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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.

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

3.

The location of the centre of pressure of a positive cambered wing at increasing angle of attack will

4.

An aeroplane has a stalling speed of 100 kt in a steady level flight. When the aeroplane is flying a level turn with a load factor of 1.5, the stalling speed is

5.

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

6.

Which of the following are used as stall warning devices?

7.

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

8.

The induced angle of attack is the result of

9.

When the C.G. position is moved forward, the elevator deflection for a manoeuvre with a load factor greater than 1 will be

10.

Vortex generators on the upper side of the wing

11.

Deploying a Fowler flap, the flap will

12.

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

13.

The effect of a positive wing sweep on static directional stability is as follows

14.

The vane of a stall warning system with a flapper switch is activated by the change of the

15.

Which statement about the trim position is true related to centre of gravity and adjustable stabiliser position ?

16.

Which of the following wing planforms produces the lowest induced drag? (all other relevant factors constant)

17.

Dihedral of the wing is

18.

Which load factor determines VA?

19.

The buffet margin

20.

The loss of total pressure in a shock wave is due to the fact that

21.

What wing shape or wing characteristic is the least sensitive to turbulence

22.

Some aeroplanes have a 'waist' or 'coke bottle' contoured fuselage. This is done to

23.

The shape of the gust load diagram is also determinated by the following three vertical speed in ft/s (clean configuration)

24.

The value of the manoeuvre stability of an aeroplane is 150 N/g. The load factor in straight and level flight is 1. The increase of stick force necessary to achieve the load factor of 2.5 is

25.

From the polar diagram of the entire aeroplane one can read

26.

Which statement about a primary control surface controlled by a servo tab, is correct ?

27.

Dihedral of the wing

28.

When flutter damping of control surfaces is obtained by mass balancing, these weights will be located with respect to the hinge of the control surface

29.

What is the approximate value of the lift of an aeroplane at a gross weight of 50 000 N, in a horizontal coordinated 45 degrees banked turn ?

30.

When an aeroplane is flying at an airspeed which is 1.3 times its basic stalling speed, the coefficient of lift as a percentage of the maximum lift coefficient (CLmax) would be

31.

During landing of a low-winged jet aeroplane, the maximum elevator up deflection is normally required when the flaps are

32.

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

33.

Which statement with respect to the climb is correct ?

34.

Mcrit is the free stream Mach Number at which

35.

How does stalling speed (IAS) vary with altitude?

36.

The trailing edge flaps when extended

37.

Which of the following statements about boundary layers is correct?

38.

Which moments or motions interact in a dutch roll?

39.

What factors determine the distance travelled over the ground of an aeroplane in a glide ?

40.

""Tuck under"" is

41.

What will increase the sensitivity to Dutch Roll?

42.

In what way do (1) induced drag and (2) parasite drag alter with increasing speed?

43.

""Flutter"" may be caused by

44.

When air has passed through a shock wave the speed of sound is

45.

If the total sum of moments about one of its axis is not zero, an aeroplane

46.

Which of the following statements is correct ?I When the critical engine fails during take-off the speed VMCL can be limiting.II The speed VMCL is always limited by maximum rudder deflection

47.

One of the requirements for dynamic stability is

48.

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

49.

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

50.

In order to maintain straight and level flight at a constant airspeed, whilst the flaps are being retracted, the angle of attack will