Vayudoot Aviation

1.
The boundary layer of a wing is caused by

the normal shock wave at transonic speeds

suction at the upper wing side.

a turbulent stream pattern around the wing.

a layer on the wing in which the stream velocity is lower than the free stream velocity, due to friction

2.
Lift and drag on an aerofoil are vertical respectively parallel to the

horizon.

longitudinal axis

chord line

relative wind/airflow

3.
Two identical aeroplanes A and B are flying horizontal steady turns. Further data are:A:W= 1500 kgBank= 20°TAS= 130 ktB:W= 1500 kgBank= 20°TAS= 200 ktWhich of the following statements is correct?

The load factor A is larger than the load factor B.

The turn radius A is larger than the turn radius B.

The rate of turn A is larger than the rate of turn B.

The lift coefficient A is smaller than the lift coefficient B.

4.
Which of the following flight phenomena can happen at Mach Numbers below the critical Mach Number?

Dutch roll

Mach buffet

Tuck under

Shock stall

5.
An aeroplane has static directional stability, in a side-slip to the right, initially the

nose of the aeroplane tends to move to the right.

right wing tends to go down.

nose of the aeroplane will remain in the same direction

nose of the aeroplane tends to move to the left

6.
When power assisted controls are used for pitch control, this

ensures that a part of the aerodynamic forces is still felt on the column

makes aerodynamic balancing of the control surfaces meaningless

makes trimming superfluous

can only function in combination with an elevator trim tab.

7.
On a wing fitted with a ""fowler"" type trailing edge flap, the ""Full extended"" position will produce

an unaffected wing area and increase in camber

an increase in wing area and camber

an increase in wing area only

an unaffected CD, at a given angle of attack

8.
The effect of a high wing with zero dihedral is as follows

Zero dihedral effect

Its only purpose is to ease aeroplane loading

Positive dihedral effect

Negative dihedral effect

9.
What increases the stalling angle of attack ? Use of

fuselage mounted speed-brakes

spoilers

slats

flaps

10.
Compared with an oblique shock wave at the same Mach number a normal shock wave has a

higher loss in total pressure

higher total pressure

lower static temperature

higher total temperature

11.
The function of the stick pusher is

to pull the stick, to avoid a high speed stall

to activate and push the stick forward at or beyond a certain value of angle of attack.

to vibrate the controls

to activate and push the stick forward prior to stick shaker

12.
An aeroplane with swept back wings is equipped with slats and/or leading edge (L.E.) flaps. One possible efficient way to arrange the leading edge devices on the wings is

Wing roots: L.E. flapsWing tips: slats

Wing roots: slatsWing tips: no devices

Wing roots: slatsWing tips: L.E. flaps

Wing roots: L.E. flapsWing tips: no devices

13.
Dihedral of the wing

is the only way to increase the static lateral stability

is only positive for aeroplanes with high mounted wings.

increases the static lateral stability

decreases the static lateral stability.

14.
There are two types of boundary layer: laminar and turbulent. One important advantage the turbulent boundary layer has over the laminar type is that

energy is less

skin friction drag is less

it is thinner

it has less tendency to separate from the surface

15.
The effects of very heavy rain (tropical rain) on the aerodynamic characteristics of an aeroplane are

decrease of CLmax and decrease of drag

decrease of CLmax and increase of drag

increase of CLmax and decrease of drag

increase of CLmax and increase of drag

16.
The stall speed

does not depend on weight

increases with an increased weight

decreases with an increased weight

increases with the length of the wingspan

17.
When the air is passing through a shock wave the static temperature will

decrease.

decrease and beyond a certain Mach number start increasing again

increase.

stay constant

18.
Positive static stability of an aeroplane means that once it has been displaced the

tendency will be to move with an oscillating motion of decreasing amplitude

initial tendency to move is towards its equilibrium position

initial tendency to move is away from its equilibrium position

tendency will be to move with an oscillating motion of increasing amplitude

19.
Which one of the following statements about Bernoulli's theorem is correct?

The dynamic pressure increases as static pressure decreases

The dynamic pressure decreases as static pressure decreases

The dynamic pressure is maximum in the stagnation point

The total pressure is zero when the velocity of the stream is zero

20.
If the Mach number of an aeroplane in supersonic flight is increased, the shock wave angles will

stay constant

decrease.

increase.

decrease and beyond a certain Mach number start increasing again.

21.
For a normal stable aeroplane, the centre of gravity is located

aft of the neutral point of the aeroplane

with a sufficient minimum margin ahead of the neutral point of the aeroplane.

at the neutral point of the aeroplane.

between the aft limit and the neutral point of the aeroplane.

22.
By what percentage does the lift increase in a steady level turn at 45° angle of bank, compared to straight and level flight?

41%.

52%.

19%.

31%.

23.
The Cl - alpha curve of a positive cambered aerofoil intersects with the vertical axis of the Cl - alpha graph

nowhere.

above the origin

below the origin

in the origin.

24.
Some aeroplanes have a 'waist' or 'coke bottle' contoured fuselage. This is done to

improve the low speed characteristics

apply area rule.

increase the strength of the wing root junction.

fit the engine intakes better to the fuselage

25.
The use of a slot in the leading edge of the wing enables the aeroplane to fly at a slower speed because

it decelerates the upper surface boundary layer air

it delays the stall to a higher angle of attack

the laminar part of the boundary layer gets thicker

it changes the camber of the wing

26.
Deflection of leading edge flaps will

increase critical angle of attack

decrease drag

not affect critical angle of attack

decrease CLmax

27.
Which statement is correct about a normal shock wave ?

The airflow changes direction

The airflow changes from supersonic to subsonic

The airflow changes from subsonic to supersonic

The airflow expands when passing the aerofoil

28.
A propeller is turning to the right, seen from behind. The asymmetric thrust effect is mainly induced by

high speed

large angles of climb

high angles of attack.

large angles of yaw.

29.
After take-off the slats (when installed) are always retracted later than the flaps. Why ?

Because FLAPS EXTENDED gives a large decrease in stall speed with relatively less drag.

Because SLATS EXTENDED gives a large decrease in stall speed with relatively less drag

Because VMCA with SLATS EXTENDED is more favourable compared to the FLAPS EXTENDED situation

Because SLATS EXTENDED provides a better view from the cockpit than FLAPS EXTENDED

30.
A light twin is in a turn at 20 degrees bank and 150 kt TAS. A more heavy aeroplane at the same bank and the same speed will

turn at a smaller turn radius.

turn at a higher turn rate

turn at the same turn radius

turn at a bigger turn radius

31.
The true airspeed (TAS) is

equal to the IAS, multiplied by the air density at sea level.

higher than the speed of the undisturbed airstream about the aeroplane

lower than the speed of the undisturbed airstream about the aeroplane

lower than the indicated airspeed (IAS) at ISA conditions and altitudes below sea level.

32.
During initiation of a turn with speedbrakes extended, the roll spoiler function induces a spoiler deflection

upward on the upgoing wing and downward on the downgoing wing.

on the upgoing wing only

on the downgoing wing only

downward on the upgoing wing and upward on the downgoing wing.

33.
""Flutter"" may be caused by

distorsion by bending and torsion of the structure causing increasing vibration in the resonance frequency

roll control reversal

low airspeed aerodynamic wing stall.

high airspeed aerodynamic wing stall

34.
One disadvantage of the swept back wing is it's stalling characteristics. At the stall

tip stall will occur first, which produces a nose-down moment

tip stall will occur first, which produces a pitch-up moment.

leading edge stall will occur first, which produces a nose-down moment

wing root stall will occur first, which produces a rolling moment

35.
In what way do (1) induced drag and (2) parasite drag alter with increasing speed?

(1) decreases and (2) decreases.

(1) increases and (2) decreases.

(1) increases and (2) increases

(1) decreases and (2) increases

36.
Which of the following statements about dihedral is correct?

Dihedral is necessary for the execution of slip-free turns

The ""effective dihedral"" of an aeroplane component means the contribution of that component to the static lateral stability

Dihedral contributes to dynamic but not to static lateral stability

Effective dihedral is the angle between the 1/4-chord line and the lateral axis of the aeroplane

37.
Sensitivity for spiral dive will occur when

the dutch roll tendency is too strongly suppressed by the yaw damper.

the static directional stability is positive and the static lateral stability is relatively weak

the static directional stability is negative and the static lateral stability is positive

the static lateral and directional stability are both negative

38.
The max aft position of the centre of gravity is amongst others limited by the

maximum longitudinal stability of the aeroplane

maximum elevator deflection

too small effect of the controls on the aeroplane

minimum value of the stick force per g.

39.
The relative thickness of an aerofoil is expressed in

% chord

meters.

camber.

degrees cross section tail angle.

40.
An engine failure can result in a windmilling (1) propeller and a non rotating (2) propeller. Which statement about propeller drag is correct?

(2) is larger than (1).

(1) is larger than (2).

(1) is equal to (2).

impossible to say which one is largest.

41.
Which statement is correct about the gust load on an aeroplane (IAS and all other factors of importance remaining constant) ?1. the gust load increases, when the weight decreases.2. the gust load increases, when the altitude increases

1 and 2 are incorrect

1 is correct and 2 is incorrect

1 and 2 are correct.

1 is incorrect and 2 is correct.

42.
I is incorrect, II is correct

1998-10-05 0:00

I is correct, II is incorrect

I is correct, II is correct

I is incorrect, II is incorrect

43.
The vane of a stall warning system with a flapper switch is activated by the change of the

centre of gravity

stagnation point

point of lowest pressure.

centre of pressure.

44.
The value of the induced drag of an aeroplane in straight and level flight at constant weight varies linearly with

V

1/V

1/V²

V²

45.
The (1) stick force stability and the (2) manoeuvre stability are positively affected by

(1) forward C.G. position (2) forward CG. position

(1) aft C.G. position (2) aft CG. position.

(1) forward C.G. position (2) aeroplane nose up trim.

(1) aeroplane nose up trim (2) aeroplane nose up trim.

46.
The shape of the gust load diagram is also determinated by the following three vertical speed in ft/s (clean configuration)

15, 56, 65

25, 50, 66

35, 55, 66

25, 55, 75

47.
Increasing air pressure will have the following effect on the drag of an aeroplane (angle of attack, OAT and TAS are constant)

The drag is only affected by the ground speed.

This has no effect

The drag increases

The drag decreases

48.
An aeroplane that has positive static stability

is never dynamically stable

can be dynamically stable, neutral or unstable

is always dynamically stable.

is always dynamically unstable.

49.
Which combination of speeds is applicable for structural strength in gust (clean configuration) ?

55 ft/sec and VB.

50 ft/sec and VC.

65 ft/sec at all speeds.

66 ft/sec and VD.

50.
Why is a propeller blade twisted from root to tip?

Because the local angle of attack of a blade segment is dependent on the ratio of that segment 's speed in the plane of rotation and the true airspeed of the aeroplane

Because the local angle of attack of a blade segment is dependent on the ratio of that segment 's speed in the plane of rotation and the angular velocity of the propellers

To ensure that the tip produces most thrust.

To ensure that the root produces most thrust.

Question Bank

Questions for INDIGO AERODYNAMIC 5259-5689

The boundary layer of a wing is caused by

Lift and drag on an aerofoil are vertical respectively parallel to the

Two identical aeroplanes A and B are flying horizontal steady turns. Further data are:A:W= 1500 kgBank= 20°TAS= 130 ktB:W= 1500 kgBank= 20°TAS= 200 ktWhich of the following statements is correct?

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

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

When power assisted controls are used for pitch control, this

On a wing fitted with a ""fowler"" type trailing edge flap, the ""Full extended"" position will produce

The effect of a high wing with zero dihedral is as follows

What increases the stalling angle of attack ? Use of

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

The function of the stick pusher is

An aeroplane with swept back wings is equipped with slats and/or leading edge (L.E.) flaps. One possible efficient way to arrange the leading edge devices on the wings is

Dihedral of the wing

There are two types of boundary layer: laminar and turbulent. One important advantage the turbulent boundary layer has over the laminar type is that

The effects of very heavy rain (tropical rain) on the aerodynamic characteristics of an aeroplane are

The stall speed

When the air is passing through a shock wave the static temperature will

Positive static stability of an aeroplane means that once it has been displaced the

Which one of the following statements about Bernoulli's theorem is correct?

If the Mach number of an aeroplane in supersonic flight is increased, the shock wave angles will

For a normal stable aeroplane, the centre of gravity is located

By what percentage does the lift increase in a steady level turn at 45° angle of bank, compared to straight and level flight?

The Cl - alpha curve of a positive cambered aerofoil intersects with the vertical axis of the Cl - alpha graph

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

The use of a slot in the leading edge of the wing enables the aeroplane to fly at a slower speed because

Deflection of leading edge flaps will

Which statement is correct about a normal shock wave ?

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

After take-off the slats (when installed) are always retracted later than the flaps. Why ?

A light twin is in a turn at 20 degrees bank and 150 kt TAS. A more heavy aeroplane at the same bank and the same speed will

The true airspeed (TAS) is

During initiation of a turn with speedbrakes extended, the roll spoiler function induces a spoiler deflection

""Flutter"" may be caused by

One disadvantage of the swept back wing is it's stalling characteristics. At the stall

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

Which of the following statements about dihedral is correct?

Sensitivity for spiral dive will occur when

The max aft position of the centre of gravity is amongst others limited by the

The relative thickness of an aerofoil is expressed in

An engine failure can result in a windmilling (1) propeller and a non rotating (2) propeller. Which statement about propeller drag is correct?

Which statement is correct about the gust load on an aeroplane (IAS and all other factors of importance remaining constant) ?1. the gust load increases, when the weight decreases.2. the gust load increases, when the altitude increases

I is incorrect, II is correct

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

The value of the induced drag of an aeroplane in straight and level flight at constant weight varies linearly with

The (1) stick force stability and the (2) manoeuvre stability are positively affected by

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

Increasing air pressure will have the following effect on the drag of an aeroplane (angle of attack, OAT and TAS are constant)

An aeroplane that has positive static stability

Which combination of speeds is applicable for structural strength in gust (clean configuration) ?

Why is a propeller blade twisted from root to tip?