Q1. The blade angle of a propeller is usually referenced at:
Q2. A wind milling propeller:
Q3. If you increase the propeller pitch during a glide with idle power at constant IAS the lift to drag ratio will
Q4. If you decrease the propeller pitch during a glide with idle-power at constant IAS the lift to drag ratio will
Q5. Which definition of propeller parameters is correct?
Q6. For any propeller:
Q7. The difference between a propeller’s blade angle and its angle of attack is called:
Q8. The angle of attack for a propeller blade is the angle between blade chord line and:
Q9. Which of these definitions of propeller parameters is correct?
Q10. During the take-off roll, when the pilot raises the tail in a tail-wheeled propeller driven aeroplane, the additional aeroplane yawing tendency is due to the effect of:
Q11. Which statement is correct regarding a windmilling propeller on a multi-engined aeroplane?
Q12. Which statement about propeller icing is correct?1. Propeller icing increases blade element drag and reduces blade element lift.2. Propeller icing does not affect propeller efficiency.
Q13. Which of these statements concerning propellers is correct?
Q14. Which statement is correct regarding a propeller?1. Increasing tip speed to supersonic speed increases propeller noise.2. Increasing tip speed to supersonic speed increases propeller efficiency.
Q15. An aeroplane is fitted with a constant speed propeller If the aeroplane speed increases while manifold pressure maintains constant,(1) propeller pitch and the(2) propeller torque will:
Q16. Why is a propeller blade twisted from root to tip?
Q17. The geometric pitch of a propeller is the:
Q18. If you push forward the RPM lever of a constant speed propeller during a glide with idle power and constant speed, the propeller pitch will:
Q19. If you pull back the RPM lever of a constant speed propeller during a glide with idle power and constant speed, the propeller pitch will:
Q20. Propeller efficiency may be defined as the ratio between:
Q21. An engine failure can result in a windmilling (1) propeller and a non-rotating (2) propeller. Which statement about propeller drag is correct?
Q22. Does the pitch-angle of a constant-speed propeller alter in medium horizontal turbulence?
Q23. Constant-speed propellers provide a better performance than fixed-pitch propellers because they:
Q24. Which of these definitions of propeller parameters is correct?
Q25. Propeller efficiency/ The effective pitch of a propeller is the:
Q26. Which statement is correct?1. A propeller with a small blade angle is referred to as being in fine pitch.2. A propeller with a large blade angle is referred to as being in coarse pitch.
Q27. Which statement is correct?1. A propeller with a small blade angle is referred to as being in fine pitch2. A propeller with significant blade twist is referred to as being in coarse pitch
Q28. The propeller blade angle of attack on a fixed pitch propeller is increased when:
Q29. Which is one of the disadvantages of increasing the number of propeller blades?
Q30. Which of the following statements about a constant speed propeller is correct?
Q31. Which statement is correct?1. A propeller with little blade twist is referred to as being in fine pitch.2. A propeller with a large blade angle is referred to as being in coarse pitch.
Q32. The angle of attack of a propeller blade element is the angle between the blade element chord line and the:
Q33. Torque effect of a propeller which turns to the right produces a:
Q34. With a clockwise rotating propeller in a climb, the asymmetric thrust effect will cause:
Q35. The angle of attack of a fixed pitch propeller can be increased by:
Q36. If you increase the propeller pitch during a glide with idle-power at constant IAS the lift to drag ratio will:
Q37. Counter rotating propellers have the effect of:
Q38. With a constant speed propeller, which of the following statements is true?
Q39. Constant-speed propellers provide a better performance than fixed-pitch propellers because they:
Q40. In which of the following lists of flight conditions will torque effect be greatest in a single-engine aeroplane?
Q41. For a tail wheel aircraft with a right-handed propeller, at the start of the take-off run, asymmetric blade effect causes:
Q42. A fixed pitch propeller is usually:
Q43. Running an engine fitted with a fixed pitch propeller at full throttle with the aircraft stationary and nose into strong wind will result in:
Q44. An aeroplane is fitted with a constant speed propeller. If the aeroplane speed increases while manifold pressure remains constant (1) propeller pitch and the (2) propeller torque will:
Q45. The angle of attack of a fixed pitch propeller blade increases when:
Q46. Why is a propeller blade twisted from root to tip?
Q47. Propeller slip is the difference between the:
Q48. The blade angle of a propeller is the angle between:
Q49. What is the primary advantage of a constant speed propeller?
Q50. A constant speed propeller is one which:
Q51. The aerodynamic loads on a propeller which produce forward thrust will tend to:
Q52. The forces acting on a propeller are:
Q53. An aircraft with constant speed propeller increases its speed with constant manifold pressure. The propeller pitch will (1) and the propeller torque will (2):
Q54. How can the angle of attack of a fixed pitch propeller be increased?
Q55. If the engine is developing no thrust in a glide, if the propeller pitch is increased:
Q56. The advantage of a constant speed propeller over a fixed pitch propeller is:
Q57. The angle of attack of a fixed pitch propeller designed for cruising flight, measured at its reference station is:
Q58. The angle of attack of a fixed pitch propeller:
Q59. Propeller blade angle of attack is the angle between the chord and the:
Q60. Does the pitch-angle of a constant-speed propeller alter in medium horizontal turbulence?
Q61. The propeller CTM will:
Q62. With a fixed pitch propeller increasing speed will ___ propeller alpha and increasing power and therefore propeller RPM will ___ propeller alpha.
Q63. For a variable propeller, which way does the blade twist from root to tip?
Q64. If the propeller pitch, within its constant speed range and at constant power, during descent at constant IAS is decreased, the aeroplane lifts to drag ratio will:
Q65. If the propeller pitch, within its constant speed range and at constant power, during descent at constant IAS is increased, the aeroplane lift to drag ratio will:
Q66. When an aircraft with a fixed pitch propeller climbs, does the angle of attack of the propeller:
Q67. Drag on a windmilling propeller compared to a stationary propeller is:
Q68. With a propeller in the feathered position:
Q69. In twin engine aeroplanes with propellers turning clockwise as seen from behind:
Q70. On a single engined aircraft with a right-hand propeller the gyroscopic effect causes:
Q71. When the blades of a propeller are in the feathered position:
Q72. In an aircraft with a two-lever power control system, in a descent with the throttle closed, what would be the effect if the pitch control were pulled fully back to the flight stop?
Q73. With a propeller feathered:
Q74. An aircraft fitted with a constant speed propeller is in a gliding descent with the throttle closed and the engine at idle; what would be the effect if the propeller lever were pulled back?
Q75. An aircraft is maintaining altitude while flying with the left engine inoperative and the wings level; which of the following indications are correct?
Q76. Which statement is correct about an aeroplane, that has experienced a left engine failure and continues afterwards in straight and level cruise flight with wings level?
Q77. If the propeller RPM lever is pushed forward during a power off descent the propeller pitch:
Q78. When considering 2 multi-engine aircraft, one a jet and one with co-rotating propellers, following an engine failure in flight which of the following is most likely to occur?
Q79. A single engine aircraft with a constant speed propeller is in a gliding descent with the engine idling; what would be the effect of increasing the propeller pitch?
Q80. A twin-engine aircraft is available in both jet and propeller variants. The engines are mounted on the wings in the same position in both types. In the case of failure of one engine how would the engine torque effect show itself?
Q81. A twin-engine aircraft is available in both jet and propeller variants. The engines are mounted on the wings in the same position in both types. In the case of failure of one engine how would the resultant roll effect show itself?
Q82. Increasing the number of propeller blades will:
Q83. Increasing the camber on propeller blades will, if all else is the same:
Q84. Why does the blade angle of a propeller change from root to tip?
Q85. For a fixed-pitch propeller designed for cruise, the angle of attack of each blade, measured at the reference section:
Q86. The number of blades in a propeller would be increased:
Q87. The more blades a propeller has, the more power it is able to absorb. The limitation on blade number from an aerodynamic standpoint is:
Q88. What is the purpose of increasing the number of propeller blades?
Q89. What is the disadvantage of increasing the number of propeller blades?
Q90. In the alpha and beta ranges respectively the governed elements of turboprop propeller controls are as follows:
Q91. For an aircraft with a right-hand propeller, the slip-stream rotation will cause:
Q92. A reversible propeller is one that:
Q93. Asymmetric propeller blade effect is mainly induced by:
Q94. A propeller is turning to the right, seen from behind. The asymmetric thrust effect in the climb will:
Q95. A propeller is turning to the right, seen from behind. The asymmetric thrust effect is mainly induced by:
Q96. A propeller turns to the right, seen from behind. The torque effect in the take- off will:
Q97. Propeller efficiency is best described as:
Q98. Which of the following definitions of propeller parameters is correct?
Q99. During the take-off roll, what affect does torque have on an aircraft with a clockwise rotating propeller?
Q100. A propeller rotating anti-clockwise when viewed from the front, during the take-off ground roll will:
Q101. Propeller torque is caused by:
Q102. The torque reaction of a right-hand propeller will cause:
Q103. Using the diagram below of the forces affecting a propeller in flight, which arrow represents the torque moment?
Q104. Which of the following would change the magnitude of the gyroscopic precession effect of the propeller?
Q105. Gyroscopic precession of the propeller is induced by:
Q106. To counteract the effect of slip-stream on a single engined aircraft:
Q107. A reduction in blade section pitch angle towards the tip is termed :
Q108. Washout is:
Q109. The main advantage of a constant speed propeller as compared to a fixed pitch propeller is a:
Q110. An asymmetric loading (p-factor) on the propeller exists:
Q111. The blade angle of a propeller is the angle between the:
Q112. A propeller blade is twisted, so as to
Q113. The main advantage of a constant speed propeller as compared to a fixed pitch propeller is a :
Q114. What will happen to the geometrical pitch angle of a ” constant speed propeller” if the manifold pressure is increased ?
Q115. When TAS increases, the pitch angle of a constant speed propeller (RPM and MAP levers are not moved) :
Q116. When in flight, a piston engine is stopped and the propeller blade angle is near 90°, the propeller is said to be:
Q117. A pilot can actuate the feathering system by:
Q118. Fixed-pitch propellers are usually designed for maximum efficiency at :
Q119. At constant RPM with a normally aspirated engine and a fixed-pitch propeller as altitude increases, if the mixture is not leaned:
Q120. When increasing true airspeed with a constant engine RPM, the angle of attack of a fixed pitch propeller :
Q121. During take-off, the angle of attack of the blades of a fixed pitch propeller, optimised for cruise condition is:
Q122. For take-off, the correct combination of propeller pitch (1), and propeller lever position (2) at brake release is:
Q123. In modern aircraft, a pilot can actuate the feather system by :
Q124. The mechanism to change the propeller blade angle of a small piston engine aeroplane in flight is operated:
Q125. In case of engine failure during flight the blades of a constant speed propeller in a single engine aeroplane, not fitted with feathering system
Q126. Concerning a constant speed propeller of a twin engine aeroplane controlled by a single-acting pitch control unit:
Q127. The ’slipstream effect’ of a propeller is most prominent at:
Q128. When changing power on engines equipped with constant-speed propeller, engine overload is avoided by:
Q129. The blade angle of a constant-speed propeller
Q130. If the manifold pressure is increased, the blade angle of a constant speed propeller :
Q131. As a result of gyroscopic precession, it can be said that:
Correct answer is – any yawing around the normal axis results in a pitching moment.
Q132. A propeller rotating clockwise as seen from the rear, creates a spiralling slipstream that tends to rotate the aeroplane to the:
Correct answer is – left around the normal axis, and to the right around the longitudinal axis.
Q133. The reason for variations in geometric pitch (twisting) along a propeller blade is that it:
Correct answer is – permits a relatively constant angle of attack along its length when in cruising flight.
Q134. The geometric pitch of a propeller is:
Correct answer is – the distance it would move forward in one revolution if there were no slip.
Q135. Propeller ‘slip’ is:
Correct answer is – the amount by which the distance covered in one revolution falls short of the geometric pitch.
Q136. The distance a propeller actually advances in one revolution is:
Correct answer is – effective pitch.
Q137. Blade angle of a propeller is defined as the angle between the:
Correct answer is – chord line and plane of rotation.
Q138. Propeller efficiency is the:
Correct answer is – ratio of thrust horsepower to shaft horsepower.
Q139. A fixed-pitch propeller is designed for best efficiency only at a given combination of:
Correct answer is – airspeed and RPM.
Q140. Which statement is true regarding propeller efficiency? Propeller efficiency is the:
Correct answer is – ratio of thrust horsepower to shaft horsepower.
Q141. Which statement best describes the operating principle of a constant speed propeller?
Correct answer is – The propeller control regulates the engine RPM and in turn the propeller RPM.
Q142. When does asymmetric blade effect cause the aeroplane to yaw to the left?
Correct answer is – When at high angles of attack.
Q143. The left turning tendency of an aeroplane caused by asymmetric blade effect is the result of the:
Correct answer is – propeller blade descending on the right, producing more thrust than the ascending blade on the left.
Q144. With regard to gyroscopic precession, when a force is applied at a point on the rim of a spinning disc, the resultant force acts in which direction and at what point?
Correct answer is – In the same direction as the applied force, 90° ahead in the plane of rotation.
Q145. The angle of attack of a fixed pitch propeller:
Correct answer is – depends on forward speed and engine rotational speed.
Q146. Counter-rotating propellers are:
Correct answer is – two propellers driven by separate engines, rotating in opposite directions.
Q147. If engine RPM is to remain constant on an engine fitted with a variable pitch propeller, an increase in engine power requires:
Correct answer is – an increase in blade angle.