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Principles of Flight - ATPL - Airline Transport Pilot Licence
Test 10 domande Principles of Flight, tempo libero
1 - A conventional stabiliser on a stable aeroplane in a normal cruise condition: 1 - always provides negative lift.2 - contributes to the total lift of the aeroplane.3 - may stall before the wing, in icing conditions, with large flap settings, unless adequate design and/or operational precautions are taken.4 - is necessary to balance the total pitch moment of the aeroplane. Which of the following lists all the correct statements ?
2, 3 and 4
1 and 4
1 and 3
1, 3 and 4
2 - Induced drag is created by the:
Spanwise flow pattern resulting in the tip vortices
Propeller wash blowing across the wing
Separation of the boundary layer over the wing
Interference of the air stream between wing and fuselage
3 - Increase of the delta load factor due to a given vertical upgust at a given EAS occurs when:
The slope of the CL - alpha graph becomes steeper
The wing loading increases
The altitude increases
The weight increases
4 - The span-wise flow is caused by the difference between the air pressure on top and beneath the wing and its direction of movement goes from:
Beneath to the top of the wing via the wing tip
The top to beneath the wing via the leading edge
Beneath to the top of the wing via the trailing edge
The top to beneath the wing via the wing's trailing edge
5 - How is adverse yaw compensated for during entry into and roll out from a turn ?
Differential aileron deflection
Anti-balanced rudder control
6 - The torque effect during the take off run in respect of a right hand propeller, when viewed from behind, will tend to:
Roll the aeroplane to the right
Pitch the aeroplane nose down
Pitch the aeroplane nose up
Roll the aeroplane to the left
7 - A body is placed in a certain airstream. The density of the airstream decreases to half of the original value. The aerodynamic drag will decrease with a factor:
8 - Which of the following situations leads to a decreasing stall speed (IAS)?
Increasing air density
Increasing load factor
9 - The point, where the single resultant aerodynamic force acts on an aerofoil, is called:
Centre of gravity
Centre of pressure
10 - In case of supersonic flow retarded by a normal shock wave a high efficiency (low loss in total pressure) can be obtained if the Mach number in front of the shock is
Lower than 1.
Small but still supersonic.
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