Principle of flight (All Questions)

1. Question

An increase in aspect ratio will:

Select one:

cause induced drag to increase.
cause VIMD to be reduced.
cause VIMD to be increased.
have no effect on a wing or airfoil section.

2. Question

An aeroplane has a stall speed of 78 KCAS at its gross weight of 6.850 lbs. What is the stall speed when the weight is 5.000 lbs?

Select one:

67 KCAS
57 KCAS
91 KCAS
78 KCAS

3. Question

Angle of attack is the angle between:

Select one:

local airflow and chord line.
local airflow and mean camber line.
undisturbed airflow and chord line.
undisturbed airflow and mean camber line.

4. Question

A laminar boundary layer is a layer, in which:

Select one:

the vortices, are weak.
the temperature varies constantly.
the velocity is constant.
no velocity components exist normal to the surface.

5. Question

As it applies to airfoils. Which statement is in agreement with Bernoullis Principle?

Select one:

The static pressure of a fluid decreases at points where the speed of the fluid decreases.
The speed of a fluid increases at points where the static pressure of the fluid increases.
The static pressure of a fluid decreases at points where the speed of the fluid increases.
The static pressure of a fluid increases at points where the speed of the fluid increases.

6. Question

A line connecting the leading- and trailing edge midway between the upper and lower surface of a aerofoil. This definition is applicable for:

Select one:

the camber line.
the mean aerodynamic chord line.
the upper camber line.
the chord line.

7. Question

As subsonic air flows through a convergent duct: i. static pressure ii. velocity

Select one:

(i) decreases and (ii) increases
(i) increases and (ii) decreases
(i) decreases and (ii) decreases
(i) increases and (ii) increases

8. Question

A low wing loading (aircraft weight has been reduced):

Select one:

does not affect any of the above.
increases stalling speed.
decreases stalling speed and landing speed.
increases take-off run, stalling speed and landing speed.

9. Question

As the angle of attack of a wing is increased in level flight:

Select one:

the C of G moves aft and the C of P forward.
the C of P and transition point move forward.
the C of P moves aft and the separation point forward.
the C of P moves forward and the stagnation point aft over the upper surface.

10. Question

A reduction in air pressure results in:

Select one:

no significant change in density.
a reduction in density.
an increase in density.
erratic variations in density.

11. Question

As the angle of attack of a wing is increased, the centre of pressure will reach its most forward position on the wing…

Select one:

after stall recovery.
just before the wing stalls.
when the aircraft is stalling.
at the optimum angle of attack.

12. Question

A symmetrical aerofoil section at CL = 0 will produce?

Select one:

A positive (nose up) pitching moment.
A negative (nose down) pitching moment.
No aerodynamic force.
Zero pitching moment.

13. Question

As the camber of an aerofoil section is increased:

Select one:

velocity of the airflow is decreased.
pressure over the upper surface is decreased.
pressure over the upper surface is increased.
pressure over the upper surface remains the same for any camber.

14. Question

A wing has a span of 50 feet and an area of 200 square feet. Its mean chord would be:

Select one:

10 feet
2.5 feet
7.5 feet
4 feet

15. Question

As the center of gravity is changed, recovery from a stall becomes progressively:

Select one:

is unaffected by center of gravity position, only by all up weight.
more difficult as the center of gravity moves aft.
less difficult as the center of gravity moves aft.
more difficult as the center of gravity moves forward.

16. Question

A wing stalling angle is:

Select one:

increased in a high rate of turn.
unaffected by a turn.
decreased in any turn.
decreased in a high rate of turn.

17. Question

At an aeroplanes minimum drag speed, what is the ratio between induced drag Di and profile drag Dp (Di/Dp)?

Select one:

2/1
1/2
It varies between aeroplane types.
1/1

18. Question

A wing will stall:

Select one:

at the stalling angle.
at the optimum angle of attack.
just below the stalling angle.
just above the stalling angle.

19. Question

At the point a wing enters a stalled condition:

Select one:

Lift and Drag rapidly reduce.
Lift slowly reduces and Drag rapidly increases.
Lift reduces sharply and Drag considerably increases.
Lift rapidly reduces and drag increases slightly.

20. Question

A wing with higher span compared with a lower wing span has (equal wing surface):

Select one:

lower induced drag.
a higher lift/drag ratio.
higher profile drag.
higher induced drag.

21. Question

At the point of stall:

Select one:

lift decreases, drag decreases.
lift decreases, drag increases.
lift decreases, drag constant.
lift constant, drag increases.

22. Question

At the same weight, with the CG at its forward limit:

Select one:

VS is lower, the stalling angle is unchanged.
VS is lower, the stalling angle is less.
VS is higher, the stalling angle is greater.
VS is higher, the stalling angle is unchanged.

23. Question

An aircraft flying straight and level; if density halves, aerodynamic drag will:

Select one:

increase by a factor of four.
increase by a factor of two.
decrease by a factor of two.
decrease by a factor of four.

24. Question

At the tip of the wing in level flight, the air flows:

Select one:

from the lower surface to the upper surface and then down at the trailing edge.
from the lower surface to the upper surface and then diverges away from the fuselage.
from the upper surface to the lower surface.
to produce induced drag at its lowest value.

25. Question

An aircraft whose weight is 237402 N stalls at 132 kt. At a weight of 356103 N it would stall at:

Select one:

88 kt
108 kt
162 kt
172 kt

26. Question

At zero angle of attack in flight, a symmetrical wing section will produce:

Select one:

some lift and drag.
zero lift with some drag.
some lift with some induced and profile drag.
zero lift and a lot of drag.

27. Question

An aircraft wing stalls at:

Select one:

a constant TAS.
a constant IAS.
a constant angle of attack.
a constant optimum angle of attack.

28. Question

A High Aspect Ratio wing is a wing with:

Select one:

long span, long chord.
long span, short chord.
short span, short chord.
short span, long chord.

29. Question

An increase in angle of attack (below the stalling angle of attack) increases lift because:

Select one:

induced drag is reduced.
the vertical component of weight is reduced.
the lift coefficient increases.
the impact pressure of the air on the lower surface of the airfoil creates less positive pressure.

30. Question

An increase in the speed at which an airfoil passes through the air increases lift because:

Select one:

the increased speed of air passing over the airfoils upper surface decreases the pressure, thus creating a greater pressure differential between upper and lower surface
the increased velocity of the relative wind increases the angle of attack
the impact pressure of the air on the lower surface of the airfoil creates less positive pressure
the increased speed of the airflow creates a lesser pressure differential between The upper and lower airfoil surfaces

31. Question

Total pressure of air will:

Select one:

not be affected by temperature.
increase with increased humidity.
reduce with increased humidity.
not be affected by moisture.

32. Question

A cambered airfoil with zero angle of attack, will in flight produce:

Select one:

no lift and no drag.
some lift with no drag.
no lift but some drag.
some lift and some drag.

33. Question

A deployed slat will:

Select one:

increase the boundary layer energy, move the suction peak from the fixed part of the wing to the slat, so that the stall is postponed to higher angles of attack.
decrease the boundary layer energy and decrease the suction peak on the slat, so that CLmax is reached at lower angles of attack.
increase the boundary layer energy and increase the suction peak on the fixed part of the wing, so that the stall is postponed to higher angles of attack.
increase the camber of the aerofoil and increase the effective angle of attack, so that CLmax is reached at higher angles of attack.v

34. Question

A Fowler flap is one which when selected:

Select one:

increases camber and wing area.
increases wing area only.
increases camber only.
dumps lift only.

35. Question

A plain flap will increase CLmax by:

Select one:

centre of lift movement.
increasing the camber of the aerofoil.
boundary layer control.
increasing angle of attack.

36. Question

A propeller blade is twisted from root to tip to:

Select one:

provide a constant angle of attack from root to tip.
to provide its greatest thrust toward the blade root.
to ensure its optimum thrust is always achieved at take off.
to prevent excessive stress at the blade tip at high R.P.M.

37. Question

A slotted flap will increase the CLmax by:

Select one:

decreasing the skin friction.
increasing the camber of the aerofoil and improving the boundary layer.
increasing the critical angle of attack
increasing only the camber of the aerofoil.

38. Question

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

Select one:

Because SLATS EXTENDED gives a large decrease in stall speed with relatively less drag.
Because SLATS EXTENDED provides a better view from the cockpit than FLAPS EXTENDED.
Because FLAPS 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.

39. Question

An aeroplane has the following flap settings: 0° , 15° , 30° and 45° . Slats can be selected too. Which of the above selections will produce the greatest negative influence on the CL/CD ratio?

Select one:

The slats.
Flaps from 30° to 45°.
Flaps from 0° to 15°.
Flaps from 15° to 30°.

40. Question

An aircraft is constructed with dihedral to provide:

Select one:

lateral stability about the longitudinal axis.
longitudinal stability about the lateral axis.
lateral stability about the normal axis.
lateral stability about the lateral axis.

41. Question

With the centre of gravity on the forward limit, the stalling speed would be:

Select one:

independent of the centre of gravity position.
the same as with the centre of gravity on the aft limit.
higher than with the centre of gravity on the aft limit.
lower than with the centre of gravity on the aft limit.

42. Question

With increasing speed in level flight:

Select one:

induced drag increases.
profile drag increases.
profile drag remains constant.
induced drag remains constant.

43. Question

With increasing angle of attack, the stagnation point will move (I) and the point of lowest static pressure will move (II):

Select one:

(I) down, (II) aft
(I) down, (II) forward
(I) up, (II) forward
(I) up, (II) aft

44. Question

With increasing angle of attack, the C of P on an airfoil will reach its most forward point:

Select one:

above the stalling angle.
below the stalling angle.
at the stalling angle.
at various points dependent on aircraft weight.

45. Question

With increasing altitude the following occurs:

Select one:

the stalling angle increases for a given indicated airspeed.
the stalling angle reduces for a given indicated airspeed.
drag remains the same for a given indicated airspeed.
drag reduces for a given indicated airspeed.

46. Question

With an increase of aircraft weight at a constant IAS:

Select one:

induced drag will remain constant.
profile drag will reduce.
induced drag will increase.

47. Question

With increasing altitude the angle at which a wing will stall:

Select one:

remains the same.
reduces.
increases.

48. Question

Winglets:

Select one:

create an elliptical lift distribution.
decrease the induced drag.
increase the manoeuvrability.
decrease the static lateral stability.

49. Question

With an increase in aspect ratio for a given IAS induced drag will:

Select one:

remain constant.
increase.
reduce.

50. Question

Which statement is true for a symmetrical wing section:

Select one:

the centre of pressure is at the aerodynamic centre of the wing.
the centre of pressure is in the front of the aerodynamic centre of the wing.
the centre of pressure is behind the aerodynamic centre of the wing.
the centre of pressure is infinitely far behind the wing.

51. Question

Which statement is correct about the Cl and angle of attack?

Select one:

For an asymmetric aerofoil, if angle of attack = 0, Cl =0
For an asymmetric aerofoil with positive camber, if angle of attack is greater than 0, Cl = 0
For a symmetric aerofoil, if angle of attack = 0, Cl =0
For a symmetric aerofoil, if angle of attack = 0, Cl is not equal to 0

52. Question

Which statement is correct?

Select one:

The stagnation point is always situated on the chord line, the centre of pressure is not
The stagnation point is another name for centre of pressure
As the angle of attack increases, the stagnation point on the wings profile moves downwards
The centre of pressure is the point on the wings leading edge where the airflow splits up

53. Question

Which statement about induced drag and tip vortices is correct?

Select one:

The flow direction at the upper side of the wing has a component in wing root direction, the flow at the underside of the wing in wing tip direction.
Tip vortices can be diminished by vortex generators.
The flow direction at the upper and under side of the wing, both deviate in wing tip direction.
The wing tip vortices and the induced drag decrease at increasing angle of attack.

54. Question

Which ratio is defined as the aspect ratio of a wing?

Select one:

Ratio between wing span and gross wing area.
Ratio between the span and the square of the gross wing area.
Ratio between the square of the span and the mean chord.
Ratio between span and mean chord.

55. Question

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

Select one:

The total pressure is zero when the velocity of the stream is zero.
The dynamic pressure increases as static pressure decreases.
The dynamic pressure is maximum in the stagnation point.
The dynamic pressure decreases as static pressure decreases.

56. Question

Which of the following would tend to increase the density altitude at a given airport?

Select one:

A large tailwind
An increase in ambient temperature
An increase in barometric pressure
A decrease in relative humidity

57. Question

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

New

Select one:

Rectangular.
Tapered.
Circular.
Elliptical.

58. Question

Which of the following wing planform gives the highest local lift coefficient at the wing root?

Select one:

Tapered.
Positive angle of sweep.
Elliptical.
Rectangular.

59. Question

Which of the following statements, about a venturi in a sub-sonic airflow are correct?

the dynamic pressure in the undisturbed flow and in the throat are equal.
the total pressure in the undisturbed flow and in the throat are equal.

Select one:

1 and 2 are correct.
1 is incorrect and 2 is correct.
1 is correct and 2 is incorrect.
1 and 2 are incorrect.

60. Question

Which of the following statements is true?

Select one:

Energy can be created and destroyed
Energy can be created but not be destroyed
Energy can not be created but destroyed
Energy can not be created nor destroyed

61. Question

Which of the following statements are correct?

Select one:

Lift acts at right angles to the top surface of the wing and drag acts at right angles to lift.
Lift acts perpendicular to the horizontal and drag parallel in a rearwards direction.
Drag acts in the same direction as the relative airflow and lift perpendicular to it.
Drag acts parallel to the chord and opposite to the direction of motion of the aircraft and lift acts perpendicular to the chord.

62. Question

Which of the following statements about the stall of a straight wing aeroplane is correct?

Select one:

The horizontal tail will stall at a higher speed than the wing.
Just before the stall the aeroplane will be have a nose-down tendency.
Buffeting is the result of flow separation on the tail plane.
The nose down effect is the result of increasing downwash, due to flow separation.

63. Question

Which of the following statements about the spin is correct?

Select one:

In the spin, airspeed continuously increases.
During spin recovery the ailerons should be kept in the neutral position.
An aeroplane is prone to spin when the stall starts at the wing root.
Every aeroplane should be designed such that it can never enter a spin.

64. Question

Which of the following situations leads to a decreasing stall speed (IAS)?

Select one:

increasing altitude.
increasing air density.
decreasing weight.
increasing load factor.

65. Question

Which of the following is the correct designation of stall speed in the landing configuration:

Select one:

VS1g
VS0
VSL
VS1

66. Question

Which of the following is the cause of wing tip vortices?

Select one:

Air spilling from the bottom surface to the top surface at the wing tip.
Air spilling from the top surface to the bottom surface at the wing tip.
Span wise flow vector from the tip to the root on the bottom surface of the wing.
Air spilling from the bottom surface to the top surface at the left wing tip and from the top. surface to the bottom surface at the right wing tip.

67. Question

Which of the following expressions could represent the relationship between force, mass and acceleration:

Select one:

F = m * a
a = F * m
a = m / F
m = F * a

68. Question

Which of the following descriptions most accurately describes the airflow that causes wing tip vortices?

Select one:

From the tip to the root on the top surface and from the root to the tip on the bottom surface over the trailing edge.
From the root to the tip on the top surface and from the tip to the root on the bottom surface over the trailing edge.
From the root to the tip on the top surface and from the tip to the root on the bottom surface over the wing tip.
From the tip to the root on the top surface and from the root to the tip on the bottom surface over the wing tip.

69. Question

Which of the following decreases induced drag?

Select one:

Anhedral.
Wing fences.
Winglets.
Low aspect ratio plan form.

70. Question

Which formula or equation describes the relationship between force (F), acceleration (a) and mass (m)?

Select one:

m = F*a
a = F*m
F = m/a
F = m*a

71. Question

Which location on the aeroplane has the largest effect on the induced drag?

Select one:

Engine cowling.
Wing tip.
Landing gear.
Wing root junction.

72. Question

Where does the lift act on the wing?

Select one:

Suction.
Centre of Pressure.
Centre of Gravity.
Always forward of the CG.

73. Question

When vortex generators are fitted they will normally be found:

Select one:

on the underside of the wing towards the leading edge.
towards the wing root to act as a stall inducer.
near the wing leading edge in front of control surfaces.
towards the wing trailing edge.

74. Question

When the angle of attack of a wing is increased:

Select one:

the boundary layer becomes thinner.
the transition point moves aft.
the boundary layer thickens.
boundary layer thickness is unaffected.

75. Question

When the angle of attack is increased, the stagnation point moves … and the separation point moves…

Select one:

Forward; Backwards
Backwards; Back
Backwards; Forward
Forward; Forward

76. Question

When the angle of attack increases in straight and level flight, we will observe:

Select one:

a reduction in varying loads due to g
lateral movement of the centre of gravity
forward movement of the centre of pressure
forward movement of the centre of gravity

77. Question

When recovering from a spin the pilot should first:

Select one:

reduce the angle of attack.
oppose the autorotation.
increase the angle of attack.
increase the drag yawing moment.

78. Question

When maintaining level flight an increase of speed will:

Select one:

have no effect on the C of P position.
cause the C of P to move forward.
cause the C of P to move aft.
cause the C of G to move forward.

79. Question

When looking at the airflow over the wing, from the wing surface and up, the air is:

Select one:

accelerated to the transition point.
decelerated to the transition point.
caused to tend to flow from root to tip over a straight wing.
accelerated to the separation point.

80. Question

When considering an angle of attack versus coefficient of lift graph for a cambered aerofoil, where does the lift curve intersect the vertical CL axis?

Select one:

At the point of origin.
Below the origin.
To the left of the origin.
Above the origin.

81. Question

When an aircraft pitches up, the angle of attack of the tailplane will:

Select one:

increase
depend solely upon the rigger´ s angle of incidence
remain the same.
decrease

82. Question

When an aircraft is on the ground, with its engine running, positive propeller torque reaction of a right handed propeller will:

Select one:

cause the port undercarriage shock absorber to be further compressed.
have no effect on shock absorber extension.
cause the starboard undercarriage shock absorber to be further compressed.
cause both port and starboard undercarriages to be further compressed.

83. Question

When an aircraft is in a non-accelerated level flight, what are the relationships between lift, weight, thrust and drag?

Select one:

Lift is greater than weight and thrust exceeds drag
Lift is greater than weight and thrust is equal to drag
Lift is equal to weight and thrust exceeds drag
Lift is equal to weight and thrust is equal to drag

84. Question

When an aircraft enters ground effect:

Select one:

the total reaction vector is inclined forwards, increasing drag.
the total reaction vector is inclined forwards, reducing drag.
the total reaction vector is inclined rearwards, increasing drag.
the total reaction vector is unaffected.

85. Question

When an aircraft enters ground effect:

Select one:

the lift vector is inclined forward which increases the thrust required.
the lift vector is inclined rearwards which increases the thrust required.
the lift vector is inclined forwards which reduces the thrust required.
the lift vector is unaffected, the cushion of air increases.

86. Question

When a pilot makes a turn in horizontal flight, the stall speed:

Select one:

increases with the square root of load factor.
increases with the load factor squared.
decreases with increasing bank angle.
increases with flap extension.

87. Question

What will happen in ground effect?

Select one:

The induced angle of attack and induced drag decreases.
A significant increase in thrust required.
An increase in strength of the wing tip vortices.
The wing downwash on the tail surfaces increases.

88. Question

What is the standard stall recovery for a light aircraft?

Select one:

Pitch down, stick neutral, wait for neutral tendency.
Pitch down, stick neutral roll, correct for bank with rudder.
Pitch down, stick neutral roll, do not correct for bank.
Pitch down, stick neutral roll, correct for bank with aileron.

89. Question

What is the SI unit that results from multiplying kg and m/s squared?

Select one:

Newton
Watt
Psi
Joule

90. Question

What is the MAC of a wing?

Select one:

The mean chord of the whole aeroplane.
The same as the mean chord of a rectangular wing of the same span.
The 25% chord of a swept wing.
Area of wing divided by the span.

91. Question

What is the effect on induced drag on entering the ground effect?

Select one:

Induce drag increases, but profile drag decreases.
Induced drag remains the same.
Induced drag decreases.
Induced drag increases.

92. Question

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

Select one:

Induced drag decreases 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 decreasing speed and induced drag decreases With increasing weight.
Induced drag decreases with increasing speed and induced drag decreases with decreasing weight.

93. Question

What is the effect of high aspect ratio of an aeroplanes wing on induced drag?

Select one:

It is reduced because the effect of wing-tip vortices is reduced.
It is unaffected because there is no relation between aspect ratio and induced drag.
It is increased because high aspect ratio has greater frontal area.
It is increased because high aspect ratio produces greater downwash.

94. Question

What is ground effect?

Select one:

The effect of hitting the ground.
The result of an alteration in airflow, increasing induced drag on the wings of an airplane.
The result of disturbing airflow around the wings of an airplane to the point where the wings will no longer support the airplane in flight.
The result of interference of the surface of the Earth with the airflow around the wing and tailplane.

95. Question

What is a high speed stall?

Select one:

Excessive dynamic pressure causing airflow separation.
A stall caused by increasing the load factor (g) during a manoeuvre.
A stall due to exceeding the critical angle of attack at high speed during a manoeuvre.
Separation of the airflow due to shockwave formation.

96. Question

What effect on induced drag does entering ground effect have:

Select one:

Decrease.
Remain the same.
Increase.
Induced drag will increase, but profile drag will decrease.

97. Question

What effect does an increased load have on an aircraft?

Select one:

The aircraft will have a tendency to spin.
The aircraft will suffer immediate structural failure.
The aircraft will stall at a higher speed.
The aircraft will have a tendency to roll and yaw.

98. Question

What changes in angle of attack must be made to maintain altitude while the airspeed is being increased?

Select one:

Increase the angle of attack to produce more lift than drag.
Maintain a constant angle of attack until the desired airspeed is reached, then increase the angle of attack
Decrease the angle of attack to compensate for the increasing lift.
Decrease the angle of attack to compensate for the increasing drag.

99. Question

What are the standard temperature and pressure values for sea level?

Select one:

59° F and 29.92 millibar
59° C and 1013.2 millibar
1013.25 Pa and 13° C
15° C and 29.92 Hg

100. Question

What are the SI units of the following?

Select one:

Density is kilograms per cubic metre, Force is Newton’ s.
Density is Newton’ s per cubic metre, Force is kilograms.
Density is kilograms per square metre, Force is kilograms.
Density is kilograms per Newton, Force is Newton-metre squared.

101. Question

What are the correct SI units for density and force?

Select one:

Kg/m3, Newton
Kg/N, Nm3
Kg/m3, Kg
N/m3, Kg

102. Question

Vortex generators:

Select one:

take kinetic energy out of the boundary layer to reduce separation.
transfer energy from the free airflow into the boundary layer.
change the turbulent boundary layer into a laminar boundary layer.
reduce the span wise flow on swept wing.

103. Question

Vectors:

Select one:

have a direction only
none of the above
have a magnitude only
have a magnitude and a direction

104. Question

Under which condition will pressure altitude be equal to true altitude?

Select one:

When standard atmospheric conditions exist.
When the atmospheric pressure is 29.92 Hg.
When indicated altitude is equal to the pressure altitude.
Never.

105. Question

Under what condition is indicated altitude the same as true altitude?

Select one:

At sea level in standard conditions (ISA)
When at 18,000 feet MSL with the altimeter set at 29.92
If the altimeter has no mechanical error
Never

106. Question

Total Drag is the sum of:

Select one:

wake drag, interference drag and form drag.
induced drag, pressure drag, skin friction drag and interference drag.
profile drag, form drag, induced drag and wake drag.
induced drag, form drag, interference drag and zero lift drag.

107. Question

To maintain level flight, if the angle of attack is increased the speed must be:

Select one:

increased in the same ratio as the lift/drag ratio decreases.
increased.
reduced in the same ratio as the lift/drag ratio increases.
reduced.

108. Question

The wing of an aeroplane will never stall at low subsonic speeds as long as:

Select one:

the CAS exceeds the power-on stall speed.
there is a nose-down attitude.
the IAS exceeds the power-on stall speed.
the angle of attack is smaller than the value at which the stall occurs.

109. Question

The wing area divided by the span of a wing is called:

Select one:

fineness ratio.
aspect ratio.
mean cord.
wash out.

110. Question

The wake vortices behind a large aircraft begin on takeoff … and end on landing…

Select one:

at 80kt; on touchdown.
on rotation; as the nosewheel goes down.
at V1; when lift dump is selected.
at V2; in the flare.

111. Question

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

Select one:

angle of attack.
square of the angle of attack.
square of the speed.
speed.

112. Question

The units of wing loading (I) W / S and (II) dynamic pressure q are:

Select one:

(I) kg / m, (II) N / m2.
(I) N / m2, (II) N / m2.
(I) N / m, (II) kg.
(I) N / m3, (II) kg / m2.

113. Question

The units of the density of the air (I) and the force (II) are:

Select one:

w(I) N / m3, (II) N
w(I) kg / m?, (II) kg
w(I) kg / m3, (II) N
w(I) N / kg, (II) kg

114. Question

The units of a turning moment are?

Select one:

Rad / second
Joule
Kilogram
Newton x meters

115. Question

The unit of density is

Select one:

psi
kg/ml
kg/cm
Bar

116. Question

The total pressure is:

Select one:

1/2 rho V2
can be measured in a small hole in a surface, parallel to the local stream
static pressure minus the dynamic pressure
static pressure plus the dynamic pressure

117. Question

The thickness/chord ratio of a wing is also known as the:

Select one:

aspect ratio.
mean chord ratio.
Fineness ratio.
incidence ratio.

118. Question

The terms q and S in the lift formula are:

Select one:

dynamic pressure and the area of the wing
static pressure and wing surface area
static pressure and dynamic pressure
square root of surface and wing loading

119. Question

The term angle of attack is defined as:

Select one:

the angle that determines the magnitude of the lift force.
the angle between the wing chord line and the relative wind.
the angle between the wing and tailplane incidence.
the angle between the relative airflow and the horizontal axis.

120. Question

The term angle of attack is defined as the angle:

Select one:

formed by the longitudinal axis of the airplane and the chord line of the wing.
between the wing chord line and the relative wind.
between the airplanes climb angle and the horizon.
between the wing chord line and the local horizon.

121. Question

The term angle of attack in a two dimensional flow is defined as:

Select one:

the angle between the wing chord line and the direction of the relative wind/airflow
the angle formed by the longitudinal axis of the aeroplane and the chord line of the wing
the angle for maximum lift/drag ratio
the angle between the aeroplane climb path and the horizon

122. Question

The static pressure is acting:

Select one:

only perpendicular to the direction of the flow
only in direction of the flow
only in the direction of the total pressure
in all directions

123. Question

The standard procedure for recovery from a stall in a light single engine aircraft is:

Select one:

maximum power; stick – roll neutral and forward, correct for bank with rudder.
maximum power; stick – roll neutral and forward, correct for bank with stick.
idle power; stick – roll neutral and forward.
idle power; stick neutral, wait for normal nose down tendency.

124. Question

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

Select one:

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

125. Question

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

Select one:

increase with increased load factor, icing conditions and an aft c.g. location.
decrease in a forward c.g. location, higher altitude and due to the slip stream from a propeller on an engine located forward of the wing.
increase with increased load factor, more flaps but will not increase due to the bank angle in a turn.
increase during turn, increased mass and forward c.g. location.

126. Question

The stall speed

Select one:

decreases with an increased weight.
increases with the length of the wingspan.
increases with an increased weight.
does not depend on weight.

127. Question

The stall speed increases, when? (all other factors of importance being constant)

Select one:

pulling out of a dive.
minor altitude changes occur e.g. 0-10.000 ft.
weight decreases.
spoilers are retracted.

128. Question

The span-wise flow is caused by the difference between the air pressure on top and beneath the wing and its direction of movement goes from:

Select one:

the top to beneath the wing via the wings trailing edge.
beneath to the top of the wing via the wing tip.
beneath to the top of the wing via the trailing edge.
the top to beneath the wing via the leading edge.

129. Question

The stagnation point is:

Select one:

static pressure plus dynamic pressure.
static pressure minus dynamic pressure.
static pressure only.
dynamic pressure only.

130. Question

The stagnation point on an aerofoil in flight is:

Select one:

located at the point of deepest section,
air at rest at the section leading edge,
air at rest between the trailing edge streamlines,
air at rest on the upper surface the wing.

131. Question

The SI unit of force is:

Select one:

Newton
Watt
Kilogram
Joule

132. Question

The sensor of a stall warning system can be activated by a change in the location of the:

Select one:

centre of lift.
stagnation point.
transition region.
centre of gravity.

133. Question

The SI unit of energy is:

Select one:

Ampere
Watt
BTU
Joule

134. Question

The relative thickness of an aerofoil is expressed in:

Select one:

% chord.
degrees cross section tail angle.
camber.
meters.

135. Question

The relationship between induced drag and the aspect ratio is:

Select one:

induced drag = 1.3 aspect ratio value.
a decrease in the aspect ratio increases the induced drag.
an increase in the aspect ratio increases the induced drag.
there is no relationship.

136. Question

The purpose of a fixed spoiler on the leading edge of a wing at the root is to:

Select one:

re-energise the boundary layer thereby delaying the stall (although at a cost of increased from drag).
prevent the wing from stalling at the root.
reduce the landing run.
ensure that the root of the wing stalls before the tip.

137. Question

The purpose of a fixed spoiler on the leading edge of a wing at the root is to:

Select one:

reduce the landing distance required.
ensure that the root of the wing stalls before the tip does.
imparting fresh momentum to the particles in the boundary layer on the top of the wing.
prevent the wing from stalling at the root.

138. Question

The Principle of Continuity states that in a tube of increasing cross-sectional area, the speed of a subsonic and incompressible airflow will:

Select one:

remain the same.
sonic.
increase.
decrease.

139. Question

The Principle of Continuity states that in a Stream tube of decreasing cross-sectional area, the speed of a subsonic and incompressible airflow will:

Select one:

remain the same.
sonic.
increase.
decrease.

140. Question

The point, where the aerodynamic lift acts on a wing is:

Select one:

the suction point of the wing
the centre of pressure
the point of maximum thickness of the wing
the c.g. location

141. Question

The normal stall recovery procedure for a light single engined aeroplane is:

Select one:

idle power and stick roll-neutral nose-down and no other corrections.
full power and stick roll-neutral nose-down, correction for angle of bank with stick.
full power and stick roll-neutral nose-down, correcting for angle of bank with rudder.
idle power and stick neutral, waiting for the natural nose-down tendency.

142. Question

The most common stall sensing devices are normally located:

Select one:

on the upper surface of the wing.
at the transition point.
at or near the wing leading edge.
on the lower surface of the wing.

143. Question

The Mean Chord of a wing is the:

Select one:

wing area divided by the root chord.
wing area divided by the tip chord.
wing area divided by the span.
line equidistant from the upper and lower surfaces.

144. Question

The mean chord is calculated by:

Select one:

dividing the net wing area by the wing span.
dividing the chord by the maximum thickness.
dividing the gross wing area by the root chord.
dividing the gross wing area by the wing span.

145. Question

The Mean Aerodynamic Chord (MAC) for a given wing of any platform is:

Select one:

the chord of a rectangular wing with same moment and lift.
the wing area divided by the wing span.
the average chord of the actual aeroplane.
the chord of a large rectangular wing.

146. Question

The Mean Chord [Geometric] is the:

Select one:

wing area divided by the span.
ratio of root chord to tip chord.
ratio of the wing span to the mean chord.
wing area multiplied by the span.

147. Question

The Lift/Drag ratio [Polar] of a wing section at its stalling angle is:

Select one:

moderate.
of a negative value.
low.
high.

148. Question

The lift formula is:

Select one:

L= n W
L= W
L= CL 2 RHO V2 S
L= CL 1/2 RHO V2 S

149. Question

The lift force, acting on an aerofoil:

Select one:

is mainly caused by overpressure at the underside of the aerofoil
increases, proportional to the angle of attack until 40 degrees
is mainly caused by suction on the upper side of the aerofoil
is maximum at an angle of attack of 2 degrees

150. Question

The interference drag is created as a result of:

Select one:

interaction between aeroplane parts (e.g. wing/fuselage).
the addition of induced and parasite drag.
separation of the induced vortex.
downwash behind the wing.

151. Question

The influence of ground affect on landing distance will be to:

Select one:

increase landing distance.
decrease landing distance.
depend on flap position.
have no affect on landing distance.

152. Question

The induced drag of an aircraft in level flight:

Select one:

decreases with increasing airspeed.
increases with increasing speed.
is not affected by airspeed.
increases as the wing aspect ratio is increased.

153. Question

The induced angle of attack is the result of:

Select one:

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.
downwash due to flow separation.

154. Question

The induced drag:

Select one:

has no relation to the lift coefficient.
increases as the magnitude of the tip vortices decreases.
increases as the aspect ratio increases.
increases as the lift coefficient increases.

155. Question

The higher the aspect ratio of a wing:

Select one:

the greater the induced drag.
the greater the rigidity of the wing.
the lower the stalling angle.
the greater the vortex drag.

156. Question

The four forces of lift, weight, thrust and drag in level flight act through:

Select one:

the Aerodynamic Centre
the Aft Limit
the C of G
the C of P

157. Question

The greatest vortex strength occurs when the generating aircraft is:

Select one:

light, dirty, and fast.
heavy, clean, and slow.
dirty.
heavy, dirty, and fast.

158. Question

The four basic forces acting on an airplane in unaccelerated flight are:

Select one:

pressure forces, centrifugal forces, centripetal forces and inertia forces
lift, weight, thrust and drag
lift, weight, gravity and thrust
lift, gravity, power, and friction

159. Question

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

Select one:

Newton
Pascal
Joule
Watt

160. Question

The following factors increase stall speed:

Select one:

a higher weight, selecting a higher flap setting, a forward c .g. shift.
an increase in load factor, a forward c.g. shift, decrease in thrust.
a lower weight, decreasing bank angle, a smaller flap setting.
increasing bank angle, increasing thrust, slat extension.

161. Question

The fineness ratio of an airfoil is:

Select one:

mean chord / thickness ratio
mean camber chord ratio / thickness ratio
thickness / span ratio
thickness / chord ratio

162. Question

The Fineness Ratio of a wing is the:

Select one:

ratio of the span to the chord.
ratio of the tip chord to the root chord.
thickness/chord ratio.

163. Question

The fineness ratio is:

Select one:

equal to the taper ratio.
equal to the thickness-to-chord ratio.
the inverse of the thickness-to-chord ratio.
the inverse of the taper ratio.

164. Question

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

Select one:

below the origin.
nowhere.
in the origin.
above the origin.

165. Question

The dynamic pressure increases proportionally with:

Select one:

density and the square of the velocity
velocity and density
the static pressure
velocity and the square of the density

166. Question

The chord line is:

Select one:

a straight line from the leading edge of the wing to the trailing edge of the wing.
a line tangential to the wing surface at the leading edge.
a line equidistant between intrados and extrados.
a line perpendicular to the longitudinal axis of the aircraft.

167. Question

The characteristics of a high aspect ratio wing has are:

Select one:

short chord, long span.
long span, long chord.
short chord, short span.
long chord, short span.

168. Question

The centripetal force in a spin is a component of:

Select one:

weight only.
weight and centrifugal force.
lift.
lift and weight.

169. Question

The centre of pressure (c.o.p) is in its most forward position:

Select one:

when the angle of attack is smaller than the stalling angle of attack.
the centre of pressure on an airfoil has no most forward position.
when the angle of attack is exceeds the stalling angle of attack.
when the angle of attack is equal to the stalling angle of attack.

170. Question

The Aspect Ratio of a wing is the ratio of:

Select one:

wing span to mean chord.
wing span to root chord.
wing span squared to mean chord.
wing span to wing area.

171. Question

The angle of attack of a wing profile is defined as the angle between:

Select one:

the local airflow and the chord line.
the undisturbed airflow and the mean camber line.
the local airflow and the mean camber line.
the undisturbed airflow and the chord line.

172. Question

The angle of attack of an aerofoil section is the angle between the:

Select one:

chord line and the mean chord line.
chord line and the relative airflow.
underside of the surface and the relative airflow.
mean camberline and the relative airflow.

173. Question

The angle of attack of a two dimensional wing section is the angle between:

Select one:

the fuselage core line and the free stream direction.
the chord line of the aerofoil and the fuselage centreline.
the chord line and the camber line of the aerofoil.
the chord line of the aerofoil and the free stream direction.

174. Question

The angle of attack is the angle between:

Select one:

the chord line and the direction of the airflow.
wing and lateral axis.
chord line and the longitudinal axis.
the direction of the airflow and the longitudinal axis.

175. Question

The angle of attack at which an aircraft stalls:

Select one:

varies with gross weight and density altitude.
increases with an increase in engine power.
decreases with an increase in engine power.
remains constant regardless of gross weight.

176. Question

The angle of attack at which a wing stalls will:

Select one:

change with an increase in gross weight.
increase if the centre of gravity is moved aft.
increase if the centre of gravity is moved forward.
remain the same regardless of gross weight.

177. Question

The angle of attack (aerodynamic angle of incidence) of an aerofoil is the angle between the:

Select one:

bottom surface and the relative airflow.
chord line and the relative undisturbed airflow.
bottom surface and the Horizontal.
bottom surface and the chord line.

178. Question

The angle between the lateral axis and the chord line is known as:

Select one:

the dihedral angle.
the sweep angle.
the incidence angle.
the chord angle.

179. Question

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

Select one:

angle of attack.
same as the angle between chord line and fuselage axis.
glide path angle.
climb path angle.

180. Question

The angle between the aeroplane longitudinal axis and the chord line is the:

Select one:

angle of incidence.
angle of attack.
climb path angle.
glide path angle.

181. Question

The airfoil chord line is:

Select one:

a straight line from the wing leading edge to the trailing edge.
a line drawn at 15% chord from the root to the tip.
a line tangential to the wing surface at the point of maximum curvature.
a line equidistant from the upper and lower wing surfaces.

182. Question

The airflow over the upper surface of the wing of an aircraft in level flight compared to the free stream air will:

Select one:

experience an increase in velocity and a reduction in static pressure
have the same velocity, resulting in reduced pressure
experience a reduction in velocity producing increased pressure
have greater velocity, resulting in increased static pressure

183. Question

The airflow over the upper surface of a cambered wing:

Select one:

increases in velocity and pressure.
increases in velocity and reduces in pressure.
reduces in velocity and pressure.
reduces in velocity and increases in pressure.

184. Question

The aeroplane drag in straight and level flight is lowest when the:

Select one:

parasite drag is equal to the induced drag.
induced drag is equal to zero.
induced drag is lowest.
parasite drag equals twice the induced drag.

185. Question

The (subsonic) static pressure:

Select one:

is the pressure in a point at which the velocity has become zero.
decreases in a flow in a tube when the diameter decreases.
increases in a flow in a tube when the diameter decreases.
is the total pressure plus the dynamic pressure.

186. Question

That portion of the aircrafts total drag created by the production of lift is called?

Select one:

Parasite drag, and is greatly affected by changes in airspeed.
Induced drag, and is greatly affected by changes in airspeed.
Profile drag, and is not affected by changes in airspeed.
Induced drag, and is not affected by changes in airspeed.

187. Question

Subsonic flow over a cambered airfoil at 4° angle of attack will cause:

Select one:

an increase in speed and drop in static pressure over the upper surface and a decrease in speed and a rise in static pressure over the lower surface.
a decrease in speed and drop in static pressure over the upper surface and a decrease in speed and a drop in static pressure over the lower surface.
an increase in speed and drop in static pressure over the upper surface and an increase in speed and a drop in static pressure over the lower surface.
a decrease in speed and drop in static pressure over the upper surface and an increase in speed and a drop in static pressure over the lower surface.

188. Question

On entering ground effect, maintaining flight at the same speed:

Select one:

more power is required.
ground effect has no effect on power.
less power is required.
lift decreases.

189. Question

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):

Select one:

move aft
remain unaffected
move forward
remain matching the airfoil aerodynamic centre

190. Question

Static pressure acts:

Select one:

parallel to dynamic pressure
parallel to airflow
in all directions
downwards

191. Question

Profile drag in straight and level flight:

Select one:

is proportional to the square of the speed.
depends mainly on the gross weight of the aircraft.
is inversely proportional to the square of the speed.
is the sum of induced drag and skin friction drag.

192. Question

On the approach to land, ground effect will begin to be felt at:

Select one:

when the angle of attack is increased.
upon elevator deflection.
twice the wingspan above the ground.
half the wingspan above the ground.

193. Question

On an airfoil the centre of pressure will be most forward:

Select one:

at the optimum angle.
just below the stalling angle.
at the stalling angle.
just above the stalling angle.

194. Question

On a symmetrical aerofoil, the pitch moment for which Cl=0 is:

Select one:

equal to the moment coefficient for stabilized angle of attack.
zero.
positive (pitch-up).
negative (pitch-down).

195. Question

On a cambered airfoil the zero lift angle of attack will be:

Select one:

positive
negative
zero
dependent on the wing aspect ratio

196. Question

Mean chord is equal to:

Select one:

wing span divided by wing area
(tip chord + root chord) / 2
mean aerodynamic chord
wing area divided by wing span

197. Question

Minimum total drag of an aircraft occurs:

Select one:

at the best rate of climb speed.
when profile drag equals induced drag.
at the stalling speed.
when induced drag is minimum.

198. Question

Lift is the component of the total aerodynamic force which is:

Select one:

parallel to the longitudinal axis of the aircraft.
perpendicular to the free stream airflow.
parallel to the free stream airflow.
perpendicular to the longitudinal axis of the aircraft.

199. Question

Lift is generated when:

Select one:

a certain mass of air is accelerated downwards
the shape of the aerofoil is slightly cambered
a certain mass of air is retarded
an aerofoil is placed in a high velocity air stream

200. Question

Lift is created over a wing because:

Select one:

airflow speed increases over the wing surface causing a increase in dynamic pressure
airflow slows down on the extrados causing a reduction in static pressure
airflow slows down over a wing causing an increase in static pressure
airflow accelerates of the top surface of the airfoil creating a reduction in static pressure

201. Question

Lift is a function of:

Select one:

velocity, wing shape, wing area and CL.
velocity, density, wing shape and lift coefficient.
velocity, density, gross wing area and CD.
velocity, wing area, CL and density.

202. Question

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

Select one:

relative wind/airflow.
chord line.
longitudinal axis.
horizon.

203. Question

Interference drag can be reduced using:

Select one:

wing fences.
winglets.
fairings.
fairings, winglets and wing fences.

204. Question

Induced drag:

Select one:

is proportional to the square of the speed.
always exceeds profile drag.
increases when reducing the wing aspect ratio.
increases when increasing the wing aspect ratio.

205. Question

Induced drag:

Select one:

increases with increase in speed.
increases with increase in aircraft weight.
reduces with an increase in angle of attack.
reduces with altitude at constant I.A.S.

206. Question

Induced drag:

Select one:

increases as the square of the speed.
varies inversely as the square of the speed.
reduces with increased angle of attack.
remains constant for a given speed regardless of angle of attack.

207. Question

Induced drag on a wing in level flight:

Select one:

is uniform across its span.
is greatest at the tip.
is greatest at the wing root.
is greatest at the leading edge.

208. Question

Induced drag may be reduced by:

Select one:

a decrease of the aspect ratio.
an increase in aspect ratio.
an decrease in the taper ratio of the wing.
the use of a wing tip with a much thinner aerofoil.

209. Question

Induced drag is:

Select one:

proportional to aspect ratio.
inversely proportional to aspect ratio.
inversely proportional to lift.
proportional to speed.

210. Question

Induced drag is:

Select one:

greatest towards the wing root and downwash is greatest at the tip.
greatest towards the wing tip and downwash is greatest toward the root.
balanced from root to tip.
greatest toward the tip and downwash decreases from tip to root.

211. Question

Induced drag is created by the:

Select one:

propeller wash blowing across the wing.
separation of the boundary layer over the wing.
interference of the air stream between wing and fuselage.
span wise flow pattern resulting in the tip vortices.

212. Question

Induced drag is caused by:

Select one:

wing tip vortices and downwash.
winglets and washout.
wing mounted fuel tanks.
increased pressure at the leading edge stagnation point.

213. Question

Induced drag is also known as:

Select one:

interference drag.
skin friction drag.
vortex drag.
form drag.

214. Question

Induced drag in straight and level flight is:

Select one:

constant.
inversely proportional to the square of speed (TAS).
always equal to profile drag.
proportional to the square of the speed (TAS).

215. Question

Induced drag at constant IAS is affected by:

Select one:

engine thrust.
aeroplane weight.
aeroplane wing location.
angle between wing chord and fuselage centre line.

216. Question

Induced drag can be reduced by:

Select one:

increased aspect ratio.
use of a wing tip with a thinner aerofoil section.
decreased taper ratio.
not changing taper ratio.

217. Question

Increasing the aspect ratio of a wing…

Select one:

decreases induced drag.
has no effect on induced drag.
decreases skin friction drag.
increases induced drag.

218. Question

Increasing the angle of attack in flight will cause the:

Select one:

boundary layer to become thinner
stagnation point to move down and aft
separation point to move aft
laminar flow to increase

219. Question

Increase of wing loading will:

Select one:

decrease the minimum gliding angle.
increase the stall speeds.
increase CLmax.
decrease take off speeds.

220. Question

In straight and level flight, which of the following would cause induced drag to vary linearly if weight is constant:

Select one:

V2
1/V
V
1/V2

221. Question

In straight and level flight, if airspeed … the angle of attack … and the incidence angle…

Select one:

decreases; increases; remains constant.
decreases; decreases; decreases.
increases; increases; decreases.
increases; decreases; decreases.

222. Question

In level flight, the four forces of Lift, Weight, Thrust and Drag are said to act through:

Select one:

the C of P.
the Aerodynamic Centre [Centre of Pressure].
the Aft Limit.
the C of G.

223. Question

In level flight an increase in angle of attack will cause:

Select one:

the centre of pressure to move aft.
a decrease in pitch angle.
the boundary layer to become thinner.
the stagnation point to move down and aft.

224. Question

In flight the C of P by increasing angle of attack, will reach its most forward point on an airfoil:

Select one:

just below the stalling angle.
at the optimum angle of attack.
at the stall.
at the stalling angle.

225. Question

In accordance with Bernoulli’ s Theorem, where PT = Total Pressure, PS = Static pressure and q = Dynamic pressure:

Select one:

PS + PT = q
PT = PS – q
PT – PS = q
PT + PS = q

226. Question

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

Select one:

increase.
increase initially, then decrease.
decrease.
not change.

227. Question

In a symmetrical airfoil the mean camber line is?

Select one:

A line joining points of mean camber along the wing.
A curve co-incident with the top surface of the airfoil.
A straight line co-incident with the chord line.
A line joining points of maximum camber along the wing.

228. Question

In a stationary subsonic streamline flow pattern, if the streamlines converge, in this part of the pattern, the static pressure will (I) and the velocity will (II):

Select one:

(I) increase; (II) decrease
(I) decrease; (II) increase
(I) decrease; (II) decrease
(I) increase; (II) increase

229. Question

In a spin:

Select one:

both wings are fully stalled.
the outer wings is stalled and the inner wing partially stalled.
both wings are partially stalled.
both inner wing is fully stalled and the outer wing partially stalled.

230. Question

In a spin:

Select one:

the angle of attack is the same on both wings.
the angle of attack is greater on the inner wing.
the angle of attack is greater on the outer wing.
both inner and outer wings are fully stalled.

231. Question

If the continuity equation is applicable, what will happen to the air density (rho) if the cross sectional area of a tube changes? (low speed, subsonic and incompressible flow:

Select one:

rho1
rho1 rho2
The density depends on the change of the tube area.
rho1 = rho2

232. Question

If you are flying at 100 kts and you increase your airspeed to 200 kts, profile drag:

Select one:

quadruples.
increases with 100%.
remains the same.
decreases with 200%.

233. Question

If the aspect ratio of a wing (for a given wing area) is decreased:

Select one:

lift coefficient increases for a given angle of attack.
lift coefficient remains unaffected at a given angle of attack.
induced drag, for a given angle of attack, increases.
induced drag decreases for a given angle of attack.

234. Question

If the angle of attack of a wing is increased in flight the:

Select one:

C of P will move forward.
C of G will move aft.
C of P will remain in the same place.
C of P will move aft.

235. Question

If the angle of attack is increased, the centre of pressure will:

Select one:

move forward towards the aerodynamic centre of the wing
move forward or aft, depending on the location of the centre of gravity
will remain stationary
move aft

236. Question

If temperature in a gas is kept constant and pressure increases, the density:

Select one:

increases
remains constant
decreases
None of the above – it depends on the type of gas

237. Question

If pressure is kept constant and temperature increases, the density:

Select one:

decreases
remains constant
temperature have no effect
increases

238. Question

If pressure increases, with OAT and TAS constant, what happens to drag?

Select one:

Remain constant.
Drag is dependant only on dynamic pressure.
Decrease.
Increase.

239. Question

If IAS is doubled, by which of the following factors should the original CL be multiplied to maintain level flight?

Select one:

4.0
0.5
2.0d
0.25

240. Question

If dynamic (kinetic) pressure increases, what is the effect on total drag (if all important factors remain constant)?

Select one:

Drag increases.
Drag only changes with changing ground speed.
It has no effect on drag.
Drag decreases.

241. Question

If density is kept constant, the dynamic pressure increases proportionally with:

Select one:

the static pressure.
velocity.
the square of the velocity.
inversely with the square of the velocity.

242. Question

If an aircraft is pitching up:

Select one:

the incidence angle first increases and than decreases.
the incidence angle remains fixed.
the incidence angle decreases.
the incidence angle increases.

243. Question

If an aeroplane flies in the ground effect:

Select one:

drag and lift are reduced.
the induced angle of attack is increased.
the effective angle of attack is decreased.
the lift is increased and the drag is decreased.

244. Question

How will frost on the wings of an airplane affect takeoff performance?

Select one:

Frost will disrupt the smooth flow of air over the wing, adversely affecting its lifting capability.
Frost will cause the airplane to become airborne with a higher angle of attack, decreasing the stall speed.
Frost will change the camber of the wing, increasing its lifting capability.
Frost has no influence on airplane performance.

245. Question

If a pilot changes the altimeter setting from 30.11 Hg to 29.96 Hg, what will be the approximate change in indication?

Select one:

Altimeter will indicate .15 Hg higher
Depends on the outside temperature
Altimeter will indicate 150 feet lower
Altimeter will indicate 150 feet higher

246. Question

How is the thickness of an aerofoil section measured?

Select one:

Related to camber
As the percentage of chord
In metres
As the ratio of wing angle

247. Question

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?

Select one:

Decreasing, then increasing.
Increasing, then decreasing.
Decreasing.
Increasing.

248. Question

How does aerodynamic drag vary when airspeed is doubled? By a factor of:

Select one:

16
1
2
4

249. Question

How do vortex generators work?

Select one:

Take energy from free stream and introduce it into the boundary layer.
Reduce kinetic energy to delay separation.
Re-direct slantwise flow.
Reduce the adverse pressure gradient.

250. Question

A gust front is

Select one:

normally encountered directly below a thunderstorm
formed by the cold air outflow from a thunderstorm
characterized by heavy lightning
another name for a cold front

251. Question

High aspect ratio:

Select one:

reduces parasite drag.
reduces manoeuvrability.
increases stalling speed.
reduces induced drag.

252. Question

Ground Effect:

Select one:

is only effective up to 1 wingspan from the ground.
has the same effect as a decrease in aspect ratio.
is usually only considered when the approach phase has commenced.
increases induced drag.

253. Question

Ground Effect occurs:

Select one:

is only effective up to 1 wingspan from the ground.
acts like a decrease in aspect ratio.
aids landing by increasing the induced drag.
during the approach to landing.

254. Question

Ground effect is most likely to result in which problem?

Select one:

Inability to get airborne even though airspeed is sufficient for normal takeoff needs.
Deep stall.
Becoming airborne before reaching recommended takeoff speed.
Hard landings.

255. Question

Ground effect has the following influence on the landing distance:

Select one:

decreases.
increases.
increases, only if the landing flaps are fully extended.
does not change.

256. Question

Geometric washout means that:

Select one:

the horizontal tail has less angle of attack than the wing.
the tip of the wing has less angle of attack than the root.
there is an airflow along the wing that keeps it clean.
the tip of the wing has more angle of attack than the root.

257. Question

Generally speaking, the transition point for an aerofoil section is the:

Select one:

point of maximum section depth.
separation point.
point of greatest pressure.
leading edge.

258. Question

For the same angle of attack a cambered wing will produce:

Select one:

less lift than one with no camber.
more lift than one with no camber.
the same lift regardless of camber.
less lift and drag than one with no camber.

259. Question

For an aircraft in straight and level flight, which forces are in equilibrium?

Select one:

Tensile, shear, twisting and stretching forces.
Thrust, drag, lift and weight.
Compressive, bending, shear and torsional forces.
Compressive, tensile, shear and torsional loads.

260. Question

For a given angle of attack induced drag is:

Select one:

greater on a high aspect ratio wing.
greater towards the wing root.
greater on a low aspect ratio wing.
balanced across the span of the wing.

261. Question

For a constant aircraft weight at constant IAS and in level flight:

Select one:

VIMD will increase with increased altitude.