Principles of Flight - ATPL - Airline Transport Pilot license

Question 1

In the transonic range the aeroplane characteristics are strongly determined by:

Accepted Answer

The Mach Number.

Answer

The TAS.

Answer

The CAS.

Answer

The IAS.

Question 2

Which statement is correct regarding a shockwave on a lift generating wing?

Accepted Answer

It moves slightly aft when an aileron is deflected downward

Answer

It reaches its highest strength when flying at the critical Mach number

Answer

It is located at the greatest wing thickness when the aeroplane reaches the speed of sound

Answer

It moves forward when the Mach number is increased

Question 3

Deflection of leading edge flaps will:

Accepted Answer

Increase critical angle of attack

Answer

Decrease drag

Answer

Decrease CLmax

Answer

Not affect critical angle of attack

Question 4

In straight and level flight, as speed is increased:

Accepted Answer

The elevator is deflected further downwards and the trim tab further upwards.

Answer

The elevator and trim tab do not move.

Answer

Both elevator and trim tab are deflected further downwards.

Answer

The elevator is deflected further upwards and the trim tab further downwards.

Question 5

The true airspeed (TAS) is:

Accepted Answer

Lower than the indicated airspeed (IAS) at ISA conditions and altitudes below sea level

Answer

Higher than the speed of the undisturbed airstream about the aeroplane

Answer

Lower than the speed of the undisturbed airstream about the aeroplane

Answer

Equal to the IAS, multiplied by the air density at sea level

Question 6

The angle of attack for a propeller blade is the angle between the blade chord line and the:

Accepted Answer

Local air speed vector.

Answer

Direction of propeller axis.

Answer

Principal direction of the propeller blade.

Answer

Aeroplane heading.

Question 7

High Aspect Ratio, as compared with low Aspect Ratio, has the effect of:

Accepted Answer

Decreasing induced drag and critical angle of attack

Answer

Increasing lift and critical angle of attack

Answer

Increasing lift and drag

Answer

Increasing induced drag and decreasing critical angle of attack

Question 8

A slat will:

Accepted Answer

Prolongs the stall to a higher angle of attack

Answer

Provide a boundary layer suction on the upper surface of the wing

Answer

Increase the lift by increasing the wing area and the camber of the aft portion of the wing

Answer

Increase the camber of the aerofoil and divert the flow around the sharp leading edge

Question 9

Which statement is correct about the laminar and turbulent boundary layer:

Accepted Answer

Friction drag is lower in the laminar layer

Answer

Friction drag will be equal in both types of layers

Answer

Separation point will occur earlier in the turbulent layer

Answer

Friction drag is lower in the turbulent layer

Question 10

Vortex generators mounted on the upper wing surface will

Accepted Answer

Decrease the shock wave induced separation.

Answer

Decrease the interference drag of the trailing edge flaps.

Answer

Increase the effectiveness of the spoiler due to increase in parasite drag.

Answer

Decrease the stalling speed by increasing spanwise flow on the wing.

Exam questions Principles of Flight - ATPL - Airline Transport Pilot license

ATPL - Airline Transport Pilot license: Principles of Flight 10 Questions no time limit

Exam questions Principles of Flight - ATPL - Airline Transport Pilot license

ATPL - Airline Transport Pilot license: Principles of Flight 10 Questions no time limit

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