[Xmat]

1. Energy may neither be created nor destroyed
a. law of conservation of energy b. Law of energy
c. law of aerodynamics

2. The act or process of changing place or position is
a. motion b. velocity c. speed

3. A person sitting in aircraft flying at 200 knots
a. is at rest with respect to the aircraft;
b. in motion with respect to the air and to the earth.
c. Both a & b

4. The flow of air around an object due to movement of air or object is
a. wind b. relative wind c. laminar airflow

4. The rate of motion in a particular direction in relation to time is
a. speed b. velocity c. acceleration

5. An aircraft reducing its velocity is an example of
a. negative acceleration b. deceleration c. Both

6. Newton’s first law is normally referred to as
a. law of inertia b. law of gravity c. law of aerodynamics

7. As per Newton’s second law
a. Force = mass × acceleration b. F = ma c. Both a & b

8. Newton’s law of action and reaction is
a. second law b. third law c. first law

9. As per Bernoulli’s principle the sum of pressure, kinetic and potential energy will
a. remain constant b. remain zero c. decrease

10. A surface designed to obtain lift when moves through the air
a. airfoil b. flap c. wing

11. The difference in pressure between upper and lower surfaces of the wing is called
a. drag b. weight c. lift.

12. Decrease in pressure over the upper surface of wing produces
a. one-fourth of the total lift. b. three-fourths of the total lift
d. total lift from upper surface only

13. The velocity of the free stream air flow is
a. equal to aircraft speed b. air speed c. half of aircraft speed

14. Pressure of the free stream airflow is
a. dynamic pressure b. static pressure c. air pressure

15. A point in front of structure, where the velocity of the air is zero
a. stagnation point b. boundary layer c. transition point

16. Upwash and downwash are the deflection directions of
a. wing b. air c. lift

17. The airflow closest to the wing surface is
a. upwash b. laminar air flow c. boundary layer

18. The viscosity means
a. internal resistance to flow b. external resistance to flow
c. more velocity

19. The point at which boundary layer changes to turbulent is
a. transition point b. stagnation point c. turbulent point

20. The shape of an a/c wing as projected onto a horizontal plane is
a. span b. planform c. wing design

21. The pressure below the wing is
a. equal to atmospheric pressure
b. greater than atmospheric pressure
c. equal or greater than atmospheric pressure

22. Spanwise movement of air below wing surface results in spillage over the wing tip is
a. whirlpool b. vortex c. both a & b

23. The chord of a wing is measured along
a. camber line b. chord line c. incidence line

24. The average distance from the L/E to T/E of the wing
a. mean aerodynamic chord b. mean aerodynamic camber
c. span

25. The angle, wing chord makes with the longitudinal axis
a. incidence angle b. wing setting angle c. Both a & b

26. In wash in, wing tip angle of incidence is
a. greater than wing root b. smaller than wing root c. same

27. The mean camber line lies within the
a. wing half way b. between upper and lower camber
C. Both a & b

28. The air passing over top surface of wing moves
a. greater velocity b. same velocity
c. as in a & travels more distance

30. A wing may have various airfoil sections from root to tip
a. taper or twist b. sweepback c. Both a & b

31. Turbulence and skin friction are controlled mainly
a. fineness ratio b. L/D ratio c. aspect ratio

32. The “fineness ratio” is the ratio of the chord of an airfoil to its
a. maximum thickness b. chord c. span

33. The high-lift wings have
a. positive camber on the upper surface
b. as in a & negative camber on lower surface
c. Both side positive camber

34. it is a

a. Laminar Flow Airfoil (Subsonic)
b. Circular Arc Airfoil (Supersonic)
c. Double Wedge Airfoil (Supersonic)

35. The higher the aspect ratio
a. greater the lift b. greater the lift c. lesser the lift

36. The common forms of airfoil contamination are
a. ice and snow b. frost c. ATA

37. Before flight, ice and snow
a. to be removed from aircraft
b. may not be removed from aircraft
c. to be removed as and when required

38. A 0.8 millimeter of ice on the upper wing surface
a. increases drag b. reduces lift
c. as in a& b and by 25 percent.

39. Drag is a backward force and caused by the
a. disruption of airflow by wings & fuselage
b. disruption of airflow by protruding objects
c. ATA

40. The four forces are balanced only when aircraft is in
a. straight-and-level unaccelerated flight
b. straight-and-level flight c. only a is correct

41. Which of the following is not the aerodynamic force
a. lift b. drag & thrust c weight

42. Which are the resultant of relative air and aircraft
a. thrust & drag b. lift & weight c. lift and drag

43. Angle of Attack (AOA) is the angle between
a. relative wind and chord line a. relative wind and camber line
c. relative wind and longitudinal axis

44. Lift related drag is
a. profile drag b. parasite drag c. induced drag

45. The amount of lift generated by a wing compared to its drag is
a. Lift to Drag ratio b. coefficient of lift d. only a is correct

46. L = (1/2) d v2 s CL, d indicated
a. drag produced by a/c b. density of air c. diameter of wing

47. The angle of attack is
a. chord line and relative air flow b. camber line and relative air flow
c. chord line and horizontal

48. The camber line passes
a. leading to trailing edge of wing b. root end to wing tip
c. through wing span

49. angle between chord line of wing & longitudinal axis of a/c is
a. anhedral angle b. stalling angle c. incidence angle

50. The CP moves along
a. airfoil chord b. airfoil camber c. longitudinal axis

51.With increase in AOA CP
a. moves forward b. moves rearward c. does not move

52. When the AOA increases to the maximum lift,
a. burble point is reached b. known as critical angle
c. both a & b

53. When a/c reaches to burble point, the angle is
a. burble angle b. stalling angle c. as in b & a/c stalls

54. As AOA decreases, the CP
a. moves forward b. moves back c. remains stable

55. The efficiency of wing is measured in terms of
a. lift to drag ratio b. thrust to weight ratio c. thrust to weight ratio

56. Most general use efficient airfoils have maximum thickness
a. one-third back from leading edge
b. two-third back from leading edge
c. center of camber

57. Drag due to aerodynamic resistance to motion & shape of the a/c
a. Form drag b. Skin friction c. Interference drag

58. Wave drag is formed during
a. transonic or supersonic flight b. sub sonic flight
c. hypersonic flight

59. The smoothness/roughness of the a/c surfaces leads to
a. form drag b. induced drag c. skin friction drag

60. The drag not associated with the production of lift
a. Parasite drag b. induced drag c. skin friction drag

61. The friction drag also known as
a. skin friction drag
b. as in a & proportional to surface area of wing
c. as in b & increases with square of velocity

62. Friction Drag is created in the
a. boundary layer b. due to air viscosity & surface friction
c. ATA

63. Square of velocity and surface area of the wing effects
a. form drag b. friction drag c. parasite drag

64. The increased streamlining of surfaces, exposed to relative wind
a. decreases form drag b. increases form drag
c. decreases friction drag

65. The skin friction drag can be reduced by
a. using flush rivets b. painting & polishing c. Both a & b

66. The continuous spilling of air upwards, around the wing tip is called
a. ‘tip effect’ b. ‘end effect’ c. both a & b

67. Winglets helps to reduce
a. induced drag b. form drag c. friction drag

68. Wave drag retards the forward motion of a/c in
a. supersonic flight b. wave drag formation c. as in a & b

69. The wave drag can be reduced by incorporating
a. wing sweep back b. ultra-thin wings
c. as in a & b and also anti shock bodies

70. In venturi tube
a. pressure energy increases & kinetic energy decreases
b. kinetic energy increases & pressure energy increases
c. pressure energy decreases & kinetic energy increases

71. The boundary layer is the part of airflow that is
a. away from the surface b. closest to wing surface
c. moving away from the surface
73. Width of wing from leading edge apex to the trailing edge is
a. span b. camber c. chord
74. A comparison between wingspan and chord is known as
a. aspect ratio b. fineness ratio c. L/D ratio
75. In the figure AB/CD is

a. aspect ratio b. fineness ratio c. L/D ratio

76. In the figure aspect ratio is

a. b2 / A b. b2 / A2 c. A2 / b
77. drag continually increases as airspeed increases
a. parasite Drag b. Interference c. Both a & b
78. The figure indicates angle of attack

a. 00 b. optimum angle of attack c. critical angle of attack

79. The figure shows, forces during

a. straight & level flight
b. stady flight
c. during banking

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