1) The critical Mach number can be increased by Report

a T-tail.

an increase in wing aspect ratio.

sweepback of the wings.

2) 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 Report

exactly 1.

small but still supersonic.

high (supersonic).

3) To increase the critical Mach number a conventional aerofoil should Report

be used with a high angle of attack.

have a large leading edge radius.

have a low thickness to chord ratio.

4) Just above the critical Mach number the first evidence of a shock wave will appear at the Report

upper side of the wing.

lower side of the wing.

leading edge of the wing.

5) If an aeroplane is flying at transonic speed with increasing Mach number the shock wave on the upper side of the wing Report

moves into trailing edge direction.

moves into leading edge direction.

stays all the time at the same position.

6) Shock induced separation results in Report

decreasing drag.

decreasing lift.

constant lift.

7) In the transonic range lift will decrease at the shock stall due to the Report

first appearance of a shock wave at the upper side of the wing.

appearance of the bow wave.

separation of the boundary layer at the shock waves.

8) The lift force, acting on an aerofoil : Report

increases, proportional to the angle of attack until 40 degrees.

is mainly caused by overpressure at the underside of the aerofoil.

is mainly caused by suction on the upperside of the aerofoil.

9) Compared with an oblique shock wave at the same Mach number a normal shock wave has a Report

higher total temperature.

lower static temperature.

higher loss in total pressure.

10) A boundary layer fence on a swept wing will: Report

improve the lift coefficient of the trailing edge flap.

improve the low speed characteristics.

improve the high speed characteristics.

11) When flaps are deployed at constant angle of attack the lift coefficient will: Report

decrease.

remain the same.

increase

12) An aeroplane has static directional stability; in a side-slip to the right, initially the: Report

nose of the aeroplane will remain in the same direction.

nose of the aeroplane tends to move to the left.

nose of the aeroplane tends to move to the right.

13) Which of the following statements is correct? Report

Static stability means that the aeroplane is also dynamically satble about the relevant axis.

Dynamic stability means that after being displaced from original equilibrium condition, the aeroplane will return to that condition without oscillation.

Dynamic stability is possible only when the aeroplane is statically stable about the relevant axis.

14) Which of the following will reduce induced drag? Report

Elliptical lift distribution.

Low aspect ratio.

Flying at high angles of attack.

15) Induced drag is created by the: Report

propeller wash blowing across the wing.

spanwise flow pattern resulting in the tip vortices.

interference of the air stream between wing and fuselage.

16) Vortex generators: Report

transfer energy from the free airflow into the boundary layer.

change the turbulent boundary layer into a laminar boundary layer.

reduce the spanwise flow on swept wing.

17) How does the total drag vary as speed is increased from stalling speed (VS) to maximum IAS (VNE) in a straight and level flight at constant weight? Report

Decreasing, then increasing.

Decreasing.

Increasing.

18) The aerofoil polar is: Report

the relation between the horizontal and the vertical speed.

a graph, in which the thickness of the wing aerofoil is given as a function of the chord.

a graph of the relation between the lift coefficient and the drag coefficient.

19) The Mach trim system will: Report

pump the fuel from tank to tank, depending on the Mach Number.

adjust the elevator trim tab, depending on the Mach Number.

adjust the stabilizer, depending on the Mach Number.

20) The lift coefficient (CL) of an aeroplane in steady horizontal flight is 0.35. Increase in angle of attack of 1 degree will increase CL by 0.079. A vertical up gust instantly changes the angle of attack by 2 degrees. The load factor will be : Report

1.45

0.9

0.45

EASA Questions Principles Of Flight Control

Subsonic Aerodynamics

Transonic Aerodynamics

Supersonic Aerodynamics

Stability

Control