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Questions for INDIGO AERODYNAMIC 5259-5689

Answer the following questions

1.

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?

2.

In a turn, the load factor n and the stalling speed VS will be

3.

Differential aileron deflection

4.

If flaps are deployed at constant IAS in straight and level flight, the magnitude of tip vortices will eventually : (flap span less than wing span)

5.

In the transonic range the aeroplane characteristics are strongly determined by

6.

For a fixed-pitch propeller designed for cruise, the angle of attack of each blade, measured at the reference section

7.

Which one of the following statements about the lift-to-drag ratio in straight and level flight is correct?

8.

When an aeroplane with the centre of gravity forward of the centre of pressure of the combined wing / fuselage is in straight and level flight, the vertical load on the tailplane will be

9.

Vortex generators mounted on the upper wing surface will

10.

After the transition point between the laminar and turbulent boundary layer

11.

The function of the stick pusher is

12.

The maximum acceptable cruising altitude is limited by a minimum acceptable loadfactor because exceeding that altitude

13.

Which statement is correct about a normal shock wave ?

14.

The stall speed

15.

What is the effect on the aeroplane's static longitudinal stability of a shift of the centre of gravity to a more aft location and on the required control deflection for a certain pitch up or down?

16.

A deployed slat will

17.

On an asymmetrical, single curve aerofoil, in subsonic airflow, at low angle of attack, when the angle of attack is increased, the centre of pressure will (assume a conventional transport aeroplane)

18.

""Flutter"" may be caused by

19.

Which of the following statements about stall speed is correct ?

20.

The aspect ratio of the wing

21.

If you pull back the RPM lever of a constant speed propeller during a glide with idle power and constant speed, the propeller pitch will

22.

During an erect spin recovery

23.

An aeroplane that has positive static stability

24.

A jet aeroplane equipped with inboard and outboard ailerons is cruising at its normal cruise Mach number. In this case

25.

How is adverse yaw compensated for during entry into and roll out from a turn ?

26.

Which of the following factors will lead to an increase of ground distance during a glide ?

27.

Mcrit is the free stream Mach Number at which

28.

A horn balance in a control system has the following purpose

29.

An aeroplane has static directional stability, in a side-slip to the right, initially the

30.

How does the exterior view of an aeroplane change, when the trim is used during a speed decrease ?

31.

Which is one of the disadvantages of increasing the number of propeller blades ?

32.

Which of the following flight phenomena can only happen at Mach Numbers above the critical Mach Number?

33.

When the air is passing through a shock wave the density will

34.

If an aeroplane flies in the ground effect

35.

""Tuck under"" is

36.

If you increase the propeller pitch during a glide with idle-power at constant IAS the lift to drag ratio will

37.

When the air is passing through an expansion wave the static temperature will

38.

One method to compensate adverse yaw is a

39.

Which kind of boundary layer has the strongest change in velocity close to the surface?

40.

If you decrease the propeller pitch during a glide with idle-power at constant IAS the lift to drag ratio will

41.

At what speed does the front of a shock wave move across the earth's surface?

42.

Which one of the following statements about the dynamic stability of a conventional aeroplane about the lateral axis is correct?

43.

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

44.

The consequences of exceeding Mcrit in a swept-wing aeroplane may be : (assume no corrective devices, straight and level flight)

45.

The unit of measurement of pressure is

46.

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

47.

The aerofoil polar is

48.

A propeller is turning to the right, seen from behind. The asymmetric thrust effect is mainly induced by

49.

Low speed pitch up is caused by the

50.

The induced drag