1) When the Mach number is slowly increased in straight and level flight the first shockwaves will occur: Report

on the underside of the wing.

at the wing root segment, upperside.

somewhere on the hoizontal tail.

2) Which kind of flow separation occurs at the smallest angle of attack? Report

shockstall.

high-speed stall.

low-speed stall.

3) Which of the following (1) aerofoils and (2) angles of attack will produce the lowest Mcrit values? Report

(1) thick and (2) large.

(1) thick and (2) small.

(1) thin and (2) large.

4) If an aeroplane is accelerated from subsonic to supersonic speeds, the centre of pressure will move: Report

to a position near the leading edge.

to a position near the trailing edge.

to the mid chord position.

5) Air passes a normal shock wave. Which of the following statements is correct? Report

The pressure decreases.

The temperature increases.

The velocity increases.

6) The Mach trim system will prevent: Report

dutch roll.

buffeting.

tuck under.

7) When air has passed an expansion wave, the static pressure is: Report

increased.

unchanged.

decreased.

8) The critical Mach Number of an aeroplane is the free stream Mach Number, which produces the first evidence of : Report

buffet.

shock wave.

local sonic flow.

9) Local sonic flow. Report

dihedral of the wings.

sweep back of the wings.

vortex generators.

10) In supersonic flight, all disturbances produced by an aeroplane are: Report

in front of the aeroplane.

very weak and negligible.

in between a conical area, depending on the Mach Number.

11) In transonic flight the ailerons will be less effective than in subsonic flight because: Report

behind the shock wave pressure is lower.

aileron down deflection moves the shock wave forward.

aileron deflection only partly affects the pressure distribution around the wing.

12) To be able to predict compressibility effects you have to determine the: Report

Mach Number.

EAS.

TAS.

13) The formula for the Mach Number is: (a= speed of sound) Report

M= TAS / a

M= a / TAS

M= TAS*a

14) If the altitude is increased and the TAS remains constant in the standard troposphere the Mach Number will: Report

not change.

increase or decrease, depends of the type of aeroplane.

increase.

15) Climbing at a constant Mach Number up to FL 350 the TAS will: Report

first increase, then decrease.

decrease.

remain constant.

16) The speed of sound is affected by the: Report

pressure of the air.

humidity of the air.

temperature of the air.

17) The most important problem of ice accretion on an aeroplane during flight is: Report

increase in drag.

blocking of control surfaces.

reduction in CLmax.

18) The additional increase of drag at Mach Numbers above the critical Mach Number is due to: Report

wave drag.

increased angle of attack.

increased interference drag.

19) What is the limit load factor of a large transport aeroplane in the manoeuvring diagram? Report

3.75

6

2.5

20) The bow wave will appear first at: Report

M= 1.3

M= 1.0

M= Mcrit

EASA Questions Principles Of Flight Transonic Aerodynamics

Subsonic Aerodynamics

Transonic Aerodynamics

Supersonic Aerodynamics

Stability

Control