POWER AVAILABLE AND POWER REQUIRED – Air – DGCA Question Bank For Politics

#1. If TAS is increased from 300 Kts to 400 Kts with no change in altitude, configuration, or weight, by what percentage will power required change?

Decrease by 135%.

Decrease by 35%.

Increase by 135%.

Increase by 235%.

#2. What is the relationship between power required and TAS, as an aircraft accelerates above VMD?

Power required increases in direct proportion to TAS.

Power required increases in inverse proportion to TAS.

Power required increases in proportion to (TAS)3.

Power required increases in proportion to (TAS)2.

#3. At what % of its stalling speed must a jet aircraft fly to achieve maximum endurance for a given fuel load?

122%.

132%.

142%.

152%

#4. For a piston aircraft at constant weight, angle of attack, and configuration, what mill be the effect of Increasing altitude?

lncreased power and TAS will be required.

Increased power will be required but at the same TAS.

Lower power will be required at the same TAS.

The same power will be required but at an increased TAS.

#5. For a piston aircraft at a constant altitude, angle of attack, and configuration, what will be the effect of increasing weight?

More power will be required but at the same TAS.

More power will be required but at a higher TAS.

The same power will be required but at a higher TAS.

More power will be required but at a lower TAS.

#6. Compared with still air, when flying for maximum range into a headwind, speed should be?

Faster.

The same,

Slower.

Depends on weight.

#7. What flight condition requires least power at a given IAS?

Zero flap high altitude.

Zero flap low altitude.

30°flap low altitude.

30° flap high altitude.

#8. Maximum propeller aircraft range occurs at?

VMD

VMP

VX

VY

#9. Power required for a given IAS at 40000 feet altitude, is .......... times that required at ISA MSL?

2

4

8

16

#10. Power required is proportional to?

TAS

IAS

TAS2

TAS3

#11. Power required equals?

Drag x IAS.

Drag x CAS.

Drag x EAS.

Drag x TAS.

#12. As altitude increases, power available from a piston or turbo-prop ......... whilst that of a turbo-jet ........... ?

Increases, Increases.

Increases, Decreases.

Decreases, Decreases.

Decreases, Increases.

#13. As altitude increases, the power required curve moves ..... whilst the power available curve moves.........?

Up and right, Down.

Up and left, UP.

Down and left, UP.

Down and right, Down.

#14. As altitude increases jet aircraft excess power?

Increases at a constant rate.

Decreases at a constant rate.

Remains constant.

Decreases at a rate that decreases with increasing altitude.

#15. Doubling IAS at a given altitude multiplies power required by?

2

4

8

16

#16. Minimum power required speed is?

Less than Vs.

More than VMD.

Less than VMD.

Vx of propeller aircraft.

#17. Maximum range for a jet aircraft occurs at?

Less than Vs.

More than VMD.

Less than VMD.

VMD.

#18. Maximum excess power IAS ...... .. .. with increasing altitude?

Increases.

Decreases.

Remains constant.

Increases then decreases.

#19. Maximum excess power TAS ......... ... with increasing altitude?

Increases.

Decreases.

Remains constant.

Increases then decreases.

#20. At the absolute ceiling, excess power?

Is zero.

Is maximum.

Varies with engine type.

Varies with TAS.

#21. At the absolute ceiling, VMP and VMD?

Are the same.

Both increase.

Both decrease.

Diverge.

#22. The power available and power required curves?

Never meet.

Never cross.

Are parallel at the absolute celling.

Cross at the absolute celling.

#23. The power available and power required curves?

Cross at maximum and minimum speeds.

Never cross.

Are always parallel.

Are never parallel.

#24. In gliding flight?

The power required curves are irrelevant.

The power available curves are irrelevant.

No power is consumed.

Power consumption is always at a minimum.

#25. The best ratio of TAS to power required occurs at?

VMP

VMD.

Vx.

VY.

#26. Maximum jet endurance occurs at?

VMD

VMP

VNE

VY

#27. Decreasing weight moves the power required curve?

Down and right.

Up and right.

Up and left.

#28. VMD is point .... on the diagram right?

A

B

C

D

#29. Power required is?

Drag x IAS.

Drag x TAS.

Thrust required x TAS.

Thrust required x IAS.

#30. Excess power / Weight = ?

The sine of the maximum angle of climb.

The cosine of the maximum angle of climb.

The sine of the maximum angle of descent.

The maximum rate of climb.

#31. Moving C of G forward will?

Decrease range.

Increases range.

Decrease range only if C of G is forward of C of P.

Decrease range only if C of G is aft of C of P.

#32. If the aft C of G limit is aft of the C of P and the forward limit if forward of the C of P, then moving the C of G from its aft limit to its forward limit will?

Decrease range.

Increases range then decrease range.

Increase range.

Decrease range then increase range.

#33. Range will be maximum when?

C of G is forward of C of P.

C of G is aft of C of P.

C of G and C of P coincide.

When flying at VMD.

#34. An aircraft of weight of 120000 Ibf can achieve a climb gradient of 2.5% using maximum climb power, At what weight will it achieve a gradient of 3% if the change in excess power is ignored?

100000 Ibf.

110000 Ibf.

130000 Ibf.

95000 Ibf.

#35. An aircraft of weight 120000 Ibf can achieve a climb gradient of 2.5% using maximum climb power. What gradient will it achieve at a weight of 150008 Ibf if the change in excess power is ignored?

2%.

3%.

4%.

1.75%.

#36. If weight is increased by 25% when flying at VMD power required will increase by?

18%.

28%.

38%.

48%.

#37. Thrust equals drag when?

Descending at constant IAS.

Flying in level flight at constant IAS.

Climbing at constant TAS.

None of the above.

#38. Maintaining altitude after an increase in mass without changing angle of attack requires?

Increased power and airspeed.

Decreased power and airspeed.

Increased power and decreased airspeed.

Decreased power and increased airspeed.

#39. Two identical turbojet aircraft flying at the same airspeed and altitude have the sime SFC. Aircraft A weighs 200000 Kg and consumes fuel at a rate of 5000 Kg/hr. If aircraft B weighs 250000 Kg what will be its fuel consumption?

5250 Kg/hr.

6250 Kg/hr.

8250 Kg/hr.

9812 Kg/hr.

#40. VIMP for a turboprop is?

Lower than Vx.

Lowest fuel consumption speed.

Higher than VY.

Lower than V2.

#41. VIMP for a turboprop is?

Higher than Vx.

Vx

Higher than VY.

Lower than V2.

#42. If service celling is 12000 ft at a weight of 50000 Kg, at a weight of 75000 Kg it will be?

Higher.

The same.

Lower.

Higher or lower depending on engine type.

#43. Increasing altitude causes the power required curve to?

Move to the left and upwards.

Move to the left and downwards.

Move to the right and upwards.

Move to the right and downwards.

#44. Decelerating at the back of the drag curve?

B

C

D

#51. As speed decreases below VMP?

Drag and power required decrease.

Drag and power required increase

Drag decreases and power required increases.

Drag increases and power required decreases.

#52. As speed increases above VMP?

Drag and power required decrease

Power required increases, whilst drag decreases then increases.

Drag decreases and power required increases.

#53. As speed changes from CL MAX to VMO?

Both drag and power required decrease then increases at the same rate.

Both drag and power required decrease then increase but at different rates.

Drag increases and power required decreases.

Drag decreases and power required increases.

#54. If air density at 40000 feet is 1/4 of that at sea level, how will power required change when climbing at constant IAS from MSL to 40000 feet?

Remain constant.

Increase by a factor of 2.

Increase by a factor of 4.

Increase by a factor of 8.

#55. If air density at 40000 feet is % of that at sea level, how will power required change when climbing at constant TAS from MSL to 40000 feet?

Remain constant

Decrease provided IAS remains above VMD.

Decrease provided IAS remains below VMO.

Decrease provided IAS remains above VMP.

#56. If power lever setting is maintained at a constant value when climbing at Vx?

C

D

#69. If weight is increased by 50% at VMD power required at the same speed will increase by?

32.5%.

42.5%.

52.5%.

62.5%.

#70. If weight is increased by 50% at a speed considerably higher than VMD power required will be increased by?

42.5%.

Less than 62.5%.

62.5%.

More than 62.5%.

#71. If weight is increased by 50% at a speed considerably lower than VMD power required will?

Increase by more than 62.5%.

Increase by more than 62.5% only if speed is lower than VMP.

Decrease by more than 62.5% only if speed is lower than VMP.

#72. A multi engine aircraft is flying at its absolute ceiling when it suffers a single engine failure. In order to continue flying at that altitude it must?

Reduce speed.

Increase speed.

Reduce weight.

lncrease power setting.

#73. A multi engine aircraft is flying at its absolute ceiling when it suffers a single engine failure. In order to continue flying at the same speed it must?

Climb.

Descend.

Accelerate.

Decelerate.

#74. An,aircraft weighing SOW0 Ibf is flying at its absolute ceiling when the pilot activates the reheat system. If reheat produces an additional 5000 Ibf of thrust it will enable the aircraft to?

Climb at a gradient of 10%.

Climb at an angle of approximately 5.7 degrees.

Climb at a rate of 1000 feet per minute.

Climb at a gradient of 10% and at an angle of approximately 5.7 degrees.

#75. As altitude increases the power required to fly at any given IAS?

Increases because the drag force increases with altitude.

Decreases because the drag force decreases wit altitude.

Decreases because the drag force remains constant while TAS decreases with altitude.

Increases because the drag force remains constant while TAS increases with altitude.

Dgca Question Bank For Pilots

Results

#1. If TAS is increased from 300 Kts to 400 Kts with no change in altitude, configuration, or weight, by what percentage will power required change?

#2. What is the relationship between power required and TAS, as an aircraft accelerates above VMD?

#3. At what % of its stalling speed must a jet aircraft fly to achieve maximum endurance for a given fuel load?

#4. For a piston aircraft at constant weight, angle of attack, and configuration, what mill be the effect of Increasing altitude?

#5. For a piston aircraft at a constant altitude, angle of attack, and configuration, what will be the effect of increasing weight?

#6. Compared with still air, when flying for maximum range into a headwind, speed should be?

#7. What flight condition requires least power at a given IAS?

#8. Maximum propeller aircraft range occurs at?

#9. Power required for a given IAS at 40000 feet altitude, is .......... times that required at ISA MSL?

#10. Power required is proportional to?

#11. Power required equals?

#12. As altitude increases, power available from a piston or turbo-prop ......... whilst that of a turbo-jet ........... ?

#13. As altitude increases, the power required curve moves ..... whilst the power available curve moves.........?

#14. As altitude increases jet aircraft excess power?

#15. Doubling IAS at a given altitude multiplies power required by?

#16. Minimum power required speed is?

#17. Maximum range for a jet aircraft occurs at?

#18. Maximum excess power IAS ...... .. .. with increasing altitude?

#19. Maximum excess power TAS ......... ... with increasing altitude?

#20. At the absolute ceiling, excess power?

#21. At the absolute ceiling, VMP and VMD?

#22. The power available and power required curves?

#23. The power available and power required curves?

#24. In gliding flight?

#25. The best ratio of TAS to power required occurs at?

#26. Maximum jet endurance occurs at?

#27. Decreasing weight moves the power required curve?

#28. VMD is point .... on the diagram right?

#29. Power required is?

#30. Excess power / Weight = ?

#31. Moving C of G forward will?

#32. If the aft C of G limit is aft of the C of P and the forward limit if forward of the C of P, then moving the C of G from its aft limit to its forward limit will?

#33. Range will be maximum when?

#34. An aircraft of weight of 120000 Ibf can achieve a climb gradient of 2.5% using maximum climb power, At what weight will it achieve a gradient of 3% if the change in excess power is ignored?

#35. An aircraft of weight 120000 Ibf can achieve a climb gradient of 2.5% using maximum climb power. What gradient will it achieve at a weight of 150008 Ibf if the change in excess power is ignored?

#36. If weight is increased by 25% when flying at VMD power required will increase by?

#37. Thrust equals drag when?

#38. Maintaining altitude after an increase in mass without changing angle of attack requires?

#39. Two identical turbojet aircraft flying at the same airspeed and altitude have the sime SFC. Aircraft A weighs 200000 Kg and consumes fuel at a rate of 5000 Kg/hr. If aircraft B weighs 250000 Kg what will be its fuel consumption?

#40. VIMP for a turboprop is?

#41. VIMP for a turboprop is?

#42. If service celling is 12000 ft at a weight of 50000 Kg, at a weight of 75000 Kg it will be?

#43. Increasing altitude causes the power required curve to?

#44. Decelerating at the back of the drag curve?

#45. A propeller aircraft is inherently ....... speed stable than a jet because its thrust . . . . . . with increasing airspeed?

#46. This diagram represents?

#47. This diagram represents?

#48. VMP is most probably at point .. on the diagram?

#49. Which point on the diagram best represents Vx for a propeller aircraft?

#50. Which point on the diagram best represents VY for a propeller aircraft?

#51. As speed decreases below VMP?

#52. As speed increases above VMP?

#53. As speed changes from CL MAX to VMO?

#54. If air density at 40000 feet is 1/4 of that at sea level, how will power required change when climbing at constant IAS from MSL to 40000 feet?

#55. If air density at 40000 feet is % of that at sea level, how will power required change when climbing at constant TAS from MSL to 40000 feet?

#56. If power lever setting is maintained at a constant value when climbing at Vx?

#57. If power lever setting is maintained at a constant value when climbing at VY?

#58. This diagram represents?

#59. This diagram represents?

#60. This diagram represents?

#61. Jet power available at high altitude is indicated by line ... on this diagram?

#62. Propeller power available at high altitude is indicated by line ... on this diagram?

#63. Jet power available at low altitude is indicated by line ... on this diagram?

#64. Propeller power available at low altitude is A indicated by line ... on this diagram?

#65. Propeller thrust available at high altitude is indicated by the line .. on this diagram?

#66. Propeller thrust available at low altitude is indicated by the line .. on this diagram?

#67. Jet thrust available at high altitude is indicated by the line .. on this diagram?

#68. Jet thrust available at low altitude is I indicated by the line .. on this diagram?

#69. If weight is increased by 50% at VMD power required at the same speed will increase by?

#70. If weight is increased by 50% at a speed considerably higher than VMD power required will be increased by?

#71. If weight is increased by 50% at a speed considerably lower than VMD power required will?

#72. A multi engine aircraft is flying at its absolute ceiling when it suffers a single engine failure. In order to continue flying at that altitude it must?

#73. A multi engine aircraft is flying at its absolute ceiling when it suffers a single engine failure. In order to continue flying at the same speed it must?

#74. An,aircraft weighing SOW0 Ibf is flying at its absolute ceiling when the pilot activates the reheat system. If reheat produces an additional 5000 Ibf of thrust it will enable the aircraft to?

#75. As altitude increases the power required to fly at any given IAS?