Principles of Flight - ATPL - Airline Transport Pilot license

Test 10 domande Principles of Flight, tempo libero

1 - Upon extension of a spoiler on a wing: Only CL is decreased (CD remains unaffected) CD is increased and CL is decreased CD is increased, while CL remains unaffected Both CL and CD are increased

2 - Positive static longitudinal stability means that a: Nose-up moment occurs with a speed change at constant angle of attack. Nose-down moment occurs after encountering an up-gust. Nose-up moment occurs after encountering an up-gust. Nose-down moment occurs with a speed change at constant angle of attack.

3 - The airload on the horizontal tailplane (tailload) of an aeroplane in straight and level flight: Is in general directed downwards and will become less negative when the c.g. moves aft. Is in general directed downwards and will always become less negative in a linear fashion with increasing airspeed. Will in principle be zero on transport aeroplanes without an electronic flight control system (Fly- by-Wire) due to the trim system. Is in general directed upwards and will increase when c.g. is moved forward.

4 - When comparing a rectangular wing and a swept back wing of the same wing area and wing loading, the swept back wing has the advantage of: Greater strength Increased longitudinal stability Higher critical Mach number Lower stalling speed

5 - When the air is passing through a shock wave the static temperature will Stay constant. Decrease. Decrease and beyond a certain Mach number start increasing again Increase.

6 - How does positive camber of an aerofoil affect static longitudinal stability? Positive effect, because the centre of pressure shifts rearward at increasing angle of attack No effect, because camber of the aerofoil produces a constant pitch down moment coefficient, independent of angle of attack Positive effect, because the lift vector rotates backward at increasing angle of attack Negative effect, because the lift vector rotates forward at increasing angle of attack

7 - Static pressure acts: Only in direction of the flow Only perpendicular to the direction of the flow In all directions Only in the direction of the total pressure

8 - Tuck under will happen Only below the critical Mach number. Only at the critical Mach number. Above or below the critical Mach number depending on the angle of attack. Only above the critical Mach number.

9 - If you increase the propeller pitch during a glide with idle-power at constant IAS the lift to drag ratio will Decrease and the rate of descent will decrease. Increase and the rate of descent will increase. Decrease and the rate of descent will increase. Increase and the rate of descent will decrease.

10 - The angle of attack of a blade section is the angle between the chord line and the: Induced airflow. Rotational airflow. Plane of rotation. Relative airflow.

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