Module 8 Set 3

 

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#1. AT STALLING ANGLE, THE C OF P

MOVES FORWARD TOWARDS LE

MOVES BACKWARD TOWARDS TE

MOVES LOWER SIDE OF THE LE

NONE

#2. AT HIGHER ALTITUDE, TAS

LESS THAN IAS

MORE THAN IAS

EQUAL TO IAS

#3. IN CLIMBING TURN, ROLLING ________

INWARDS

OUTWARDS

EITHER OF THE ABOVE

#4. ________ INCREASES, INDUCED DRAG DECREASES

ASPECT RATIO

WING SPAN

FINENESS RATIO

#5. WHICH OF THE FOLLOWING PROPERTY AFFECTS THE AIRCRAFT PERFORMANCE?

TEMP..

PRESSURE

DENSITY

PRESSURE ONLY

#6. PITCHING ONLY IS CONTROLLED BY _______

RUDDER

ELEVATOR

AILERON

#7. WHICH OF THE FOLLOWING IS AUTOMATICALLY ACTIVATED WHEN CONTROL IS FAILED ?

STICK SHAKER

STICK PUSHER

TRACTOR

#8. WHEN LIFT GENERATED THEN __________ IS PRODUCED.

FORM DRAG

PARASITE DRAG

INDUCED DRAG

#9. WHICH OF THE FOLLOWING IS CONTRIBUTED IN LONGITUDINAL STABILITY ?

VERTCAL FIN

WING

HULL

#10. STICK FIXED MEANS ________________________

ELEVATOR ARE HELD IN THEIR NEUTRAL POSITION W.R.T TAIL PLAIN

RELEASE THE CONTROL COLUMN AND ALLOW THE ELEVATOR TO TAKE UP THEIR OWN POSITION

EITHER OF THE ABOVE

#11. IF THE NOSE OF THE PLANE IS DOWN, THEN GLIDING IS ________

FLATTER

STEEPER

EITHER OF THE ABOVE

#12. COEFFICIENT OF VISCOSITY IS___________

RATIO OF VISCOUS STRESS TO VELOCITY

RATIO OF VISCOUS STRESS TO VELOCITY GRADIENT

RATIO OF VELOCITY TO VISCOUS GRADIENT

#13. WHICH OF THE FOLLOWING STABILITY IS VERY DIFFICULT FOR ACHIEVING ?

DEAD BIT STABILITY

DYNAMIC STABILITY

NEGATIVE STABILITY

#14. WHEN THE AIRCRAFT MOVE FORWARD DISTANCE IN UNIT WEIGHT OF FUEL THEN

ENDURANCE RANGE

SPECIFIC AIR RANGE

SPECIFIC WEIGHT RANGE

#15. APPLICABLE NEWTONS LAWS OF AIR

1 & 2

1, 2 & 3

ONLY 2 & 3

#16. IN STRAIGHT AND LEVEL FLIGHT _____

NEWTONS FIRST LAW

AS IN A & UNIFORM VELOCITY

AS IN B & LIFT EQUALS WEIGHT

#17. AS THE ALTITUDE INCREASES, COEFFICIENT OF VISCOSITY _______

DECREASES

AS IN (A) UP TO TROPOPAUSE

AS IN (B) UP TO STRATOPAUSE

AS IN (A) & CONSTANT IN STRATOPAUSE

#18. SWEEP BACK ANGLE EFFECTS

LONGITUDINAL STABILITY

LATERAL STABILITY

DIRECTIONAL STABILITY

#19. IN DELTA WING A/C, LIFT ______

INCREASES WITH INCREASE IN AOA

DECREASES WITH DECREASE IN AOA

NEITHER INCREASE NOR DECREASE

#20. LONGITUDINAL STABILITY IS DUE TO

PITCHING MOMENT ON FUSELAGE

CHANGE IN AS OF TAIL PLANE

MOMENT OF CP

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