Module 8 Set-9 - DGCA MODULE

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#1. Propeller convert————- into ———–(Ref-ACK 131)

a. Thrust, torque

b. Torque, thrust

c. Thrust, power

#2. Aircraft will have weaker positive directional opposed to positive lateral stability can result in a

a. Spiral divergence

b. Directional divergence

c. Dutch roll

#3. There must be some point on the chord about which there is no change in pitching moment is called

a. Line of zero lift

b. Aerodynamic center

c. Stagnation point

#4. The ratio ofInertial to elastic force is called

a. Reynolds no

b. Euler’s no

c. Mach no

#5. On a swept wing aircraft if both wing tip loses lift simultaneously the aircraft will

a. Roll

b. Pitch nose up

c. Pitch nose down

#6. The stability of an aircraft considered during design of the aircraft (Ref-ACK 257)

a. Lateral stability

b. Inherent stability

c. Dead-beat stability

#7. In flat plate an increase of the angle of attack over the same angles causes the center of pressure to move

a. Forward

b. Backward

c. Remains same

#9. Blown & jet flaps may be a serious disadvantage in the event of

a. Diving

b. Climbing

c. Power failure

#10. The control surfaces are placed as far as possible away the_________ So as to provide sufficient leverage to alter the position of the airplane. (Ref-ACK 274)

a. Center of pressure

b. Center of gravity

c. Aerodynamic center

#11. Movement of the center of gravity during flight caused, for instance, by (Ref-ACK 149)

a. Consumption of fuel

b. Movement of passengers

c. Both a and b

#12. The value of the dynamic pressure and hence the indicated speed at which this occurs will always be the _______ whatever the height.

a. Increases

b. Decreases

c. Same

#13. Longitudinal stability is highly affected due to (Ref-ACK 259)

a. Movement of tail plane

b. Movement of center of gravity

c. Movement of center of pressure

#14. If wing loading is increasing then stalling speed will be (Ref ACK 193)

a. Increasing

b. Decreasing

c. Remains the same

#15. A laminar boundary layer over the boundary layer over the whole surface of a wing the skin friction would be reduced to about__________ of its value.

a. One - tenth

b. One - third

c. One - fourth

#16. Angle of airfoil is slightly negative will it generate lift

a. Do not generate lift

b. May be generate lift

c. None

#17. The streamline shapes which have given the least resistance at subsonic speeds have had a

a. fineness ratio

b. pressure ratio

c. aspect ratio

#18. The L/D ratio increases very rapidly up to 3 or 4 degree at which angles the lift is nearly

a. 20 times the drag

b. 24 times the drag

c. 10 times the drag

#19. In the case of aircraft nose drop thrust line is placed———- and drag line is———(Ref-ACK 149)

a. High ; low

b. High ; high

c. Low ; high

#20. If viscosity is increasing the Reynolds number will be