTThis question has been asked 2112 times with a success rate of 66 percent.Comment/Reference:

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Plain flaps stall at a lower AOA than a basic aerofoil (AC Kermode Fig 3.32 refers). Thus whilst they provide more lift at low speed, the stall will occur earlier unless we increase the stalling speed. On a slotted flap this does not happen

4.Speed brakes are a device used on large transport category aircraft

Your Answer: to prevent aquaplaning INCORRECT

Correct Answer:to increase drag in order to maintain a steeper gradient of descent

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5.When flying close to the stall speed a pilot applies left rudder the aircraft will

Your Answer: pitch nose up INCORRECTCorrect Answer: stall the left wingThis question has been asked 2158 times with a success rate of 62

percent.Comment/Reference:

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The reduced speed of the left wing will cause it to stall. Answer b is very close, but it is believed that the roll would not be controlled hence we suggest c is the answer

6.When an aircraft is in a bank, the upper wing produces more drag. To compensate

Your Answer:when bank angle is achieved then the ailerons are operated in the opposite direction to cause the opposite effect INCORRECT

Correct Answer: the rudder is operatedThis question has been asked 2174 times with a success rate of 52 percent.Comment/Reference:

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This effect is known as adverse aileron yaw.

7. When flaps are down

Your Answer:it will increase angle of attack and increase slow speed stabilityCORRECT

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Flaps going down the angle of attack will increase... The additional lift increases slow speed stability

8. When pulling out of a dive (e.g. looping) the angle of attackYour Answer: remains the same INCORRECTCorrect Answer: increasesThis question has been asked 2194 times with a success rate of 72 percent.Comment/Reference:

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9.In which phase of the take-off is the aerodynamic effect of ice located on the wing leading edge most critical?

Your Answer: During climb with all engines operating INCORRECTCorrect Answer: The last part of the rotationThis question has been asked 2111 times with a success rate of 52 percent.Comment/Reference:

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10.The result of an aircraft flying into a rainstorm of super cooled rain droplets would be an accretion of

Your Answer: glaze ice CORRECTThis question has been asked 2210 times with a success rate of 64 percent.Comment/Reference:

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301-310

Test Results

1.Ice accretion on an aircraft in flight that is opaque, rough, with low shear strength is

Your Answer: rime ice CORRECT

This question has been asked 2231 times with a success rate of 60 percent.

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Rime ice is opaque and rough, thus disrupts airflow and reduces lift. Note that Glaze ice is clear and smooth

2. In a steady climb

Your Answer: thrust is greater than drag CORRECT

This question has been asked 2131 times with a success rate of 78 percent.

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The thrust must overcome drag plus a component of the weight. See Kermode page 216

3. On a slender delta wing at low speed the lift/drag ratio is

Your Answer: constant INCORRECT

Correct Answer: increased

This question has been asked 2199 times with a success rate of only 41 percent.

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An additional lift generated at high angles of attack on delta-wing aircraft is known as Vortex Lift

4.A high winged aircraft in a turn requires returning to level flight.

Your Answer: Lift must increase on the upper wing INCORRECT

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Correct Answer: Lift must decrease on the upper wing

This question has been asked 2127 times with a success rate of 74 percent.

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A decrease in lift on the raised wing will allow the wings to roll towards level

5.What happens to the load factor as you decrease the turn radius?

Your Answer: Load factor increases CORRECT

This question has been asked 2085 times with a success rate of 65 percent.

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Load factor (g) is a function of bank angle. g = 1/cos(bank angle)

6.A high wing aircraft in a banked turn increases its angle of bank without increasing its angle of attack. The aircraft will

Your Answer: sideslip INCORRECT

Correct Answer: sideslip with a loss of altitude

This question has been asked 2069 times with a success rate of 83 percent.

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Assuming constant TAS the lift opposing weight decreases and slip occurs with loss of altitude

7.If the ambient temperature at sea level decreases, the operational ceiling height of the aircraft

Your Answer: increases CORRECT

This question has been asked 2383 times with a success rate of 68 percent.

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If temperature at sea level decreases then it is colder at altitude. Therefore density increases, and more lift is available

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8.Which control surfaces provide directional and pitch control?

Your Answer: Ruddervators CORRECT

This question has been asked 2352 times with a success rate of 74 percent.

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Ruddervators are the movable surfaces in a v tail empennage

9.Name the four fundamentals involved in manoeuvring the aircraft.

Your Answer: Take off, slow flight and stalls INCORRECT

Correct Answer: Aircraft power, pitch, bank and trim

This question has been asked 2095 times with a success rate of 64 percent.

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Power and bank for turns, pitch and trim for climb and dive

10.Under the category system the design load factor for an aeroplane in the normal category is

Your Answer: 4.4 g INCORRECT

Correct Answer: 3.8 g

This question has been asked 2155 times with a success rate of 69 percent.

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CS 25.337 and FAR 23.337

311-320

Test Results

1.For a given bank angle the load factor imposed on both the aeroplane and pilot in a co-ordinated constant altitude turn

Your Answer: is varied with the ratio of turn INCORRECT

Correct Answer: is constant

This question has been asked 2151 times with a success rate of only 47 percent.

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A coordinated turn is one that all parameters are constant, without the aircraft climbing or sideslipping

2.The degree of aeroplane wing loading during level coordinated turn in smooth air depends upon

Your Answer: density altitude INCORRECT

Correct Answer: angle of bank

This question has been asked 2178 times with a success rate of 54 percent.

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The more bank required the more lift is required, hence wing loading (lift/wing area) increases

3. The primary purpose of wing spoilers is to

Your Answer: increase drag INCORRECT

Correct Answer: decrease lift of the wing by disturbing the airflow

This question has been asked 2345 times with a success rate of 71 percent.

Comment/Reference: We are going for 'decrease lift...' because spoilers are also

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known as lift dumpers, however if you increase turbulence you also increase drag

4.A wing flap is a

Your Answer: primary control surface INCORRECT

Correct Answer: high lift device

This question has been asked 2331 times with a success rate of 73 percent.

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Flaps are also known as lift augmentation devices

5. Frise ailerons are used to minimise

Your Answer: lateral stability INCORRECT

Correct Answer: adverse yaw

This question has been asked 2079 times with a success rate of 68 percent.

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When deflected up a frise aileron inserts a beak into the airflow on the underside of the wing, this balances the increased drag created by the downgoing aileron on the other side. Mechanics of Flight AC Kermode 10th edition Page 301

6.During a steep dive, the load factor will be

Your Answer: 2g INCORRECT

Correct Answer: zero

This question has been asked 2064 times with a success rate of 50 percent.

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In a vertical dive lift is zero, therefore the load factor is zero

7.Which statement is true regarding CofG location and drag?

Your Answer:If loaded with CofG forward the aircraft will cruise at a faster speed because of reduced drag. INCORRECT

Correct Answer:If loaded with CofG aft but within limit, the aircraft will cruise at faster airspeed because of reduced air drag.

This question has been asked 2261 times with a success rate of only 48 percent.

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Barnard and Phillips Aircraft Flight Page 319 states that trim drag reduces as the CofG moves aft

8.In a steady climb at constant indicated airspeed, true airspeed will

Your Answer: remain constant INCORRECT

Correct Answer: increase

This question has been asked 2181 times with a success rate of 67 percent.

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TAS is greater than IAS at altitude because of the drop in density

9.A wing develops 10,000 N of lift at 100 Kts. Assuming the wing remains at the same angle of attack - how much lift will it develop at 300 Kts.

Your Answer: 90,000 N CORRECT

This question has been asked 2054 times with a success rate of 82 percent.

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Lift varies with velocity squared

10.With an aircraft in a 90 degree banked turn, holding the longitudinal axis of the aircraft level

Your Answer: the pilot uses the elevators to maintain height INCORRECT

Correct Answer: altitude cannot be maintained

This question has been asked 2109 times with a success rate of 64 percent.

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321-330

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1. During a correctly executed turn

Your Answer: the lift vector must be increased CORRECT

This question has been asked 2147 times with a success rate of 63 percent.

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The VERTICAL COMPONENT of the lift vector must be equal to the weight vector

2. The lowering of a flap will

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Your Answer: bend the chord line of the aerofoil INCORRECT

Correct Answer: affect the mean camber line

This question has been asked 2125 times with a success rate of 69 percent.

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3.True stalling speed of an aircraft increases with altitude

Your Answer:because humidity is increased and this increases dragINCORRECT

Correct Answer: because air density is reduced

This question has been asked 2031 times with a success rate of 83 percent.

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True airspeed is Indicated Airspeed corrected for density

4.The optimum angle of attack is the best angle of attack

Your Answer: for landing INCORRECT

Correct Answer: in cruise

This question has been asked 2278 times with a success rate of 76 percent.

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5.Vortex generators are fitted to aircraft to

Your Answer: move the stagnation point rearwards INCORRECT

Correct Answer: move the transition point forward

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6.A vortex generator is designed

Your Answer:to enlarge the tip vortex thus reducing parasitic dragINCORRECT

Correct Answer: to delay boundary layer separation

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7.Aerodynamic balance of a control surface may be achieved

Your Answer:by a horn at the extremity of the surface forward of the hinge line CORRECT

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8.In a reversed cambered stabiliser the yoke has been moved such that the elevator is up. This

Your Answer: will increase tailplane download CORRECT

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331-340

Test Results

1. Airbrakes can be used to

Your Answer: prevent turbulence during high speed flight INCORRECT

Correct Answer: dump the lift off the wings on landing

This question has been asked 2330 times with a success rate of 82 percent.

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2. If the ailerons are moved from the neutral position there is

Your Answer:induced drag on both ailerons but more so on downgoing oneCORRECT

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3. When maintaining a constant IAS at high altitude

Your Answer: TAS will higher than when at a lower altitude CORRECT

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TAS is indicated airspeed corrected for density so TAS is always greater than IAS at higher altitude

4. When is the L/D (Lift to Drag) ratio at its highest? When the AoA is

Your Answer: 0 degrees INCORRECT

Correct Answer: 4 degrees

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L/D ratio is highest at about 4 degrees AoA

5.Which of the following is true about forces acting on an aircraft during climb?

Your Answer:Lift acts at right angles to the flight path and the weight acts vertically downwards CORRECT

This question has been asked 2053 times with a success rate of 82 percent.

Comment/Reference: Lift acts at right angles to the flight path

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6.Which of the following L/D ratio will enable one to achieve maximum distance in a glide?

Your Answer: Minimum L/D INCORRECT

Correct Answer: Maximum L/D

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Maximum L/D gives max distance

7.If an aircraft is turned/controlled to the left, what happens to the speed of the airflow over the left wing?

Your Answer: Decreases CORRECT

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'Inner' wing flies with reduced turn radius, hence less speed.

8. What is the purpose of a slot?

Your Answer: To re-energise the boundary layer CORRECT

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9. If a plain flap is lowered or extended

Your Answer: camber increases INCORRECT

Correct Answer: both camber and angle of attack increase

This question has been asked 2268 times with a success rate of 61 percent.

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10. The power required at high altitude for a given IAS is

Your Answer: same as at low altitude INCORRECT

Correct Answer: higher

This question has been asked 2285 times with a success rate of only 43 percent.

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External website... Para 7.5.5

341-347

Test Results

1. An aircraft wing is said to have stalled when the

Your Answer:speed of the aircraft falls below the stalling speed INCORRECT

Correct Answer: airflow separates from the upper surface

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2.What happens to the pressure, density and temperature of the airflow behind a normal shockwave?

Your Answer: They remain the same INCORRECT

Correct Answer: They are increased

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3.To carry out a correctly banked turn, the angle of attack must be

Your Answer: increased with an increase in power CORRECT

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4. Flaps are said to be split when

Your Answer:the upper surface of the wing trailing edge is fixed, and only the lower surface contour alters when the flaps are loweredCORRECT

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5.A swept wing aircraft experiences 3G in pulling out of a dive; due to the G loading the wing will

Your Answer:lose incidence at the tip and cause nose down pitch INCORRECT

Correct Answer: lose incidence at the tip and cause nose up pitch

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As the wing flexes up, the AofA decreases at the tip, reducing lift at the tip. Due to the sweep, the loss of lift is aft of the CofG, hence the nose will rise.

6. Mcrit is the speed at which

Your Answer: the aircraft is considered to be fully supersonic INCORRECT

Correct Answer: a shock wave forms on the fuselage

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The shockwave is most likely to form on the fuselage first, due to the greater deviation of airflow.

7. As humidity increases, lift will

Your Answer: increase INCORRECT

Correct Answer: decrease

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Humidity reduces density, because moist air is lighter than dry air. Reduced density reduces lift.