Vayudoot Aviation

1.
Ground effect has the following influence on the landing distance

increases, only if the landing flaps are fully extended.

does not change

increases.

decreases.

2.
Compared with stalling airspeed (VS) in a given configuration, the airspeed at which stick shaker will be triggered is

greater than VS

1.12 VS

1.20 VS.

1.30 VS.

3.
The effects of very heavy rain (tropical rain) on the aerodynamic characteristics of an aeroplane are

decrease of CLmax and decrease of drag

increase of CLmax and increase of drag

increase of CLmax and decrease of drag

decrease of CLmax and increase of drag

4.
In transonic flight the ailerons will be less effective than in subsonic flight because

aileron down deflection moves the shock wave forward

behind the shock wave pressure is lower

aileron deflection only affects the air in front of the shock wave.

aileron deflection only partly affects the pressure distribution around the wing

5.
An engine failure can result in a windmilling (1) propeller and a non rotating (2) propeller. Which statement about propeller drag is correct?

(1) is larger than (2).

(1) is equal to (2).

(2) is larger than (1).

impossible to say which one is largest.

6.
What happens during an engine failure with two similar aeroplanes with wing mounted engines, one of them with jet engines, the other one with co-rotating propellers

More roll tendency for the propeller aeroplane

The same yaw tendency for both aeroplanes regardless of left or right engine failure.

The same roll tendency for both aeroplanes

Less roll tendency for the propeller aeroplane

7.
What will increase the sensitivity to Dutch Roll?

An increased anhedral

An increased static lateral stability.

A forward movement of the centre of gravity.

An increased static directional stability

8.
Which statement is correct about a normal shock wave ?

The airflow expands when passing the aerofoil

The airflow changes direction

The airflow changes from supersonic to subsonic

The airflow changes from subsonic to supersonic

9.
The ""short period mode"" is an

unstable movement of the aeroplane, induced by the pilot

oscillation about the longitudinal axis

oscillation about the lateral axis

oscillation about the vertical axis.

10.
Which combination of design features is known to be responsible for deep stall?

Straight wings and a T-tail

Swept back wings and a T-tail

Swept back wings and wing mounted engines

Straight wings and aft fuselage mounted engines

11.
The critical angle of attack

increases if the CG is moved forward

decreases if the CG is moved aft

remains unchanged regardless of gross weight

changes with an increase in gross weight

12.
A strongly swept back wing stalls. If the wake of the wing contacts the horizontal tail, the effect on the stall behaviour can be

nose up tendency and/or lack of elevator response

nose down tendency

increase sensitivity of elevator inputs

tendency to increase speed after initial stall

13.
If the altitude is increased and the TAS remains constant in the standard troposphere the Mach Number will

increase or decrease, depends of the type of aeroplane

not change.

decrease.

increase.

14.
An aeroplane has a stall speed of 78 KCAS at its gross weight of 6850 Ibs. What is the stall speed when the weight is 5000 Ibs ?

91 KCAS

57 KCAS

78 KCAS

67 KCAS

15.
The stalling speed in IAS will change according to the following factors

Will increase in a turn, higher temperature and will increase when the c.g. moves aft

May increase when the c.g. moves forward, with higher altitude and due to the slip stream from a propellor on an engine located forward of the wing

Will increase with increased load factor, more flaps and increased bank angle in a turn

May increase with altitude, especially high altitude, will increase during icing conditions and will increase when the c.g. moves forward

16.
Slat extension will

increase critical angle of attack.

create gaps between leading edge and engine nacelles.

decrease the energy in the boundary layer on the upperside of the wing

increase critical angle of attack.

17.
Does the pitch-angle of a constant-speed propeller alter in medium horizontal turbulence?

No.

Yes, but only if the pitch is full-fine.

Yes strongly

Yes slightly

18.
Shock induced separation results in

increasing lift.

decreasing drag

constant lift.

decreasing lift

19.
The (1) stick force stability and the (2) manoeuvre stability are positively affected by

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

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

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

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

20.
When the air is passing through an expansion wave the static temperature will

decrease and beyond a certain Mach number start increasing again

increase.

decrease.

stay constant

21.
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 is incorrect and 2 is correct.

1 and 2 are correct.

1 and 2 are incorrect

1 is correct and 2 is incorrect

22.
What will happen in ground effect ?What will happen in ground effect ?

a significant increase in thrust required

the wing downwash on the tail surfaces increases

an increase in strength of the wing tip vortices

the induced angle of attack and induced drag decreases

23.
To be able to predict compressibility effects you have to determine the

IAS.

TAS.

EAS.

Mach Number

24.
The following unit of measurement: kgm/s² is expressed in the SI-system as

Newton

Watt

Joule

Pascal

25.
""Flutter"" may be caused by

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

low airspeed aerodynamic wing stall.

high airspeed aerodynamic wing stall

roll control reversal

26.
In the transonic range lift will decrease at the shock stall due to the

appearance of the bow wave

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

attachment of the shock wave on the trailing edge of the wing.

separation of the boundary layer at the shock waves.

27.
The bow wave will appear first at

M= 1.0

M= 1.3

M= Mcrit

M= 0.6

28.
In a two-dimensional flow pattern, where the streamlines converge the static pressure will

increase.

increase initially, then decrease.

decrease.

not change.

29.
The induced angle of attack is the result of

downwash due to flow separation

downwash due to tip vortices.

a large local angle of attack in a two dimensional flow.

change in direction of flow due to the effective angle of attack.

30.
An aeroplane performs a continuous descent with 160 kts IAS and 1000 feet/min vertical speed. In this condition

weight is greater than lift

drag is less than the combined forces that move the aeroplane forward

lift is less than drag

lift is equal to weight

31.
After a disturbance about the lateral axis, an aeroplane oscillates about the lateral axis at a constant amplitude. The aeroplane is

Statically unstable - Dynamically neutral

Statically stable - Dynamically unstable

Statically stable - Dynamically neutral

Statically unstable - Dynamically stable

32.
The angle between the airflow (relative wind) and the chord line of an aerofoil is

glide path angle

angle of attack

climb path angle

same as the angle between chord line and fuselage axis.

33.
In which phase of the take-off is the aerodynamic effect of ice located on the wing leading edge most critical?

The take-off run.

During climb with all engines operating.

All phases of the take-off are equally critical.

The last part of the rotation

34.
When the blades of a propeller are in the feathered position

the propeller produces an optimal windmilling RPM

the drag of the propeller is then minimal

the RPM is then just sufficient to lubricate the engine

the windmilling RPM is the maximum

35.
Positive static stability of an aeroplane means that once it has been displaced the

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

initial tendency to move is away from its equilibrium position

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

initial tendency to move is towards its equilibrium position

36.
An aeroplane has a stall speed of 100 kt at a load factor n=1. In a turn with a load factor of n=2, the stall speed is

282 kt

141 kt

70 kt

200 kt

37.
Vortex generators on the upper side of the wing surface will

increase the magnitude of the shock wave.

decrease the span wise flow at high Mach Numbers

decrease the intensity of shock wave induced air separation

increase the critical Mach Number

38.
The regime of flight from the critical Mach number up to M = 1.3 is called the

supersonic range

transonic range

subsonic range

hypersonic range

39.
Examples of aerodynamic balancing of control surfaces are

mass in the nose of the control surface, horn balance and mass balance.

servo tab, spring tab, seal between the wing trailing edge and the leading edge of control surface.

spring tab, servo tab, and power assisted control

balance tab, horn balance, and mass balance

40.
What is the effect on induced drag of weight and speed changes ?

induced drag increases with decreasing speed and induced drag increases with increasing weight

induced drag increases with increasing speed and induced drag increases with decreasing weight

induced drag decreases with increasing speed and induced drag decreases with decreasing weight

induced drag decreases with decreasing speed and induced drag decreases with increasing weight

41.
The high speed buffet is induced by

boundary layer control

a shift of the centre of gravity.

boundary layer separation due to shock waves

expansion waves on the wing upper side.

42.
Longitudinal static stability is created by the fact that the

centre of gravity is located in front of the neutral point of the aeroplane

wing surface is greater than the horizontal tail surface

centre of gravity is located in front of the leading edge of the wing

aeroplane possesses a large trim speed range.

43.
The value of the parasite drag in straight and level flight at constant weight varies linearly with the

speed.

angle of attack

square of the speed

square of the angle of attack.

44.
Compared with level flight prior to the stall, the lift (1) and drag (2) in the stall change as follows

(1) decreases (2) increases.

(1) decreases (2) decreases.

(1) increases (2) decreases.

(1) increases (2) increases

45.
Which statement is correct about an expansion wave in a supersonic flow ?1- The density in front of an expansion wave is higher than behind.2- The pressure in front of an expansion wave is higher than behind

1 is correct and 2 is incorrect

1 is incorrect and 2 is correct.

1 and 2 are incorrect

1 and 2 are correct

46.
Which of the following statements, about a venturi in a sub-sonic airflow are correct?1. the dynamic pressure in the undisturbed flow and in the throat are equal.2. the total pressure in the undisturbed flow and in the throat are equal

1 is correct and 2 is incorrect.

1 and 2 are correct.

1 and 2 are incorrect.

1 is incorrect and 2 is correct

47.
If an aeroplane is flying at transonic speed with increasing Mach number the shock wave on the upper side of the wing

moves into trailing edge direction

stays all the time at the same position.

disappears.

moves into leading edge direction

48.
The aerofoil polar is

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

the relation between the horizontal and the vertical speed

a graph of the relation between the lift coefficient and the angle of attack.

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

49.
One advantage of a movable-stabilizer system compared with a fixed stabilizer system is that

it is a more powerful means of trimming

the structure weighs less

it leads to greater stability in flight

the system's complexity is reduced

50.
In the transonic range the aeroplane characteristics are strongly determined by

the Mach Number

the CAS.

the IAS.

the TAS

Question Bank

Questions for INDIGO AERODYNAMIC 5259-5689

Ground effect has the following influence on the landing distance

Compared with stalling airspeed (VS) in a given configuration, the airspeed at which stick shaker will be triggered is

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

In transonic flight the ailerons will be less effective than in subsonic flight because

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

What happens during an engine failure with two similar aeroplanes with wing mounted engines, one of them with jet engines, the other one with co-rotating propellers

What will increase the sensitivity to Dutch Roll?

Which statement is correct about a normal shock wave ?

The ""short period mode"" is an

Which combination of design features is known to be responsible for deep stall?

The critical angle of attack

A strongly swept back wing stalls. If the wake of the wing contacts the horizontal tail, the effect on the stall behaviour can be

If the altitude is increased and the TAS remains constant in the standard troposphere the Mach Number will

An aeroplane has a stall speed of 78 KCAS at its gross weight of 6850 Ibs. What is the stall speed when the weight is 5000 Ibs ?

The stalling speed in IAS will change according to the following factors

Slat extension will

Does the pitch-angle of a constant-speed propeller alter in medium horizontal turbulence?

Shock induced separation results in

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

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

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

What will happen in ground effect ?What will happen in ground effect ?

To be able to predict compressibility effects you have to determine the

The following unit of measurement: kgm/s² is expressed in the SI-system as

""Flutter"" may be caused by

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

The bow wave will appear first at

In a two-dimensional flow pattern, where the streamlines converge the static pressure will

The induced angle of attack is the result of

An aeroplane performs a continuous descent with 160 kts IAS and 1000 feet/min vertical speed. In this condition

After a disturbance about the lateral axis, an aeroplane oscillates about the lateral axis at a constant amplitude. The aeroplane is

The angle between the airflow (relative wind) and the chord line of an aerofoil is

In which phase of the take-off is the aerodynamic effect of ice located on the wing leading edge most critical?

When the blades of a propeller are in the feathered position

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

An aeroplane has a stall speed of 100 kt at a load factor n=1. In a turn with a load factor of n=2, the stall speed is

Vortex generators on the upper side of the wing surface will

The regime of flight from the critical Mach number up to M = 1.3 is called the

Examples of aerodynamic balancing of control surfaces are

What is the effect on induced drag of weight and speed changes ?

The high speed buffet is induced by

Longitudinal static stability is created by the fact that the

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

Compared with level flight prior to the stall, the lift (1) and drag (2) in the stall change as follows

Which statement is correct about an expansion wave in a supersonic flow ?1- The density in front of an expansion wave is higher than behind.2- The pressure in front of an expansion wave is higher than behind

Which of the following statements, about a venturi in a sub-sonic airflow are correct?1. the dynamic pressure in the undisturbed flow and in the throat are equal.2. the total pressure in the undisturbed flow and in the throat are equal

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

The aerofoil polar is

One advantage of a movable-stabilizer system compared with a fixed stabilizer system is that

In the transonic range the aeroplane characteristics are strongly determined by