MODEL QUESTIONS

1.The flow of air around an object caused by the movement of either the air or the object ,or both is called :

a) Average wind b) Relative wind c) incoming wind d)outgoing wind

Ans: b) Relative wind

Ref: Airframe & Power plant MECHNICS AC 65-15A Page No 29 Para : Motion
2. The density of gases is governed by the following rules :
a) Density varies in direct proportion with the pressure

b) Density varies inversely proportion with the pressure

c) As in (a) Density varies inversely proportion with the temperature

d) As in (b) Density varies in direct proportion with the temperature

Ans: c) As in (a) Density varies inversely proportion with the temperature
Ref : Airframe & Power plant MECHNICS AC 65-15A Page No 28 Para : Density

3.The air at any altitude results from the mass of air supported above that level is:
a) Dynamic Pressure b) Critical Pressure c)Static Pressure d) Absolute Pressure
Ans : c)Static Pressure

Ref: Aircraft basic science by Krose and Rardon 7th edition page No 56 Para Atmosphere
4.An adiabatic temperature change means that :

a) The temperature of the air has changed ,but the air has not gained heat energy.
b) The temperature of the air has changed ,but the air has not lost heat energy.
c) The temperature changes is due to a change in pressure

d) All are correct.

Ans: d) All are correct.

Ref: Aircraft basic science by Krose and Rardon 7th edition page No 59 Para Adiabatic lapse rate.
5.The temperature of the air is affected by:
a) Mountains and clouds b) As in (a) Surface winds

c) As in (b) Bodies of water d) As in (c) sunshine

Ans: d) As in (c) sunshine

Ref: Aircraft basic science by Krose and Rardon 7th edition page No 59 Para
6.Adiabatic lapse rate.
An important factor affecting the atmosphere is

a) Density b) Humidity c)Moisture d)Temperature

Ans: d)Temperature

Ref : Mechanics of Flight by AC Kermode Page No 31 Para : Temerature

7. The effect of wind gradient takes place with in
a) 10-20 feet from the ground b ) 15 to 25 feet from the ground
c) 10-15 feet from the ground d) 0 to 10 feet from the ground

Ans : c) 10-15 feet from the ground

8. It is the sudden tearing or shearing effect encountered along the edges of a zone which there is violent
change in wind speed or direction.

a) wind shear b)wind gradient c) wind disturbance d)None

Ans : a) wind shear
9.Severe wind shear can impose penalties on the airplane performance during

a) landing and take off b) level flight c)on ground d) None

Ans : a) landing and take off

10 Air pressure :-
a) Acts in all directions b) Acts only vertically downwards
c) Is measured Pascal per square inch d) Increases with altitude

Ans: a) Acts in all directions

11 Relative airflow is _____ and ______ the movement of the aircraft
a) Parallel to/in the same direction as b) Perpendicular to /Opposite to

c) Perpendicular to/in the same direction as d) parallel to/ Opposite to

Ans : d) parallel to/ Opposite to

12 Dynamic pressure equals :

a) Total pressure minus static pressure b)Total pressure plus static pressure
c) Static pressure multiplied by total pressure d) Total pressure divided by static pressure

Ans : a) Total pressure minus static pressure

Ref : Mechanics of Flight by AC Kermode Page No 41 Para : Air speed measurement

13. The condition of moisture or dampness in the air is called :

a) Condenstion b) Saturation c) Humidity d) None
Ans: c) Humidity

Ref: Aircraft basic science by Krose and Rardon 7th edition page No 59 Para
Humidity.

14 In order for an aircraft to fly, a force must be created that will overcome the force of gravity is called :
a) Thrust b) Drag c) Lift d) pressure
Ans : c) Lift

Ref: Aircraft basic science by Krose and Rardon 7th edition page No 60 Para Lift
15 A relative wind flows opposite the direction of the objects in motion. The velocity of its flow around or over
the object in motion is the object’s:

a) Wind speed b) Relative speed c) Speed d) Air speed

Ans : d) Air speed
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Ref: Aircraft basic science by Krose and Rardon 7th edition page No 63 Para
Airfoil in motion

16 In troposphere ,the air is :

a) rarely completely dry b) As in (a) contains water vapour and fog

c) completely wet d). As in (c) is the bottom most layer

Ans : b) As in (a) contains water vapour and fog
Ref : Mechanics of Flight by AC Kermode Page No 31 Para :

17. The Stratosphere starts just above the troposphere and extends to about : -a) 11 kms above earth b) 51
kms above earth ) 500 kms above earth 4. None
Ans: b) 51 kms above earth

Ref : Mechanics of Flight by AC Kermode Page No 32 Para : Temp changes

18.The International Standard Atmosphere (ISA) defines precise values of:
a) Sea level values of Temperature, Pressure and Density.

b) As in(a) Lapse rate and height of the tropopause.

c) As in (a) To use standard set of conditions for aircraft performance calculations.
d) All are correct.

Ans : (d) All are correct

Ref : Mechanics of Flight by AC Kermode Page No 31 Para: Temp changes in the Atmosphere

19 The speed of sound is a function of: -a). Pressure b) Density c) Temperature d). All of them are correct
Ans : c) Temperature
Ref: Aircraft basic science byKrose and Rardon 7th edition page No 52 Para :Sound

20. The speed of sound in the stratosphere is :

a) 340 m/s b) 210 m/s c) 280 m/s d) 295 m/s

Ans : d) 295 m/s

Ref : Aerodynamics by C J Clancy page No 7 Para 1.2
21. The speed of sound in the sea level in standard atmosphere is :

a) 340 m/s b) 210 m/s c) 280 m/s d) 295 m/s

Ans a) 340 m/s

Ref : Aerodynamics by C J Clancy page No 7 Para 1.2

22. The most obvious effects of flow separation are :
a) The breakdown of streamline flow.

b) A sudden reduction of lift (If any) of the body.

c) A violent unsteadiness in the flow ,resulting in buffeting of the body

d) All are correct.

Ans : d) All are correct.
Ref : Aerodynamics by C J Clancy page No 49 Para 4.44 Flow separation
23. It is the limiting altitude at which further climb is not possible: -a) service ceiling b). Absolute ceiling. c).
critical ceiling d). Max ceiling

Ans: b). Absolute ceiling

Ref : Aerodynamics by CJ Clancy page No 439 para 15.10 Ceiling

24. At stagnation point Cp has its maximum value of:

a) >1 b) <1 c) 1 d) 0
Ans : c) 1

Ref : Aerodynamics by C J Clancy page No 59 Para 5.5 Pressure distribution

25 Where there is a reasonably large value of the lift, it is contributed mainly by the ;

a) Lower surface pressure of the airfoil

b) Upper surface suction of the airfoil
c) Equal Pressure on both the surface of the airfoil.

d) None of the above

Ans : b) Upper surface suction of the airfoil
Ref : Aerodynamics by C J Clancy page No 62 Para 5.6 Variation of pressure distribution

26. A fairly sharp nose (i.e ,with small radius of curvature)) may cause :
a) Delayed flow separation b) Early flow separation c) Both are correct.

Ans : b) Early flow separation

Ref : Aerodynamics by C J Clancy page No 65 Para 5.8 Maximum Cl
27. Winglets are used in some aircraft. The purpose is to: -a) Increase lift b) Increase drag c) Prevent wing tip
vortices d) and 3 are correct

Ans : c) Prevent wing tip vortices

28. In aviation ,temperature can be expressed using a number of different scales are:

a) Fahrenheit and Celsius b) As in (a) Rankine c) as in (b) Kelvin d) All are correct
Ans: d) All are correct
Ref: Aircraft basic science by Krose and Rardon 7th edition page No 45 Para Heat

29 The speed of sound in air at 0°C is:

a) 300 m/s b) 295 m/s c) 315m/s d) 331.5m/s

Ans : d) 331.5m/s
Ref: Aircraft basic science byKrose and Rardon 7th edition page No 54 Para Sound
30.As the temperature increases ,the speed of sound :

a) Decreases b) Increases c) No change

Ans : b) Increases

Ref: Aircraft basic science by Krose and Rardon 7th edition page No 54 Para Sound
31 The velocity of sound through a substance depends upon :
 y g p p
a) Density b) Intensity c) Elasticity of the substance d) Both (a) and (c)
Ans: d) Both (a) and (c)

Ref: Aircraft basic science by Krose and Rardon 7th edition page No 54 Para Sound
32. Sound is transmitted better at :

a) Low altitude b) High altitude c) both (a) and (b) correct

Ans: a) Low altitude
Ref: Aircraft basic science by Krose and Rardon 7th edition page No 54 Para Sound

33. The range of altitudes within which the temperature falls steadily is called the:
a) Stratosphere b) Mesosphere c) Troposphere d) Thermosphere

Ans : c) Troposphere
Ref : Aerodynamics by C J Clancy page No 2 Para 1.2 The ISA
34. The point at which the temperature ceases to fall is called the :

a) Stratopause b) Mesospause c) Thermopause d) Tropopause

Ans : d) Tropopause
Ref : Aerodynamics by C J Clancy page No 2 Para 1.2 The ISA

35. A Gas can be compressed ,and it is compressed its :

a) Pressure increases as its volume decreases ,with temperature remains constant

b) Pressure decreases as its volume increases ,with temperature remains constant

c) Both Pressure and volume decreases ,with temperature remains constant
d) Both Pressure and volume increases ,with temperature remains constant

Ans : a) Pressure increases as its volume decreases ,with temperature remains constant
Ref: Aircraft basic science byKrose and Rardon 7th editionpage No51 Para Nature and Laws of Gases

36. Sound intensity levels are measured by a unit is called :

a) Hertz b) Decibal c) Feet/second d) None
Ans: b) Decibal

Ref: Aircraft basic science byKrose and Rardon page 7th edition No54 Measurement of sound
37. On a hot day the air becomes:

a) Air expands and becomes more dense b)Air expands and becomes thinner
c) Air contracts and becomes more dense d) Nochange,
Ans: (b)Air expands and becomes thinner

Ref: Aircraft basic science by Krose and Rardon 7th edition page No59 Para Density
38. With the same thrust, an aeroplane :

a) Can fly slower at high altitudes where density low

b) Can fly faster at high altitudes where density low
c) Can fly faster at low altitude where density low
 y y
d) None
Ans: b) Can fly faster at high altitudes where density low

Ref : Aircraft basic science by Krose and Rardon page No 647th edition Para Density and Lift
39. Laminar flow is most likely to occur where the surface is :

a) Extremely smooth b) As in (a) Especially near the leading edge of an airfoil

c) Laminar flow diminishes when the boundary layer thickens.d) All are correct.
Ans : d) All are correct

? Ref : Aircraft basic science by Krose and Rardon 7th edition page No 65 Boundary Layer
?

? 40. Mark the correct statement :

? a) At low reynolds number ,The flow is laminar
? b) At High Reynolds number ,the flow is Laminar,

? c) As in (a) Low Re number result from small chord surfaces, low velocities and high altitudes.
? d) As in (c) At High Reynolds number ,the flow is Turbulent
? Ans : d) As in (c) At High Reynolds number ,the flow is Turbulent

? Ref : Aircraft basic science by Krose and Rardon 7th edition page No 65 Reynolds number
I41. It is the increase or decrease in the temperature of the air for a given change in altitude is :-

a) Steady rate b) lapse rate c) Adiabatic lapse rate d) None

Ans : c) Adiabatic lapse rate
Ref :Aircraft basic science by Kros & Rardon 7th edition page No 59

42. At a stagnation point the total pressure is equal to :

a) The static pressure b) The dynamic pressure zero

c) Both (a) and (b) are correct c) None

Ans: c) Both (a) and (b) are correct
Ref : Aerodynamics by C J Clancy page No 21 Para 3.5

43. The free stream velocity, which is equal to the forward speed of the aircraft ,depends on the :
a) Free stream dynamic pressure b) Static pressure

c) Air density d) Both (a) and (c) are correct

Ans : d) Both (a) and (c) are correct
Ref : Aerodynamics by C J Clancy page No 23 Para 3.8

44. The boundary layer is caused by the :

a) Density of the air sticking to the surface of the wing and the succeeding layers b) Viscosity of the air
sticking to the surface of the wing and the succeeding layers

c) Due to Pressure
d) None
Ans : b) Viscosity of the air sticking to the surface of the wing and the succeeding layers
Ref : Aircraft basic science by Krose and Rardon page No 65 ,7th edition Para Boundary Layer

45.The wing ,which is the one having the section of chord lines are not at all parallel is called as :
a) Tapered wing b) cambered wing c) twisted wing d) None

Ans : c) twisted wing

Ref : Aerodynamics by C J Clancy page No 73 Para 5.13
46. When the Lift vector is tilted rearward due to downwash ,

a) The lift is lost b) As in (a) The loss of lift is due to Induced drag
c) The lift is increased d) None

Ans b) As in (a) The loss of lift is due to Induced drag

Ref :Aircraft basic science by Kros & Rardon 7th edition page No 66 Induced drag
47. The induced drag:

a) Decreses with velocity b) Increses with the velocity

c) As In (a) The higher angle of attack the grater the Induced drag
d) As In (a) The higher angle of attack the Induced drag is less

Ans : As In (a) The higher angle of attack the grater the Induced drag
Ref: Aircraft basic science by Kros & Rardon 7th edition page No 66 Induced drag

48. Any wing which is not producing any lift or zero at lift will have :
a) Induced Drag b) Wing drag c) No induced drag d) Interference drag
Ans : c) No induced drag

Ref : Aerodynamics by C J Clancy page No 82 Para 5.17

49. The minimum speed is given by the maximum lift coefficient is termed as :

a) Critical speed b) Minimum speed c) maximum speed d) stalling speed

Ans: d) stalling speed
Ref : Aerodynamics by C J Clancy page No 89 Para 5.21

50 . The wing loading of an aircraft is defined as the weight per unit area, rather than simply weight, that
determines the :
a) stalling speed b) Lift c) stalling angle d) None

Ans : a) stalling speed

Ref : Aerodynamics by C J Clancy page No 90 Para 5.22
51 . The speed corrected for instrument and position error is called :

a) True Air Speed b) Indicated Airspeed c) Calibrated Air Speed d) Equivalent Air Speed
Ans : c) Calibrated Air Speed

Ref : Mechanics of Flight by AC Kermode Page No 43 Para : Air speed Indicator corrections
52. After all the corrections have been applied , the resulting speed is called the:
a) True Air Speed b) Indicated Airspeed
c) Calibrated Air Speed d) Equivalent Air Speed

Ans : d) Equivalent Air Speed

Ref : Mechanics of Flight by AC Kermode Page No 43 Para : Air speed Indicator corrections

53. It is the Instrument which indicates the speed relative to the local speed of sound :
a) Altimeter b) Tachometer c) Ammeter d) Machmeter
Ans : d) Machmeter

Ref : Mechanics of Flight by AC Kermode Page No 44 Para : Air speed Indicator corrections
54. A body so shaped as to produce the least possible resistance is said to be of :

a) Parabolic shape b) Elliptical shape c) Streamline shape d) None

Ref : c) Streamline shape
Ref : Mechanics of Flight by AC Kermode Page No 46 Para : Stream lines

55. When the flight speed exceeds the speed of sound (M=1.05) the bow wave forms at:
a) Trailing edge b) Middle part of the wing c)Leading edge d) None
Ans : c)Leading edge

Ref: : Aircraft basic science by Kros & Rardon 7th edition page No 71 Tronsonic flight
56. In supersonic flow these types of waves are formed :

a) The oblique shock wave b) The normal shock wave

c) The expansion wave d) All are correct
Ans : d) All are correct

Ref: Aircraft basic science by Kros & Rardon 7th edition page No 72
Tronsonic flight

57. When the angle of attack increases to the angle of maximum lift , the burble point is reached is known as
the :
a) Angle of Incidence b) Positive Angle c) Critical angle d) Negative Angle
Ans : (c) Critical Angle

Ref : Airframe & Power plant MECHNICS AC 65-15A Page No 31

58. The point on the airfoil where the airflow divides is called the

a) Mid point b) Center Point c) Transition point d) Stagnation point

Ans : d) Stagnation point
Ref : Aircraft basic science by Kros & Rardon 7th edition page No 63

59. As the speed increases the transition point tends to move further :
a) Backward b) Forward c) Remain at same place

Ans : ( b) Forward
Ref : Mechanics of Flight by AC Kermode Page No 53 Para : Air speed Indicator corrections
60. The center of pressure is generally located at approximately in this chord position for most airfoils :
a) 40% of the chord b) 35% of the chord c) 25% of the chord d)50 % of the chord

Ans : c) 25% of the chord

Ref : Aircraft basic science by Kros & Rardon 7th edition page No 67

61. This flow describes the situation when air is flowing in thin sheets ,or layers ,close to the surface of a wing
with no disturbance between layers of air:
a) Laminar flow b) Turbulent flow c) Rotational flow d)Unsteady flow
Ans: a) Laminar flow

Ref : Aircraft basic science by Kros & Rardon 7th edition page No 65
62. Mark the correct statement:

a) The CP moves forward when angle of attack of increases

b) As in (a) moves backward when AOA decreases
c) The CP always moves forward

d) The CP is always in the same position

Ans : b) As in (a) moves backward when AOA decreases
Ref : Airframe & Power plant MECHNICS AC 65-15A Page No 31 Para :AOA

63. A swept back wing has :

a) High aspect ratio b) Lateral control may be poor, especially at high speeds

c) As in (b) Low aspect ratio d) As in (c) Aeroelastic effects in manoeuvers

Ans : d) As in (c) Aeroelastic effects in manoeuvers
Ref : Aerodynamics by C J Clancy page No 295 Para 11.19

64. The efficiency of wing is measured in terms of the ;

a) Lift over Drag (L/D) ratio

b) Drag over Lift (D/L) ratio

c) Lift over Weight (L/W) ratio
d) None

Ans: a) Lift over Drag (L/D) ratio

Ref : Airframe & Power plant MECHNICS AC 65-15A Page No 32 Para : Wing Area

65. The angle of attack which gives the best L/D ratio
a) Decreases with decrease in density. b) In unaffected by density changes
c) increase with a decrease in density d) None

Ans : b) In unaffected by density changes

Ref : Airframe & Power plant MECHNICS AC 65-15A Page No 32 Para : Wing Area

66. An ideal aerofoil is one which possesses: -a) A high maximum lift coefficient b) A good L / D ratio c). A
small movement of centre of pressure d) All are correct
Ans : d) All are correct
67. Lift equation is: -a). L = Cl 1/2 ρV² b). L = Cl 1/2 ρV² S c). L = W d). L = D
Ans: b). L = Cl 1/2 ρV² S

68. This ratio is a measure of the effectiveness of an airfoil :

a) Lift/Drag b). Drag/Lift c) Lift/weight d.Thrust/weight

Ans: a) Lift/Drag
69. It is a stationary vane projecting from the upper surface of an airfoil ,which is used to prevent the :
a) Chord wise flow of air

b) Span wise flow of air

c) prevent turbulence

d) Increase the stalling angle

Ans: b) Span wise flow of air
70. This drag depends on fineness ratio:

a) Profile drag b)Wave drag c)Form drag d).Induced drag

Ans: c)Form drag
Ref :Mechanic of flight by AC Kermode 11th edition page 48 Para: Form drag

71. The larger the wing span as compared to the chord ,the greater the lift is obtained, this ratio is called:
a) Aspect ratio b) Fineness ratio c) Taper Ratio d)None

Ans : a) Aspect ratio

Ref : Airframe & Power plant MECHNICS AC 65-15A Page No 33 Para : Wing Area
72. Turbulence and skin friction are controlled by the :

a) Aspect ratio b) Fineness ratio c) Taper Ratio d)None

Ans: b) Fineness ratio

Ref : Airframe & Power plant MECHNICS AC 65-15A Page No 32 Para : Wing Area
73. If the wing has high fineness ratio :
a) It is a very thin wing b) It is a thick wing

c) As in (a) it produces a large amount of skin friction.

d) As in (b) it produces a large amount of turbulence

Ans: c) As in (a) it produces a large amount of skin friction.

Ref : Airframe & Power plant MECHNICS AC 65-15A Page No 32 Para : Wing Area
74. A wing with high fineness ratio produces :

a) a large amount of skin friction and it is a very thin wing

b) a large amount of turbulence and it is a thick wing

c) a large amount of skin friction and it is a very thick wing

d) a large amount of turbulence and it is a thin wing
Ans : (a) a large amount of skin friction and it is a very thin wing
 g y g
Ref : Airframe & Power plant MECHNICS AC 65-15A Page No 32 Para : Shape of the Airfoil
75. The study of airflow at high speeds must account for the changes in air density and consider the fact that
the air is:

a) incompressible b) compressible c) Normal d)None b) compressible

Ans : b) compressible

Ref : Aircraft basic science by Kros & Rardon 7th edition page No 68
76. The speed of the air flowing a particular part of the aircraft is called the :
a) correct speed b) Local speed c) sonic speed d0 Normal speed

Ans : b) Local speed

Ref : Aircraft basic science by Kros & Rardon 7th edition page No 69

77. When flight speed exceeds the speed of sound (M=1.05) , the bow wave forms at the :
a) Trailing edge of the wing b) Leading edge of the wing c) Wing tip d)none
Ans : b) Leading edge of the wing

Ref : Aircraft basic science by Kros & Rardon 7th edition page No 69
78. When the leading edge of the wing is higher than the trailing edge, the angle of Incidence is said to be :
a) Negative b) Positive c) Neutral d) Equal

Ans : ( b) Positive
Ref : Airframe & Power plant MECHNICS AC 65-15A Page No 32 Para : Angle of Incidence

79. The angle between the flight path and the horizontal is called the ;
a) Stalling angle b) Critical angle c) Glide angle d) None
Ans : c) Glide angle

Ref : Aerodynamics by C J Clancy page No 400 Para 14.4

80. The pitching moment is positive when :

a) It tends to push the nose upwards b) It tends to push the nose downwards
c) No change d) None
Ans : a) It tends to push the nose upwards

Ref :Mechanic of flight by AC Kermode 11th edition page 79

81. The pitching moment and its coefficient ,depends on

a) Only on the Lift b) Position on center of pressure

c) Reference Point d) All are correct
Ans : d) All are correct

Ref : Mechanic of flight by AC Kermode 11th edition page 85

82. The Lift L is always defined as the component of the aerodynamic force :

a) Parallel to the relative wind b) Perpendicular to the relative wind

c) It is the downward force d) None
Ans : b) Perpendicular to the relative wind
Ref ; Introduction of flight D Anderson Jr 5th edition page 255

83. Within certain limitations the lift ,drag and pitching moment of an airfoil depend on :
a) The shape and plan area of the airfoil b) The square of velocity

c) The density of air d) All are correct

Ans : ( d) All are correct
Ref : Mechanics of Flight by AC Kermode Page No 53 Para : Air speed Indicator corrections

84. It is the ratio of the total load supported by the airplane’s wing to the actual weight of the airplane and its
contents:
a) Wing loading c) Weight factor c) Load factor d) None

Ans : (c) Load factor

Ref : Aircraft Maint &Repair by Kroes .Watkins.Delp, VI Edition Page No 15
85. In this angle of attack at which the lift coefficient of an airfoil is maximum and beyond which it begins to
decrease owing to the airflow being separated:

a) Critical angle b) Incidence angle c) stalling angle d) none

Ans : c) stalling angle
Ref : Mechanics of Flight by AC Kermode Page No 83 Para : Stalling of airfoil

86. The taper ratio is the ratio of:

a) tip chord to root chord b) root chord to tip chord

c) Span/mean chord d) Length /breath

Ans : a) tip chord to root chord
Ref : Aircraft basic science by Kros & Rardon 7th edition page No 86

87. The induced drag is caused by :

a) due to turbulant flow b) more number exposed parts c) caused by the lift

Ans : caused by the lift

Ref : Ref : Mechanics of Flight by AC Kermode Page No 101 Para : Induced drag
88. It is the speed at which the airflow over any position of an airfoil surface reaches the speed of sound:

a) Mach Number b) Critical speed c) critical mach number d)Maximum speed

Ans : c) critical mach number

Ref :A&P Technician AIRFRAME by Jeppesen Page No 1-13 Vortex Generator

89. The three axes pass through a common reference point is called :
a) Center of Pressure b) center point c) Midpoint d) Center of Gravity

Ans : d) Center of Gravity

Ref :A&P Technician AIRFRAME by Jeppesen page No

90. It is a simply small plates intended to prevent the outward drift of the boundary layer which is a factor in
causing the tip stall:
a) Boundary layer fences b) Vortex generators c) wing fences d) plates
Ans : a) Boundary layer fences

Ref : Aerodynamics by C J Clancy page No 100 Para 5.31

91. The trailing edge flap is simply a small auxiliary airfoil, located near the rear of a main airfoil is used to:

a) vary the lift provided by the various airfoils on the aircraft in general conditions of flight
b) As in (a) it changes the geometry of the airfoil
c) it bring changes to the aerodynamic characteristics .

d) All are correct.

Ans : d) All are correct

Ref : Aerodynamics by C J Clancy page No 102 Para 6.2

92 . The purpose of boundary layer suction is to :
a) prevent flow separation b) keep drag low c) prevent transition d) All are correct

Ans: d) All are correct

Ref : Aerodynamics by C J Clancy page No 113 Para 6.13
93. The lift L, acting vertically upwards through the :

a) Center of Gravity b) Point of balance c) Center of Pressure d) Reference point

Ans : c) Center of Pressure

Ref : Mechanics of Flight by AC Kermode Page No 147 Para : The four forces
94. The airplane may travel to right or left along the lateral axis :such motion is called;
a) Rolling b) Descending c) Side slipping or skidding d) Ascending

Ans : c) Side slipping or skidding

Ref : Mechanics of Flight by AC Kermode Page No 231

95. When an aircraft experiences induced drag :

a) Air flows under the wing spanwise towards the tip and on top of the wing spanwise towards the root.
b) Air flows under the wing spanwise towards the root and on top of the wing spanwise towards the tip.

c) Niither (a) or (b) since induced drag does not caused by span wise flow
d) None

Ans: a) Air flows under the wing spanwise towards the tip and on top of the wing spanwise towards the root
Ref : Aerodynamics by C J Clancy page No 79 Para 5.17 Induced drag
96. The relationship between induced drag and airspeed is,induced drag is:

a) Directly proportional to the square of speed

b) Directly proportional to speed

c) Inversely proportional to the square of speed.

d) None
Ans: c) Inversely proportional to the square of speed
 yp p q p
Ref : Aerodynamics by C J Clancy page No 79 Para 5.17 Induced drag
97. The principal factors which determine the aerodynamic characteristics of a wing:
a) The wing area b) Aspect ratio c) Taper ratio d All are correct
Ans : d All are correct

Ref : Aerodynamics by C J Clancy page No 72 Para 5.13

98. It is the ratio of the tip chord to the root chord:
a) Chord ratio b) Aspect ratio c) Fineness ratio d) Taper ratio

Ans: d) Taper ratio

Ref : Aircraft basic science by Kros & Rardon 7th edition page No 69

99. It is the device designed to reduce the lift on a wing is called :

a) Flap b).Slats c) Aileron d)Spoilers
Ans: d)Spoilers

Ref : Aircraft basic science by Kros & Rardon 7th edition page No 92 Para: Spoilers
100. On an airfoil section, the force of lift acts perpendicular to, and the force of drag acts parallel to the :
a) Flight path b) Longitudinal axis c) Chord line d)lateral axis
Ans : c) Chord line
Ref : Aircraft basic science by Kros & Rardon 7th edition page No78 Para: Lift

101. The point on the wing leading edge, where the airflow divides is called:
a) Dividing point b) Mid point c) Stagnation point d) Centre point
Ans : c) Stagnation point

Ref : Aircraft basic science by Kros & Rardon 7th edition page No 63 Para: Airfoil
102. Mention the relationship between the forces acting on an aircraft in level flight, for that the aircraft to be
in a state of equilibrium:

a) L=W and T=D b) L=D and T=W c) L= W+D d) L=T and W=D
Ans: a) L=W and T=D
Ref : Aircraft basic science by Kros & Rardon 7th edition page No 98 Para: Forces on the airplane in flight

he speed of the air flowing over a particular part of the ac is called the: - a) Maximum speed b) Minimum
d c) High speed d) Local speed
d) Local speed

Aircraft basic science by Kros & Rardon 7th edition page No 69 Para:High speed

Flap is a high lift surface operated: a) Only at the time of landing b). Only at the time of take off c) Both for
off and landing d)4. To increase drag in flight
c) Both for take off and landing

Aircraft basic science by Kros & Rardon 7th edition page No 88 Para:Wing flaps
The automatic slat forms a slot when: - a) The slat opens automatically at high angle of attack b) The angle of
k is low
e aircraft is flying at cruising speed
e slat lever in the cockpit is pulled up

a) The slat opens automatically at high angle of attack

Aircraft basic science by Kros & Rardon 7th edition page No 69 Para:Slats

Which flying control surface(s) give(s) control about aircraft normal axis
e elevator b) The rudder c) The aileron d) The flap
b) The rudder

Aircraft basic science by Kros & Rardon 7th edition page No 106 Para:Rudder
The primary and secondary control effect of the aileron are :

l and yaw b) Roll and pitch c) Pitch and yaw d) Yaw and roll
a) Roll and yaw
Aircraft basic science by Kros & Rardon 7th edition page No 106 Para:Aileron

Aileron give :
eral control about the longitudinal axis
eral control about the normal axis

ngitudinal control about lateral axis

ectional control about normal axis

a) Lateral control about the longitudinal axis

Aircraft basic science by Kros & Rardon 7th edition page No 106 Para:Aileron
f the control column is moved forward and to the left :

e left aileron moves up,right aileron moves down,elevator moves down

e left aileron moves up, right aileron moves down, elevator moves up

e left aileron moves down, right aileron moves up, elevator moves up
The left aileron moves down, right aileron moves up, elevator moves down
a) The left aileron moves up,right aileron moves down,elevator moves down

An airfoil is designed to produce lift resulting from a difference in the :

gher air pressure below and lower air pressure above the surface

egative air pressure below and vacuum above the surface

th side equal pressure
wer air pressure below and higher air pressure above the surface

a) The left aileron moves up,right aileron moves down,elevator moves down
A wing which is inclined downwards from root to tip is said to have:

hedral b) Washout c) Taper d)Sweep

a) Anhedral
Mechanics of Flight by AC Kermode Page No 260 Para : Dihedral
 g y g
112. The tail plane is usually set an angle less than that of the main plane, the angle between the chord of the
tail plane and the chord of the main plane being known as the :
a) Dihedral b) Lateral Dihedral

c) Longitudinal Incidence d) Longitudinal Dihedral

Ans : d) Longitudinal Dihedral

Ref : Mechanics of Flight by AC Kermode Page No 260 Para : Longitudinal Dihedral

113. It is the stationary vane ,projecting from the upper surface of an airfoil .ich is used to prevent the span
wise flow of air:
a) winglets b) wing fences c) vortex generator d) End plate

Ans : b) wing fences

Ref : Aircraft basic science by Kros & Rardon 7th edition page No 95

114. The term refers to the angle at which the wings are slated rearward from the root to the tip:
a) wing incidence b) Critical angle c) sweep back d) taper angle
Ans : c) sweep back(Ref : Aircraft basic science by Kros & Rardon 7th edition page No 95)

115. If a wing has a long span and a very narrow chord , it is said to have a:
a) Low aspect ratio b) Medium aspect ratio c) High aspect ratio c) Taper ratio
Ans : c) High aspect ratio

Ref: Aviation Maint Technician hand book General Page No 3.41 Para AOA
116. Many aeoplanes are designed with a greater angle of incidence at the root of the wing than at the tip
and this is referred to as :

a) Down wash b) Wash-In c) Upwash d)Wash-out

Ans : d)Wash-out
Ref : Aviation Maint Technician hand book General Page No 3.41 Para AOA

117. As the wing moves forward through the air , the boundary layer at first flow smoothly over the
streamlined shape of the airfoil,this flow is called :
a) Laminar layer b) Uniform layer c) Undisturbed layer d) None

Ans : a) Laminar layer

Ref : Aviation Maint Technician hand book General Page No 3.41 Para Boundary layer flow
118. The resultant stream of air which flows over the fuselage ,tail units ,and other parts of the airplane is
called:

a) Back stream b) Behind stream c) Slip stream d)Rear stream

Ans : c) Slip stream

Ref : Mechanics of Flight by AC Kermode Page No 143 Para : Slip stream

119. A rectangular wing has a taper ratio 0f 1.0 ,and the pointed tip delta wing has a taper ratio of :
a) 1.0 only b) Greater than 1 c) 0.0 d) Lesser than 1

Ans : c) 0.0
Ref : Aircraft basic science by Kros & Rardon 7th edition page No 86
120. It is the speed that pilots reads on Airspeed Indicator based on dynamic pressure with respect to
standard sea level conditions
a) True Air Speed b) Indicated Airspeed

c) Calibrated Air Speed d) Equivalent Air Speed

Ans : b) Indicated Airspeed

121. The effect of down wash is:

a) It reduces the effective incidence of the wing
b) This affects the lift and drag characteristics of the wing adversely.

c) In conventional aircraft design, down wash affects the flow over the airplane.
d) All are correct.

Ans : All are correct

Ref : Aerodynamics by C J Clancy page No 75 Para 5.14
QUESTIONS PHYSICS OF ATMOSPHERE

1. What is atmosphere ,and its compositions

2. Name the different layers of atmosphere and its properties-
3. Briefly explain about troposphere:-

4. What is international standard atmosphere? And its importace

5. What is wind shear and wind gradient.

7. Explain with the neat diagram the different layer of atmosphere and the importance of ionosphere
8 Explain Density and the its effects on aircraft performance
9.Write the difference between Wind speed, Ground speed and Air speed

10.Explain True Airspeed,Indicated Air speed, Calibrated Airspeed and Equivalent airspeed.
QUESTIONS 8.2 AERODYNAMICS:

1. Explain Bernoulli’s theorem with neat diagam

2..What is boundary layer and its importance.
3. Discuss the various forms of drag

4. Write short notes on:

a) Airfoil b) Angle of attack c) Dihedral d) Wash out e) Stagnation point

5 .Write short notes on:

a. Angle of Incidence b) Center of Gravity c) Center of Pressure d)Aspect Ratio e) L/D ratio
6.Explain with the neat diagram the four forces acting on airplane in level flight

7.Discuss the term aspect ratio, taper ratio, and Fineness ratio.
8. Briefy explain the various factors governing the airplane performance

9. How the Airfoil gets contaminated and explain the preventive measures.
10. Draw and explain the various parts of airplane .
11. Briefly explain the nomenclature of an airfoil with tne neat diagram.
12.Define the factors affecting the Lift and Drag.

13. Write the factors to be considered for selection of airfoil and the criteria for Ideal airfoil should possess.
14. Explain a) Aerodynamic Center b) Stalling speed c) Stalling angle d)Mach Number.

SEM-II UNIT -3 & 4

1. The sweep of a wing causes definite changes in

a) Compressiblity b) Maximum lift c) Stall characteristics d) All are correct

Ans : d) All are correct

Ref : Aircraft basic science by Kros & Rardon 7th edition page No 87

2. Swept wings tend to stall first near the:

a) Wing Root b) Wing tip c) None

Ans : b) Wing tip

Ref : Aerodynamics by C J Clancy page No 99 Para 5.30 Effect of planform

3.If the aspect ratio is greater :
a) More induced drag b) Less induced drag c) No induced drag

Ans : b) Less induced drag

Ref : : Mechanics of Flight by AC Kermode Page No 101 Para : induced drag

4. If the center of pressure is behind the center of gravity the nose will tend to :
a) rise and tail tend to drop b) drop and the tail to rise c) straight &level flight
Ans : b) drop and the tail to rise

Ref : : Mechanics of Flight by AC Kermode Page No 149 Para :Condition of equilibrium

5. To get maximum endurance ,must use the :

a) Minimum power b) Least possible fuel in a given time

c) both (a) & (b) are correct c) None
Ans : c) both (a) & (b) are correct

Ref : : Mechanics of Flight by AC Kermode Page No 173 Para :Endurance

6. If an aeroplane is to glide as far as possible, the AOA during the glide must be such that the :

a) Lift/Drag is maximum b) Lift /Drag is minimum

c) Lift is more d) Drag is more
Ans : a) Lift/Drag is maximum

Ref : : Mechanics of Flight by AC Kermode Page No 181 Para :Gliding

7. When the aeroplane during glide , the greater weight will affect the :

a) Gliding angle b) Range c) Speed d) All are correct

Ans : c) Speed
Ref : : Mechanics of Flight by AC Kermode Page No 185 Para :Glide

8. The free –stream mach number at which sonic flow is first obtained somewhere on the airfoil surface is
called :
a) Mach Number b) Special Mach Number c) Critical Mach Number d)None

Ans : c) Critical Mach Number

Ref :Introduction of flight by John D Anderson Jr ,5th edition, Page 283,Para 5.9
9. When an object moves along a curved path, the motion is called :

a) Rectilinear b) Linear c) Curvilinear d) None

Ans : c) Curvilinear

Ref :Introduction of flight by John D Anderson Jr ,5th edition, Page 392

,Para 6.2
10. The forces of lift and drag are the direct result of the relationship between the:

a) Relative wind b) aircraft c)Gravitational Force d) Both (a) & (b) correct.
Ans : d) Both (a) & (b) correct.
Ref :FAA-H-8083-31 by FAA page No 1.7 para Thrust and Drag

11. The lift L is always defined as the component of the aerodynamic force :
a) Perpendicular to the relative wind b) Parallel to the relative wind

c) Vertical to the relative wind d) Horizontal to the relative wind

Ans : a) Perpendicular to the relative wind
Ref :Introduction of flight by John D Anderson Jr ,5th edition, Page 255

,Para 5.2
12. The maximum rate of climb for given aircraft decreases with ;

a) Decreasing altitude b) Increasing altitude c) No effect on altitude

Ans : b) Increasing altitude
Ref : Aerodynamics by C J Clancy page No 437 Para 15.8 Max rate of climb

13 A wing that produces a large amount of skin friction due to its :

a) Low fineness ratio b) High fineness ratio c) Taper ratio d) High aspect ratio

Ans : b) High fineness ratio

Ref :FAA-H-8083-31 by FAA page No 2.5 para Shape of the airfoil
14. A wing with a low fineness ratio produces a :

a) Laminar flow b) Critical flow c) Turbulent flow d) Smooth flow

Ans : c) Turbulent flow

Ref :FAA-H-8083-31 by FAA page No 2.5 para Shape of the airfoil

15 A thick wing has :
a) Low fineness ratio b) High fineness ratio c) fineness ratio
Ans : a) Low fineness ratio

Ref :FAA-H-8083-31 by FAA page No 2.5 para Shape of the airfoil

16 Turbulence and skin friction are controlled mainly by the :

a) Aspect ratio b) taper ratio c) Fineness ratio d) None

Ans : a) Low fineness ratio
Ref :FAA-H-8083-31 by FAA page No 2.5 para Shape of the airfoil

17 . When the leading edge of the wing is higher than the trailing edge, the angle of Incidence is said to be :
a) Negative b) positive c) Neutral d ) None

Ans : b) positive
Ref :FAA-H-8083-31 by FAA page No 2.6 para Angle of Incidence
18. The more streamlined object is, the parasite drag is:

a) More b) Less c) No drag d) None

Ans : b) Less
Ref: Aircraft basic science by Krose and Rardon 7th edition page No 66 Para

Parasite drag
19. The more dense the air moving past the airplane, the parasite drag is:

a) Greater b) Lesser c) No drag d) None

Ans : a) Greater
Ref: Aircraft basic science by Krose and Rardon 7th edition page No 66 Para

Parasite drag
20. The larger size of the object in the airstream , the parasite drag is :

a) Greater b) Lesser c) No drag d) None

Ans : a) Greater
Ref: Aircraft basic science by Krose and Rardon 7th edition page No 66 Para

Parasite drag
21. As the airspeed increases, the amount of parasite drag is :

a) Decreases b) Increases c) No effect d) None

Ans: b) Increases
Ref: Aircraft basic science by Krose and Rardon 7th edition page No 66 Para

Parasite drag
22. When the lift vector is tilted rearward due to the downwash ,the lift is lost. This loss of lift is :

a) Skin friction Interference drag c) Induced drag d) Wave drag

Ans : c) Induced drag
Ref: Aircraft basic science by Krose and Rardon 7th edition page No 66 Para
 y p g
Induced drag.
23. The principal factors which determine the aerodynamic characteristics of a wing are:

a) Wing area b) Aspect and Taper ratio c) Sweep back d)All are correct
Ans : d)All are correct

Ref: Aircraft basic science by Krose and Rardon 7th edition page No 81 Para
Shape of Airfoil.
24. A rectangular wing has a taper ratio of :

a) 0 b) <1 c) > 1 d) 1
Ans: d) 1

Ref: Aircraft basic science by Krose and Rardon 7th edition page No 86 Para
Taper
25. The pointed tip delta wing has a taper ratio of :

a) 0 b) <1 c) > 1 d) 1
Ans: a) 0
Ref: Aircraft basic science by Krose and Rardon 7th edition page No 86 Para

Taper
26 The sweep of a wing causes definite changes in :

a) Compressibility b) Maximum Lift c)Stall Characteristics d) All are correct

Ans : d) All are correct
Ref: Aircraft basic science by Krose and Rardon 7th edition page No 86 Para

Taper.
27 This drag is inversely proportional to the square of the speed :

a) Interference drag b) Form drag c) Induced drag

Ans : c) Induced drag
Ref : : Mechanics of Flight by AC Kermode Page No 104 Para :Induced drag

28 For an aerofoil of symmetrical shape zero lift corresponds to :

a) +2 degree AOA b) Zero AOA c) -2 AOA d)None

Ans : b) Zero AOA

Ref : : Mechanics of Flight by AC Kermode Page No 71 Para :Line of Zero lift
29. The main purpose of Lift dumpers is to :

a) Increase drag b) Destroy Lift c) Both (a) and (b) correct

Ans: c) Both (a) and (b) correct

Ref : Mechanics of Flight by AC Kermode Page No 116 Para :flaps

30. The performance capability of a jet engine is given in terms of:
a) Power b) Force c) Thrust d) Momentum
Ans : c) Thrust
Ref : Mechanics of Flight by AC Kermode Page No 130 Para :turbo fan engine

31. The propeller produces thrust by forcing the air backwards, and the resultant stream of air which flows
over the fuselage, tail units and other parts of the airplane is called the :
a) Down stream b) Drift stream c) Slipstream d) None

Ans : c) Slipstream
Ref : Mechanics of Flight by AC Kermode Page No 143 Para : Slipstream
32. On a pure Glide the greater weight does not affect the:

a) Glide angle and Range b) Glide range and Speed c) Glide angle and speed
Ans : a) Glide angle and Range

Ref : Mechanics of Flight by AC Kermode Page No 185 Para : effect on wing on gliding
33. This condition means that the pilot releases the control column and allows the elevators to take up their
own position is known as :
a) Stick fixed b) stick-free c) Stick altered

Ans: b) stick-free
Ref : Mechanics of Flight by AC Kermode Page No 258 Para : Stability
34. This condition means that the elevatore are held in their neutral position relative to the tail plane is known
as :

a) Stick fixed b) stick-free c) Stick altered

Ans: a) Stick fixed

Ref : Mechanics of Flight by AC Kermode Page No 258 Para : Stability

35. The stability or control of an airplane in so far as it concerns pitching about the lateral axis is called :
a) Lateral stability and control

b) Longitudinal stability and control

c) Directional stability and control

Ans : b) Longitudinal stability and control

Ref : Mechanics of Flight by AC Kermode Page No 259 Para : Stability
36. The stability or control of an airplane in so far as it concerns rlling about the longitudinal axis is called :

a) Lateral stability and control

b) Longitudinal stability and control

c) Directional stability and control

Ans : a) Lateral stability and control
Ref : Mechanics of Flight by AC Kermode Page No 259 Para : Stability

37. The stability or control of an airplane in so far as it concerns yawing about the normal axis is called :
a) Lateral stability and control

b) Longitudinal stability and control

c) Directional stability and control
Ans : c) Directional stability and control

Ref : Mechanics of Flight by AC Kermode Page No 259 Para : Stability

38. To prevent flutter and mechanical balancing which is liable to occur at high speeds ,this is fitted in front of
the hinge of the control surface:

a) a mass b) stopper c) Balance weight

Ans : a) a mass
Ref : Mechanics of Flight by AC Kermode Page No 259 Para : Stability

39 The control column often incorporates ,which operates when the aircraft approaches a stalled condition :
a) stick limiter b) stick pusher c ) stick shaker d) stick controller

Ans : c ) stick shaker

Ref : Mechanics of Flight by AC Kermode Page No 285 Para :control at low speeds
40. On some aircraft ,if the pilot fails to respond correctly by pushing the control stick forward ,the controls
takes over and this does the job for him is known as :

a) stick limiter b) stick pusher c ) stick shaker d) stick controller

Ans : b) stick pusher
Ref : Mechanics of Flight by AC Kermode Page No 285 Para :control at low speeds

41 The downwash is particularly very important due to this fact :

a) It reduces the effective incidence of the wing

b) This affects the lift and drag characteristics of the wing adversely
c) It affects the flow over the tail plane in conventional aircraft which affects its stability.
d) all are correct

Ans : d) all are correct

Ref : Aerodynamics by C J Clancy page No 75 Para 5.14 Effect of planform

42. Any wing at zero lift will produce :

a) Induced drag b) No induced drag c) Interference drag
Ans : b) No induced drag

Ref : Aerodynamics by C J Clancy page No 82 Para 5.17 Induced drag

43 This determines the aircraft stalling speed :

a) wing weight b) wing planform c) wing loading

Ans : c) wing loading
Ref : Aerodynamics by C J Clancy page No 75 Para 5.22 Cl in straight flight

44. To achieve low stalling speed this requires:

a) High wing loading b) Low wing loading c) Critical wing loading

Ans : b) Low wing loading

Ref : Aerodynamics by C J Clancy page No 75 Para 5.22 Cl in straight flight
 y y yp g g g
45. The equivalent air speed for minimum drag is independent of everything except :
a) Lift b) Thrust c) Weight d) Drag

Ans : c) Weight
Ref : Aerodynamics by C J Clancy page No 93 Para 5.25 Drag

46. The thickness distribution of the airfoil essentially control the :

a) Lift b) Thrust c) As in (a) Moment characteristics of the airfoil d) Drag
Ans : c) As in (a) Moment characteristics of the airfoil

Ref : Introduction to flight By John AndersonJr 5th edition page No 254 para 5.2
47. The temperature is a measure of the average :

a) Potential energy of the particles in the gas

b) Kinetic energy of the particles in the gas
c) Pressure energy of the particles in the gas

Ans : b) Kinetic energy of the particles in the gas

Ref : Introduction to flight By John AndersonJr 5th edition page No 58 para; Temp
48. An adiabatic process is one which :

a) Heat is added b) No heat is added or taken away c)None

Ans : b) No heat is added or taken away

Ref : Introduction to flight By John AndersonJr 5th edition page No147 para; 4.6
49. The major consequences of the flow separating over an airfoil :
a) A drastic loss of lift b) A major increase in drag c) Both are correct.

Ans : c) Both are correct.

Ref : Introduction to flight By John AndersonJr 5th edition page No223 para; 4.20

50. Thin wings with large angles of sweepback have the :

a) more wave drag b) smallest wave drag c) No wave drag
Ans : b) smallest wave drag

Ref : Introduction to flight By John AndersonJr 5th edition page No332 para; 5.16
51. The slowest speed at which an airplane can fly in straight and level flightis defined as the :

a) Normal speed b) critical speed c) Effective speed d) Stalling speed

Ans : d) Stalling speed
Ref : Introduction to flight By John AndersonJr 5th edition page No342 para; 5.17

52 In order to decrease the Stalling speed (Vstall):

a) Increse CL Max b) Decrease CL Max c) ) Increase AOA

Ans : a) Increse CL Max

Ref : Introduction to flight By John AndersonJr 5th edition page No342 para; 5.17
The stability of an aircraft is sometimes called:

a) Inherent stability b) coherent stability c) Neutrality d) capability