5802222
Description
Question 1
Question
159 Trailing edge flaps…………………….……………….landing attitude?
Answer
-
O Decrease.
-
O Increase.
-
O Do not affect,
-
O Increase or decrease depending on flap type.
Question 2
Question
160 Trailing edge flaps…………………………………….stalling angle?
Answer
-
O Decrease.
-
O Increase.
-
O Do not affect
-
O Increase or decrease depending on flap type.
Question 3
Question
161 The purpose of leading edge slats is to…………………………….?
Answer
-
O Increase stalling angle.
-
O Decreases stalling angle.
-
O Increase stalling speed,
-
O Create advanced turbulent boundary layer.
Question 4
Question
162 Leading edge slats……………………...stalling angle?
Answer
-
O increase.
-
O Decrease.
-
O Do not affect.
-
O Increase or decrease depending on weight.
Question 5
Question
163 Asymmetric flap deployment………………………………………...?
Answer
-
O Causes loss of control.
-
O Improves lift performance.
-
O Is used to prevent asymmetric yaw.
-
O Is not possible.
Question 6
Question
164 The diagram (Fig.1), includes?
Answer
-
O Split flap
-
O Double slotted plain flaps.
-
O Leading edge flaps
-
O Double slotted fowler flaps.
Question 7
Question
165 The diagram (Fig.2), includes?
Answer
-
O Slat and plain flap.
-
O Drooped leading edge and plain flap.
-
O Leading edge flap.
-
O Double slotted split flaps.
Question 8
Question
166 Flap asymmetry causes…………………………………………….?
Answer
-
O Roll and yaw.
-
O Roll.
-
O Roll, pitch and yaw.
-
O None of the above.
Question 9
Question
167 Trailing edge flap deployment………….……………………...
pitch attitude required in take-off and landing?
Answer
-
O Decreases stalling speed and stalling angle of attack.
-
O Increases stalling speed and stalling angle of attack.
-
O Decreases stalling speed and angle of incidence.
-
O Improves stability.
Question 10
Question
168 Trailing edge flap deployment……………………………………………..
pitch attitude required in take-off and landing?
Answer
-
O Decreases,
-
O Increases.
-
O Does not affect.
-
O Increases or decreases depending on weight
Question 11
Question
169 Trailing edge flap deployment………………….power required?
Answer
-
O Increases.
-
O Decreases.
-
O Does not affect.
-
O Increases or decreases depending on C of G position.
Question 12
Question
170 Deployment of flaps………………………………………………….?
Answer
-
O Decreases lateral stability.
-
O Increases longitudinal stability.
-
O Decreases longitudinal stability.
-
O Increases lateral stability.
Question 13
Question
171 Trailing edge flap deployment...................................... ?
Answer
-
O Decreases stalling angle.
-
O Increases stalling angle.
-
O Does not affect stalling angle,
-
O Increases or decreases stalling angle depending on C of G position.
Question 14
Question
172 What effect does increasing load factor have on power required at any given aircraft eweight and TAS?
Answer
-
O Increases in direct proportion to load factor.
-
O .No effect.
-
O Decreases in direct proportion to load factor,
-
O Power required is inversely proportional to load factor.
Question 15
Question
173 What effect will increasing aircraft weight have on minimum drag speed (Vmd) and speed stability,
Answer
-
O Increase, Decrease.
-
O Increase, Increase.
-
O Decrease, Increase.
-
O Decrease, Decrease.
Question 16
Question
174 What effect will lowering the landing gear have on VMD and speed stability?
Answer
-
O Decrease, Increase,
-
O Increase, Increase.
-
O Increase, Decrease.
-
O Decrease, Decrease.
Question 17
Question
175 What is the relationship between Di and Dp at speeds below VMD?
Answer
-
O Di is greater than Dp.
-
O Di is less than Dp.
-
O Di = Dp.
-
O Di = DP =DTOTAL
Question 18
Question
176 Complete the following statement.
As airspeed changes from VMD to CLMAX………………………………..increases and………………. decreases.
Answer
-
O DI, DP.
-
O DP, DI.
-
O DTOTAL DP.
-
O D TOTAL DI.
Question 19
Question
177 Which of the following definitions of Dp is the most accurate?
Answer
-
O It is made up of friction, form and interference drag,
-
O It is made up of form, friction and induced drag.
-
O It is made up of friction, induced and shock drag.
-
O It is made up of interference, shock and form drag.
Question 20
Question
178 What causes wing tip vortices?
Answer
-
O High pressure air leaking from below the wings.
-
O Pressure differences in front of and behind the wings.
-
O Spanwise flow from tip to root under the wings,
-
O Spanwise flow from root to tip above the wings.
Question 21
Question
179 Which of the following occur at Vmd?
Answer
-
O Minimum drag and greatest L/D ratio.
-
O Minimum power required and best L/D) ratio.
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O Minimum angle of attack and best rate of climb.
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O Minimum drag and greatest jet propeller aircraft range.
Question 22
Question
180 In what direction does the drag force act?
Answer
-
O Parallel but opposite to the direction of flight.
-
O Parallel to relative airflow.
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O Parallel to lift,
-
O Parallel to weight.
Question 23
Question
181 In what direction does lift act?
Answer
-
O At right angles to the flight path.
-
O Straight up.
-
O At right angles to the relative airflow.
-
O At right angles to thrust.
Question 24
Question
182 The majority of lift is produced by?
Answer
-
O Low pressure above the wing.
-
O High pressure below the wing.
-
O Increased velocity below the wing.
-
O Increased density below the wing.
Question 25
Question
183 What proportion of total drag is made up of induced drag when flying at VMD?
Answer
-
O 50%
-
O 75%
-
O 25%
-
O 100%
Question 26
Question
184 All other factors being equal, minimum drag is……………………………………………...?
Answer
-
O Proportional to weight.
-
O Constant.
-
O A function of density altitude.
-
O A function of pressure altitud
Question 27
Question
185 If air density is reduced by a factor of 4, by what factor will drag alter?
Answer
-
O Decrease by a factor of 4.
-
O Decrease by a factor of 2.
-
O Increase by a factor of 4.
-
O Decrease by a factor of 16.
Question 28
Question
186 Which of the following, causes induced drag (Di) ?
Answer
-
O Downwash of airflow over the trailing edge caused by wing tip vortices.
-
O Shock waves above and below the wing.
-
O Friction due to the air passing over the wing.
-
O Upwash of airflow over the trailing edge caused by wingtip vortices.
Question 29
Question
187 Which of the following is responsible for the creation of induced drag?
Answer
-
O Angle of attack, camber, wing area and airspeed.
-
O Pitch angle, camber, wing area and airspeed.
-
O Pitch angle, camber, wing area and angle of attack.
-
O Airspeed, wing area and pitch angle.
Question 30
Question
188 Entering ground effect causes?
Answer
-
O Downwash is reduced.
-
O Low pressure below the wings reduces lift
-
O Downwash is increased.
-
O The aircraft slows down.
Question 31
Question
189 In what way does ground effect influence induced drag?
Answer
-
O Decreases it.
-
O Increases it.
-
O No effect.
-
O Angles it aft.
Question 32
Question
191 What will be the effect of raising the undercarriage of an aircraft?
Answer
-
O Decreased profile drag and lower speed stability.
-
O Increased induced drag due to more efficient lift production.
-
O Decreased induced drag due to less efficient lift production.
-
O Increased profile drag and greater speed stability.
Question 33
Question
192 How will power required vary when leaving ground effect?
Answer
-
O increase.
-
O No change.
-
O Decrease.
-
O Decrease or increase depending on airspeed.
Question 34
Question
193 In what ways are Di and Dp proportional to V?
Answer
-
O (1/V)2 (V)2
-
O (V)3 (1/V)3
-
O Inversely.
-
O (V)2 (1/V)2
Question 35
Question
194 How does total drag vary with air density?
Answer
-
O Directly.
-
O Constant.
-
O Inversely.
-
O Conversely.
Question 36
Question
195 How does retraction of flaps affect induced drag if IAS remains constant?
Answer
-
O Decreases.
-
O Increases.
-
O Constant.
-
O Increase or decrease depending on speed.
Question 37
Question
196 ……………………………………………………….causes induced drag?
Answer
-
O The generation of lift.
-
O Angle of attack.
-
O Aspect ratio.
-
O Boundary layer separation.
Question 38
Question
197 Entering ground effect……………………………..power required?
Answer
-
O Decreases,
-
O Increases.
-
O Does not affect,
-
O Increases or decreases depending on height.
Question 39
Question
198 Increasing air temperature will......................................?
Answer
-
O Decrease lift at any given CL and TAS.
-
O Increase the gradient of the lift slope
-
O Decrease CL max.
-
O Increase profile drag.
Question 40
Question
199 Increasing humidity will………………………………………………………...?
Answer
-
O Increase required CL,
-
O Increase CL max.
-
O Decrease stalling speed,
-
O Increase profile drag.
Question 41
Question
200 Which of the following statements are true?
1. Increasing aspect ratio reduces induced drag.
2. Increasing sweep back angle reduces induced drag.
3. Increasing EAS increases induced drag.
4. Increasing CL increases induced drag.
Answer
-
O 1 and 4.
-
O 1,2 and 3.
-
O 1,3 and 4.
-
O 2,3 and 4.
Question 42
Question
201 ……………………………………………………………………………..aircraft weight will………………………………………………………………………ground effect?
Answer
-
O Increasing, increase.
-
O Increasing, decrease.
-
O Decreasing, increase.
-
O Decrease, diminish.
Question 43
Question
202 ……………………………………………………………………….landing speed at constant weight will……………………………….ground effect?
Answer
-
O Increasing,………………………………………..decrease.
-
O Increasing,………………………………………increase.
-
O Decreasing,…………………………………….stabilize,
-
O Decreasing,……………………………………decrease
Question 44
Question
203 Increasing load factor will…………………………………..Dp,………………………VMD and………………………………..speed dtability.
Answer
-
O Not affect, Increase, Decrease,
-
O Increase, Increase, Increase.
-
O Decrease, Decrease, Decrease,
-
O Not affect, Decrease, Increase
Question 45
Question
204 Why might trim tabs be employed in power assisted flying controls?
Answer
-
O To reduce control forces to zero,
-
O To enable control to be maintained following hydraulic failure.
-
O To prevent overstressing of hydraulic actuators.
-
O To provide better sability.
Question 46
Question
205 How is control mass balance achieved?
Answer
-
O By fitting weights onto or in front and above the leading edge.
-
O By fitting weight aft of the hinge.
-
O By fitting weights into the tip cap.
-
O By fitting a extra weights to the aft of fuselage.
Question 47
Question
206 In a climbing turn the ................wing is likely to stall..... ……...causing the aircraft to.. .......and yaw .......... the turn?
Answer
-
O Outer first roll out of.
-
O Outer last pitch in to.
-
O Inner first roll in to.
-
O Inner last pitch out of.
Question 48
Question
207 In a descending turn the ......... wing is likely to stall...... causing the aircraft to……
...and yaw ............'the turn?
Answer
-
O .Inner first roll in to.
-
O .Outer last pitch in to.
-
O Outer first roll out of.
-
O .Inner last pitch out of.
Question 49
Question
208 A swept............................wing is prone to..............................all due to separation of boundary layer air at the...............?
Answer
-
O Back tip tips
-
O Forward root roots
-
O Back tip roots,
-
O Forward root tips.
Question 50
Question
209 Straight wings are prone to pitch..................in low speed stall and pitch........................in high speed stall?
Answer
-
O Down up then down.
-
O Down up.
-
O Up up.
-
O d Up down then bank.
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