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?Â
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Question 3 of 362
3. Question
Angle of attack is the angle between:Â
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Question 4 of 362
4. Question
A laminar boundary layer is a layer, in which:Â
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Question 5 of 362
5. Question
As it applies to airfoils. Which statement is in agreement with Bernoullis Principle?Â
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Question 6 of 362
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:Â
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Question 7 of 362
7. Question
As subsonic air flows through a convergent duct:Â i. static pressure ii. velocityÂ
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Question 8 of 362
8. Question
A low wing loading (aircraft weight has been reduced):Â
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Question 9 of 362
9. Question
As the angle of attack of a wing is increased in level flight:Â
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Question 10 of 362
10. Question
A reduction in air pressure results in:Â
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Question 11 of 362
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…Â
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Question 12 of 362
12. Question
A symmetrical aerofoil section at CL = 0 will produce?Â
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Question 13 of 362
13. Question
As the camber of an aerofoil section is increased:Â
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Question 14 of 362
14. Question
A wing has a span of 50 feet and an area of 200 square feet. Its mean chord would be:Â
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Question 15 of 362
15. Question
As the center of gravity is changed, recovery from a stall becomes progressively:Â
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Question 16 of 362
16. Question
A wing stalling angle is:Â
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Question 17 of 362
17. Question
At an aeroplanes minimum drag speed, what is the ratio between induced drag Di and profile drag Dp (Di/Dp)?Â
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Question 18 of 362
18. Question
A wing will stall:Â
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Question 19 of 362
19. Question
At the point a wing enters a stalled condition:Â
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Question 20 of 362
20. Question
A wing with higher span compared with a lower wing span has (equal wing surface):Â
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Question 21 of 362
21. Question
At the point of stall:Â
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Question 22 of 362
22. Question
At the same weight, with the CG at its forward limit:Â
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Question 23 of 362
23. Question
An aircraft flying straight and level; if density halves, aerodynamic drag will:Â
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Question 24 of 362
24. Question
At the tip of the wing in level flight, the air flows:Â
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Question 25 of 362
25. Question
An aircraft whose weight is 237402 N stalls at 132 kt. At a weight of 356103Â NÂ it would stall at:Â
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Question 26 of 362
26. Question
At zero angle of attack in flight, a symmetrical wing section will produce:Â
Â
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Question 27 of 362
27. Question
An aircraft wing stalls at:Â
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Question 28 of 362
28. Question
A High Aspect Ratio wing is a wing with:Â
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Question 29 of 362
29. Question
An increase in angle of attack (below the stalling angle of attack) increases lift because:Â
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Question 30 of 362
30. Question
An increase in the speed at which an airfoil passes through the air increases lift because:Â
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Question 31 of 362
31. Question
Total pressure of air will:
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Question 32 of 362
32. Question
A cambered airfoil with zero angle of attack, will in flight produce:Â
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Question 33 of 362
33. Question
A deployed slat will:Â
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Question 34 of 362
34. Question
A Fowler flap is one which when selected:Â
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Question 35 of 362
35. Question
A plain flap will increase CLmax by:Â
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Question 36 of 362
36. Question
A propeller blade is twisted from root to tip to:Â
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Question 37 of 362
37. Question
A slotted flap will increase the CLmax by:Â
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Question 38 of 362
38. Question
After take-off the slats (when installed) are always retracted later than the flaps. Why?Â
Â
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Question 39 of 362
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?Â
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Question 40 of 362
40. Question
An aircraft is constructed with dihedral to provide:Â
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Question 41 of 362
41. Question
With the centre of gravity on the forward limit, the stalling speed would be:
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Question 42 of 362
42. Question
With increasing speed in level flight:
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Question 43 of 362
43. Question
With increasing angle of attack, the stagnation point will move (I) and the point of lowest static pressure will move (II):
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Question 44 of 362
44. Question
With increasing angle of attack, the C of P on an airfoil will reach its most forward point:
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Question 45 of 362
45. Question
With increasing altitude the following occurs:
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Question 46 of 362
46. Question
With an increase of aircraft weight at a constant IAS:
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Question 47 of 362
47. Question
With increasing altitude the angle at which a wing will stall:
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Question 48 of 362
48. Question
Winglets:
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Question 49 of 362
49. Question
With an increase in aspect ratio for a given IAS induced drag will:
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Question 50 of 362
50. Question
Which statement is true for a symmetrical wing section:
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Question 51 of 362
51. Question
Which statement is correct about the Cl and angle of attack?
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Question 52 of 362
52. Question
Which statement is correct?
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Question 53 of 362
53. Question
Which statement about induced drag and tip vortices is correct?
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Question 54 of 362
54. Question
Which ratio is defined as the aspect ratio of a wing?
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Question 55 of 362
55. Question
Which one of the following statements about Bernoulli’ s theorem is correct?
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Question 56 of 362
56. Question
Which of the following would tend to increase the density altitude at a given airport?
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Question 57 of 362
57. Question
Which of the following wing planform produces the lowest induced drag? (all other relevant factors constant)
Which of the following wing planform gives the highest local lift coefficient at the wing root?
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Question 59 of 362
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.
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Question 60 of 362
60. Question
Which of the following statements is true?
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Question 61 of 362
61. Question
Which of the following statements are correct?
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Question 62 of 362
62. Question
Which of the following statements about the stall of a straight wing aeroplane is correct?
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Question 63 of 362
63. Question
Which of the following statements about the spin is correct?
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Question 64 of 362
64. Question
Which of the following situations leads to a decreasing stall speed (IAS)?
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Question 65 of 362
65. Question
Which of the following is the correct designation of stall speed in the landing configuration:
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Question 66 of 362
66. Question
Which of the following is the cause of wing tip vortices?
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Question 67 of 362
67. Question
Which of the following expressions could represent the relationship between force, mass and acceleration:
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Question 68 of 362
68. Question
Which of the following descriptions most accurately describes the airflow that causes wing tip vortices?
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Question 69 of 362
69. Question
Which of the following decreases induced drag?
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Question 70 of 362
70. Question
Which formula or equation describes the relationship between force (F), acceleration (a) and mass (m)?
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Question 71 of 362
71. Question
Which location on the aeroplane has the largest effect on the induced drag?
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Question 72 of 362
72. Question
Where does the lift act on the wing?
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Question 73 of 362
73. Question
When vortex generators are fitted they will normally be found:
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Question 74 of 362
74. Question
When the angle of attack of a wing is increased:
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Question 75 of 362
75. Question
When the angle of attack is increased, the stagnation point moves … and the separation point moves…
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Question 76 of 362
76. Question
When the angle of attack increases in straight and level flight, we will observe:
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Question 77 of 362
77. Question
When recovering from a spin the pilot should first:
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Question 78 of 362
78. Question
When maintaining level flight an increase of speed will:
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Question 79 of 362
79. Question
When looking at the airflow over the wing, from the wing surface and up, the air is:
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Question 80 of 362
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?
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Question 81 of 362
81. Question
When an aircraft pitches up, the angle of attack of the tailplane will:
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Question 82 of 362
82. Question
When an aircraft is on the ground, with its engine running, positive propeller torque reaction of a right handed propeller will:
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Question 83 of 362
83. Question
When an aircraft is in a non-accelerated level flight, what are the relationships between lift, weight, thrust and drag?
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Question 84 of 362
84. Question
When an aircraft enters ground effect:
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Question 85 of 362
85. Question
When an aircraft enters ground effect:
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Question 86 of 362
86. Question
When a pilot makes a turn in horizontal flight, the stall speed:
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Question 87 of 362
87. Question
What will happen in ground effect?
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Question 88 of 362
88. Question
What is the standard stall recovery for a light aircraft?
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Question 89 of 362
89. Question
What is the SI unit that results from multiplying kg and m/s squared?
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Question 90 of 362
90. Question
What is the MAC of a wing?
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Question 91 of 362
91. Question
What is the effect on induced drag on entering the ground effect?
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Question 92 of 362
92. Question
What is the effect on induced drag of weight and speed changes?
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Question 93 of 362
93. Question
What is the effect of high aspect ratio of an aeroplanes wing on induced drag?
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Question 94 of 362
94. Question
What is ground effect?
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Question 95 of 362
95. Question
What is a high speed stall?
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Question 96 of 362
96. Question
What effect on induced drag does entering ground effect have:
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Question 97 of 362
97. Question
What effect does an increased load have on an aircraft?
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Question 98 of 362
98. Question
What changes in angle of attack must be made to maintain altitude while the airspeed is being increased?
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Question 99 of 362
99. Question
What are the standard temperature and pressure values for sea level?
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Question 100 of 362
100. Question
What are the SI units of the following?
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Question 101 of 362
101. Question
What are the correct SI units for density and force?
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Question 102 of 362
102. Question
Vortex generators:
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Question 103 of 362
103. Question
Vectors:
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Question 104 of 362
104. Question
Under which condition will pressure altitude be equal to true altitude?
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Question 105 of 362
105. Question
Under what condition is indicated altitude the same as true altitude?
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Question 106 of 362
106. Question
Total Drag is the sum of:
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Question 107 of 362
107. Question
To maintain level flight, if the angle of attack is increased the speed must be:
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Question 108 of 362
108. Question
The wing of an aeroplane will never stall at low subsonic speeds as long as:
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Question 109 of 362
109. Question
The wing area divided by the span of a wing is called:
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Question 110 of 362
110. Question
The wake vortices behind a large aircraft begin on takeoff … and end on landing…
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Question 111 of 362
111. Question
The value of the parasite drag in straight and level flight at constant weight varies linearly with the:
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Question 112 of 362
112. Question
The units of wing loading (I) W / S and (II) dynamic pressure q are:
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Question 113 of 362
113. Question
The units of the density of the air (I) and the force (II) are:
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Question 114 of 362
114. Question
The units of a turning moment are?
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Question 115 of 362
115. Question
The unit of density is
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Question 116 of 362
116. Question
The total pressure is:
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Question 117 of 362
117. Question
The thickness/chord ratio of a wing is also known as the:
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Question 118 of 362
118. Question
The terms q and S in the lift formula are:
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Question 119 of 362
119. Question
The term angle of attack is defined as:
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Question 120 of 362
120. Question
The term angle of attack is defined as the angle:
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Question 121 of 362
121. Question
The term angle of attack in a two dimensional flow is defined as:
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Question 122 of 362
122. Question
The static pressure is acting:
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Question 123 of 362
123. Question
The standard procedure for recovery from a stall in a light single engine aircraft is:
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Question 124 of 362
124. Question
The stalling speed in IAS will change according to the following factors?
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Question 125 of 362
125. Question
The stalling speed in IAS will change according to the following factors:
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Question 126 of 362
126. Question
The stall speed
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Question 127 of 362
127. Question
The stall speed increases, when? (all other factors of importance being constant)
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Question 128 of 362
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:
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Question 129 of 362
129. Question
The stagnation point is:
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Question 130 of 362
130. Question
The stagnation point on an aerofoil in flight is:
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Question 131 of 362
131. Question
The SI unit of force is:
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Question 132 of 362
132. Question
The sensor of a stall warning system can be activated by a change in the location of the:
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Question 133 of 362
133. Question
The SI unit of energy is:
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Question 134 of 362
134. Question
The relative thickness of an aerofoil is expressed in:
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Question 135 of 362
135. Question
The relationship between induced drag and the aspect ratio is:
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Question 136 of 362
136. Question
The purpose of a fixed spoiler on the leading edge of a wing at the root is to:
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Question 137 of 362
137. Question
The purpose of a fixed spoiler on the leading edge of a wing at the root is to:
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Question 138 of 362
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:
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Question 139 of 362
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:
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Question 140 of 362
140. Question
The point, where the aerodynamic lift acts on a wing is:
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Question 141 of 362
141. Question
The normal stall recovery procedure for a light single engined aeroplane is:
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Question 142 of 362
142. Question
The most common stall sensing devices are normally located:
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Question 143 of 362
143. Question
The Mean Chord of a wing is the:
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Question 144 of 362
144. Question
The mean chord is calculated by:
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Question 145 of 362
145. Question
The Mean Aerodynamic Chord (MAC) for a given wing of any platform is:
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Question 146 of 362
146. Question
The Mean Chord [Geometric] is the:
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Question 147 of 362
147. Question
The Lift/Drag ratio [Polar] of a wing section at its stalling angle is:
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Question 148 of 362
148. Question
The lift formula is:
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Question 149 of 362
149. Question
The lift force, acting on an aerofoil:
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Question 150 of 362
150. Question
The interference drag is created as a result of:
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Question 151 of 362
151. Question
The influence of ground affect on landing distance will be to:
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Question 152 of 362
152. Question
The induced drag of an aircraft in level flight:
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Question 153 of 362
153. Question
The induced angle of attack is the result of:
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Question 154 of 362
154. Question
The induced drag:
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Question 155 of 362
155. Question
The higher the aspect ratio of a wing:
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Question 156 of 362
156. Question
The four forces of lift, weight, thrust and drag in level flight act through:
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Question 157 of 362
157. Question
The greatest vortex strength occurs when the generating aircraft is:
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Question 158 of 362
158. Question
The four basic forces acting on an airplane in unaccelerated flight are:
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Question 159 of 362
159. Question
The following unit of measurement kgm/s2 is expressed in the SI-system as:
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Question 160 of 362
160. Question
The following factors increase stall speed:
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Question 161 of 362
161. Question
The fineness ratio of an airfoil is:
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Question 162 of 362
162. Question
The Fineness Ratio of a wing is the:
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Question 163 of 362
163. Question
The fineness ratio is:
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Question 164 of 362
164. Question
The Cl – alpha curve of a positive cambered aerofoil intersects with the vertical axis of the Cl – alpha graph:
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Question 165 of 362
165. Question
The dynamic pressure increases proportionally with:
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Question 166 of 362
166. Question
The chord line is:
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Question 167 of 362
167. Question
The characteristics of a high aspect ratio wing has are:
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Question 168 of 362
168. Question
The centripetal force in a spin is a component of:
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Question 169 of 362
169. Question
The centre of pressure (c.o.p) is in its most forward position:
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Question 170 of 362
170. Question
The Aspect Ratio of a wing is the ratio of:
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Question 171 of 362
171. Question
The angle of attack of a wing profile is defined as the angle between:
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Question 172 of 362
172. Question
The angle of attack of an aerofoil section is the angle between the:
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Question 173 of 362
173. Question
The angle of attack of a two dimensional wing section is the angle between:
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Question 174 of 362
174. Question
The angle of attack is the angle between:
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Question 175 of 362
175. Question
The angle of attack at which an aircraft stalls:
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Question 176 of 362
176. Question
The angle of attack at which a wing stalls will:
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Question 177 of 362
177. Question
The angle of attack (aerodynamic angle of incidence) of an aerofoil is the angle between the:
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Question 178 of 362
178. Question
The angle between the lateral axis and the chord line is known as:
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Question 179 of 362
179. Question
The angle between the airflow (relative wind) and the chord line of an aerofoil is:
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Question 180 of 362
180. Question
The angle between the aeroplane longitudinal axis and the chord line is the:
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Question 181 of 362
181. Question
The airfoil chord line is:
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Question 182 of 362
182. Question
The airflow over the upper surface of the wing of an aircraft in level flight compared to the free stream air will:
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Question 183 of 362
183. Question
The airflow over the upper surface of a cambered wing:
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Question 184 of 362
184. Question
The aeroplane drag in straight and level flight is lowest when the:
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Question 185 of 362
185. Question
The (subsonic) static pressure:
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Question 186 of 362
186. Question
That portion of the aircrafts total drag created by the production of lift is called?
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Question 187 of 362
187. Question
Subsonic flow over a cambered airfoil at 4° angle of attack will cause:
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Question 188 of 362
188. Question
On entering ground effect, maintaining flight at the same speed:
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Question 189 of 362
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):
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Question 190 of 362
190. Question
Static pressure acts:
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Question 191 of 362
191. Question
Profile drag in straight and level flight:
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Question 192 of 362
192. Question
On the approach to land, ground effect will begin to be felt at:
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Question 193 of 362
193. Question
On an airfoil the centre of pressure will be most forward:
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Question 194 of 362
194. Question
On a symmetrical aerofoil, the pitch moment for which Cl=0 is:
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Question 195 of 362
195. Question
On a cambered airfoil the zero lift angle of attack will be:
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Question 196 of 362
196. Question
Mean chord is equal to:
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Question 197 of 362
197. Question
Minimum total drag of an aircraft occurs:
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Question 198 of 362
198. Question
Lift is the component of the total aerodynamic force which is:
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Question 199 of 362
199. Question
Lift is generated when:
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Question 200 of 362
200. Question
Lift is created over a wing because:
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Question 201 of 362
201. Question
Lift is a function of:
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Question 202 of 362
202. Question
Lift and drag on an aerofoil are vertical and respectively parallel to the:
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Question 203 of 362
203. Question
Interference drag can be reduced using:
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Question 204 of 362
204. Question
Induced drag:
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Question 205 of 362
205. Question
Induced drag:
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Question 206 of 362
206. Question
Induced drag:
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Question 207 of 362
207. Question
Induced drag on a wing in level flight:
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Question 208 of 362
208. Question
Induced drag may be reduced by:
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Question 209 of 362
209. Question
Induced drag is:
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Question 210 of 362
210. Question
Induced drag is:
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Question 211 of 362
211. Question
Induced drag is created by the:
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Question 212 of 362
212. Question
Induced drag is caused by:
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Question 213 of 362
213. Question
Induced drag is also known as:
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Question 214 of 362
214. Question
Induced drag in straight and level flight is:
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Question 215 of 362
215. Question
Induced drag at constant IAS is affected by:
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Question 216 of 362
216. Question
Induced drag can be reduced by:
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Question 217 of 362
217. Question
Increasing the aspect ratio of a wing…
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Question 218 of 362
218. Question
Increasing the angle of attack in flight will cause the:
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Question 219 of 362
219. Question
Increase of wing loading will:
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Question 220 of 362
220. Question
In straight and level flight, which of the following would cause induced drag to vary linearly if weight is constant:
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Question 221 of 362
221. Question
In straight and level flight, if airspeed … the angle of attack … and the incidence angle…
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Question 222 of 362
222. Question
In level flight, the four forces of Lift, Weight, Thrust and Drag are said to act through:
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Question 223 of 362
223. Question
In level flight an increase in angle of attack will cause:
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Question 224 of 362
224. Question
In flight the C of P by increasing angle of attack, will reach its most forward point on an airfoil:
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Question 225 of 362
225. Question
In accordance with Bernoulli’ s Theorem, where PT = Total Pressure, PS = Static pressure and q = Dynamic pressure:
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Question 226 of 362
226. Question
In a two-dimensional flow pattern, where the streamlines converge the static pressure will:
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Question 227 of 362
227. Question
In a symmetrical airfoil the mean camber line is?
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Question 228 of 362
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):
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Question 229 of 362
229. Question
In a spin:
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Question 230 of 362
230. Question
In a spin:
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Question 231 of 362
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:
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Question 232 of 362
232. Question
If you are flying at 100 kts and you increase your airspeed to 200 kts, profile drag:
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Question 233 of 362
233. Question
If the aspect ratio of a wing (for a given wing area) is decreased:
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Question 234 of 362
234. Question
If the angle of attack of a wing is increased in flight the:
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Question 235 of 362
235. Question
If the angle of attack is increased, the centre of pressure will:
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Question 236 of 362
236. Question
If temperature in a gas is kept constant and pressure increases, the density:
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Question 237 of 362
237. Question
If pressure is kept constant and temperature increases, the density:
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Question 238 of 362
238. Question
If pressure increases, with OAT and TAS constant, what happens to drag?
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Question 239 of 362
239. Question
If IAS is doubled, by which of the following factors should the original CL be multiplied to maintain level flight?
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Question 240 of 362
240. Question
If dynamic (kinetic) pressure increases, what is the effect on total drag (if all important factors remain constant)?
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Question 241 of 362
241. Question
If density is kept constant, the dynamic pressure increases proportionally with:
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Question 242 of 362
242. Question
If an aircraft is pitching up:
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Question 243 of 362
243. Question
If an aeroplane flies in the ground effect:
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Question 244 of 362
244. Question
How will frost on the wings of an airplane affect takeoff performance?
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Question 245 of 362
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?
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Question 246 of 362
246. Question
How is the thickness of an aerofoil section measured?
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Question 247 of 362
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?
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Question 248 of 362
248. Question
How does aerodynamic drag vary when airspeed is doubled? By a factor of:
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Question 249 of 362
249. Question
How do vortex generators work?
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Question 250 of 362
250. Question
A gust front is
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Question 251 of 362
251. Question
High aspect ratio:
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Question 252 of 362
252. Question
Ground Effect:
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Question 253 of 362
253. Question
Ground Effect occurs:
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Question 254 of 362
254. Question
Ground effect is most likely to result in which problem?
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Question 255 of 362
255. Question
Ground effect has the following influence on the landing distance:
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Question 256 of 362
256. Question
Geometric washout means that:
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Question 257 of 362
257. Question
Generally speaking, the transition point for an aerofoil section is the:
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Question 258 of 362
258. Question
For the same angle of attack a cambered wing will produce:
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Question 259 of 362
259. Question
For an aircraft in straight and level flight, which forces are in equilibrium?
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Question 260 of 362
260. Question
For a given angle of attack induced drag is:
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Question 261 of 362
261. Question
For a constant aircraft weight at constant IAS and in level flight: