THEORY OF FLIGHT QUE 101 TO 150 FOR EASA AND DGCA EXAM.

101. The upper part of the wing in comparison to the lower
# a) develops more lift    b) develops the same lift    c) develops less lift
102. What effect would a forward CG have on an aircraft on landing?
# a) Increase stalling speed    b) No effect on landing    c) Reduce stalling speed
103. QNH refers to
a) Quite near horizon   b) setting the altimeter to zero    
# c) setting the mean sea level atmospheric pressure so an altimeter reads the aerodrome altitude above mean sea level
104. QNE refers to
# a) Setting an altimeter to read aerodrome altitude above sea level    b) Quite new equipment
c) setting the mean sea level atmospheric pressure in accordance with ICAO standard atmosphere i.e. 1013 millibars
105. An aspect ratio of 8 would mean
# a) span 64, mean chord 8    b) mean chord 64 , span 8   c) span squared 64 ,chord 8
106. If an aircraft in level flight loses engine power it will
a) pitch nose up    # b) pitch nose down    c) not change pitch without drag increasing
107. QFE is
a) sea level pressure    # b) airfield pressure    c) difference between sea level and airfield pressure
108. The lift /drag ratio at stall
a) increases     # b) decreases     c) is unchanged
109. On a straight unswept wing, stall occurs at
# a) the thick portion at the wing root       b) the thick portion at the wing tip    c) the thin portion at the wing tip
110. During a climb from a dive
# a) the thrust required is greater than required for level flight
b) the thrust required is lower than for level flight
c) the thrust required is the same as for level flight
111. When power is off, the aircraft will pitch
# a) nose down     b) nose up     c) trim level
112. Angle of attack on a down going wing in a roll
# a) increases    b) decreases    c) unaffected

113. For any given speed, a decrease in aircraft weight, the induced drag will
a) increase    # b) decrease    c) remain the same
114. The amount of lift generated by a wing is
# a) greatest at the root    b) greatest at the tip    c) constant along the span
115. Induced Drag is
a) greatest towards the wing root and downwash is greatest at the tip
b) greatest towards the wing tip and downwash is greatest towards the root
# c) greatest towards the tip and downwash decreases from tip to root
116. Induced Drag is
a) equal to profile drag at stalling angle    # b) equal to profile drag at Vmd   c) never equal to profile drag
117. With an increase in aircraft weight
a) Vmd will be at the same speed    b) Vmd will be at a lower speed   # c) Vmd will be at a higher speed
118. For a given IAS an increase in altitude will result in
a) no change a) increase
# b) decrease
c) remain the same
# a) greatest at the root
b) greatest at the tip
c) constant along the span
a) greatest towards the wing root and downwash is greatest at the tip
b) greatest towards the wing tip and downwash is greatest towards the root
# c) greatest towards the tip and downwash decreases from tip to root
a) equal to profile drag at stalling angle
# b) equal to profile drag at Vmd
c) never equal to profile drag
a) Vmd will be at the same speed
b) Vmd will be at a lower speed
# c) Vmd will be at a higher speed
a) in the value of induced drag
# b) an increase in induced drag
c) an increase in profile drag
119. As the angle of attack of a wing is increased in level flight
a) the Cof G moves aft and the Cof P forward
# b) the Cof P and transition point move forward
c) the Cof P moves forward and the stagnation point aft over the upper surface
120. Stall inducers may be fitted to a wing
a) at the tip to cause the root to stall first
b) at the root to cause the tip to stall first
# c) at the root to cause the root to stall first
121. With increasing altitude pressure decreases and
a) temperature decreases at the same rate as pressure reduces
# b) temperature decreases but at a lower rate than pressure reduces
c) temperature remains constant to 8000 ft
122. The Centre of Pressure is
# a) the point on the chord line at which the resultant lift force may be said to act
b) the point of maximum pressure on the under surface of the wing
c) the centre of gravity of the wing
123. If the angle of attack is increased the Centre of Pressure will
# a) move forward    b) move rearward    c) remain stationary
124. The optimum angle of attack of an aerofoil is the angle at which
a) the aerofoil produces maximum lift    b) the aerofoil produces zero lift
# c) the highest lift/drag ratio is produced
125. A high aspect ratio wing has a
a) increased induced drag    # b) decreased induced drag    c) decreased skin friction drag
126. Minimum total drag of an aircraft occurs
a) at the stalling speed    # b) when profile drag equals induced drag    c) when induced drag is least
127. If the weight of an aircraft is increased, the induced drag at a given speed
# a) will increase   b) will decrease   c) will remain the same
128. The transition point on a wing is the point where
a) the flow separates from the wing surface
# b) the boundary layer flow changes from laminar to turbulent
c) the flow divides to pass above and below the wing
129. The boundary layer of a body in a moving airstream is
# a) a thin layer of air over the surface where the air is stationary
b) a layer of separated flow where the air is turbulent
c) a layer of air over the surface where the airspeed is changing from free stream speed to zero speed
130. A laminar boundary layer will produce
a) more skin friction drag than a turbulent one
# b) less skin friction drag than a turbulent one
c) the same skin friction drag as a turbulent one
131. Longitudinal stability is given by
a) the fin    b) the wing dihedral    # c) the horizontal tailplane
132. Lateral stability is given by
a) the ailerons    # b) the wing dihedral    c) the horizontal tailplane
133. Stability about the lateral axis is given by
a) wing dihedral    # b) the horizontal tailplane    c) the ailerons
134. Sweepback of the wings will
# a) increase lateral stability    b) decrease lateral stability    c) not affect the lateral stability
135. Dutch Roll is
# a) a combined rolling and yawing motion    b) a type of slow roll   c) primarily a pitching instability
136. A high wing position gives
# a) more lateral stability than a low wing
b) less lateral stability than a low wing
c) the same lateral stability as a low wing
137. On an aircraft in an unpowered steady speed descent
a) the lift equals the weight    b) the weight equals the drag    # c) the weight equals the resultant of the lift and drag
138. When an aircraft rolls to enter a turn and power is not increased
a) the lift equals the weight    b) the lift is greater than the weight    # c) the lift is less than the weight
139. The boundary layer is
a) thickest at the leading edge    # b) thickest at the trailing edge    c) constant thickness from leading to trailing edges
140. The amount of thrust produced by a jet engine or a propeller can be calculated using
a) Newton’s 1st law    # b) Newton’s 2nd law    c) Newton’s 3rd law
141. An engine which produces an efflux of high speed will be
a) more efficient    # b) less efficient    c) speed of efflux has no affect on the engine efficiency
142. When an aircraft with a Cof G forward of the Cof P rolls, the nose of the aircraft will
a) stay level   b) rise    # c) drop
143. Directional stability may be increased with
a) pitch dampers    b) horn balance     # c) yaw dampers
144. Lateral stability may be increased with
# a) increased lateral dihedral    b) increased lateral anhedral     c) increased longitudinal dihedral
145. Longitudinal stability is increased if the
a) CP moves forward of the CG     b) Thrust acts on a line below the total drag    # c) CG is forward of the CP
146. Wing loading is calculated by weight
# a) divided by gross wing area    b) divided by lift    c) multiplied by gross wing area
147. Induced drag is
# a) inversely proportional to the square of speed   b) proportional to speed    c) nothing to do with speed
148. In a bank, the weight is
a) increased    b) decreased     # c) the same
149. L/D ratio is
a) higher at supersonic cruise speed    # b) higher at sub sonic speed    c) the same
150. The power required at low altitude for a given IAS is

# a) the same as at high altitude    b) higher    c) lower

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