CLIMBING FLIGHT – Air – DGCA Question Bank For Politics

#1. What speed is required to achieve maximum endurance in a piston engine powered and jet engine powered aircraft respectively?

VMD VMP

VMP VMD

VMO VMP

VMP VMO

#2. Select the appropriate words to complete the following statement. Fuel flow in a piston engine aircraft is proportional to .......... whilst that in a jet powered aircraft is proportional to ......... Thrust output of a jet engine .................. with increasing airspeed whilst that of a piston engine ................ 1. Is approximately constant 2. Thrust 3. Reduces rapidly 4. Power 5. RPM

5,2,1,3.

4,2,3,1.

4,2,1,3.

2,4,3,1.

#3. Select the correct words to complete the following statement. To achieve the maximum possible glide range it is necessary to fly at ........... This is achieved by flying the aircraft in a .................... condition and at .........?

BEST L:D RATIO 20° FLAPS VMP

BEST L²:D RATIO FLAPS UP VMD

BEST L:D RATIO FLAPS UP VMD

BEST L²:D RATIO FLAPS UP VMP

#4. What speed is required to achieve maximum angle of climb in a jet aircraft and a piston aircraft respectively and for what purpose might this be required?

VMD Minimum safe speed Obstacle clearance after take-off.

VMP Minimum safe speed Obstacle clearance after take-off.

Minimum safe speed VMD Gain height rapidly.

VMD Minimum safe speed Gain height rapidly.

#5. What is the effect of increasing altitude on best rate of climb IAS and best climb TAS respectively?

Increases Decreases

Constant Increases

Decreases Constant

Decreases Increases

#6. What happens to the range between minimum and maximum flight speeds for a subsonic aircraft as altitude increases?

It increases.

It decreases.

It remains constant.

It decreases then increases.

#7. Select the appropriate words to complete the following statement. Thrust horsepower output of a propeller aircraft ...... with increasing airspeed whilst that of a jet ... 1. Is approximately constant. 2. Is unchanged. 3. Increases rapidly then decreases rapidly. 4. Reduces slowly. 5. increases approximately linearly.

4, 1.

5, 2.

4, 2.

3, 5.

#8. When flying at VMD an aircraft has a C1, of 0.45 and a CD of 0.0225. If its engines fail when flying at 36000 feet what will be its maximum glide range?

100 nm.

200 nm.

120 nm.

175 nm.

#9. When flying at VMD an aircraft weighing 400000 Ibf has a CL of 0.45 and a CD of 0.0225. If its engines fail when flying at 36000 feet what will be its maximum glide range if the pilot immediately dumps 100000 lbf of fuel? What effect will the reduced weight have on VMD?

100 nm Reduce VMD by 25%.

200nm Increase VMD by 25%.

120nm No change in VMD

120nm Reduce VMD.

#10. What is the available rate of climb at service ceiling for a piston and jet aircraft respectively?

500 fpm 100 fpm.

100 fpm 500 fpm.

50 fpm 100 fpm.

250 fpm 500 fpm.

#11. What speed is required to achieve best rate of climb in a piston and jet aircraft respectively?

VMD VMP.

VMP VMD.

Between VMP and VMD Between VMD and VNE

Greater than VMD Less than VNE.

#12. How is the absolute ceiling indicated on a power available / power required graph for a piston and jet aircraft respectively?

The power available curve will be tangential to the power required curve.

The distance between power available and power required will be just sufficient to give rates of climb of 100 fpm and 500 fpm respectively.

For a piston aircraft the power available curve will be tangential to the power required curve. A thrust available / thrust required curve must be used for a jet aircraft.

At VMD and VMP respectively.

#13. What will be the effect of a headwind on glide range and glide angle respectively?

Decrease Decrease.

No effect Increase.

Decrease Increase.

Increase No effect.

#14. What will be the effect of a tailwind on glide range and rate of descent?

Increase Decrease.

No effect Increase.

Decrease Increase.

Increase No effect

#15. Which of the following best describes the effect of flap deployment?

Increased lift at any given speed, reduced L;D ratio, increased take-off speed and landing speeds, increased angle of climb.

Increased lift at any given speed, increased L;D ratio, reduced take-off speed and landing speeds, reduced angle of climb.

Increased lift at any given speed, reduced L;D ratio, reduced take-off speed and landing speeds, reduced angle of climb.

Increased lift at any given speed, reduced L;D ratio, increased take-off speed and landing speeds, no effect on angle of climb.

#16. Best endurance for a piston aircraft is achieved at VMP, whilst that for a jet aircraft is achieved at (VMD) Why is this so?

Fuel consumption in a piston aircraft is proportional to power output, whereas that of a jet aircraft is proportional to thrust and hence drag.

Fuel consumption in a piston aircraft is proportional to rpm, whereas that of a jet aircraft is proportional to power and hence drag.

Fuel consumption in a piston aircraft is proportional to thrust, whereas that of a jet aircraft is proportional to power and hence drag.

Fuel consumption in a piston aircraft is proportional to power output, whereas that of a jet aircraft is proportional to rpm.

#17. Which of the following best describes the effect of increasing altitude on maximum rate of climb?

Both power available and power required increase with increasing altitude but the gap between them narrows so rate of climb reduces.

Botli power available and power required decrease with altitude but the gap between them narrows so rate of climb reduces.

Power available increases with altitude whilst power required reduces so the gap between them and hence rate of climb increases.

Power available reduces with altitude whilst power required increases so the gap between them and hence rate of climb decreases.

#18. Which of the following best describes the manner in which best climb speed varies with altitude?

Best climb EAS increases whilst best climb TAS reduces with increasing altitude for both piston and jet aircraft. The effect on TAS is of the same magnitude in both cases.

Best climb EAS and best climb TAS both increase with increasing altitude for both piston and jet aircraft. The effect on TAS is greater for a piston than for a jet.

Best climb EAS and TAS both decrease with increasing altitude for both piston and jet aircraft. The effect on TAS is greater for a jet than for a piston.

Best climb EAS reduces whilst best climb TAS increases with increasing altitude for both piston and jet aircraft. The effect on TAS is greater for a piston than for a jet.

#19. How will a headwind and a tailwind respectively affect best range glide speed?

Decrease Increase

Decrease Decrease

Increase Decrease

Increase Increase

#20. If an aircraft enters a banked turn whilst climbing to cruising altitude what effect will this have on rate of climb at constant power setting?

Climbing and turning occur in different planes and hence are not related, so rate of climb will remain constant regardless of bank angle.

Banking will increase load factor and hence induced drag. This will reduce the rate of climb.

Although banking will increase load factor and hence induced drag, rate of climb depends only on excess thrust. Rate of climb will therefore remain unchanged.

Banking will reduce the climb gradient, so more power will be available to increase rate of climb.

#21. Select the appropriate words to complete the following statement. Fuel flow in a piston engine aircraft is proportional to .......... whilst that in a jet powered aircraft is directly proportional to ......... Thrust available from a jet engine .................. with increasing airspeed whilst that of a piston engine ................ 1. Is approximately constant 2. Thrust 3. Reduces rapidly 4. Power 5. Increases approximately linearly

5, 2, 1, 5.

4, 2, 1, 3.

4, 2, 5, 3.

2, 4, 5, 1.

#22. An aircraft weighing 200000 Ibf has a maximum excess power available of 1500 Thrust Horse Power. What will be its maximum rate of climb?

512 fpm.

753 fpm.

248 fpm.

358 fpm.

#23. An aircraft weighing 50000 lbf requires a thrust of 20000 Ibf when flying straight and level at 250 Kts IAS. What will be its maximum angle of climb at this speed assuming its maximum thrust at this speed is 40000 lbf and the total drag force does not change during the climb?

45.6 Degrees.

20.6 Degrees.

23.6 Degrees.

12.6 Degrees.

#24. In tlie climb described in question 23 what will be the lift force generated by the aircraft?

50000 lbf.

35825 Ibf.

45825 lbf.

25825 Ibf.

#25. An aircraft weighing 50000 Ibf requires a thrust of 20000 Ibf when flying straight and level at 250 Kts IAS. How many Thrust Horse Power will it be developing when flying straight and level at this speed? (Assume 1 nm = 6000 ft)

20151

15151.

17151.

19151

#26. Which of the following describes the method of calculating the thrust horsk power being developed by an aircraft in unaccelerated straight and level flight? 1. Convert EAS into feet per minute, multiply by total drag in Ibf then divide by 33000 ft lbflmin. 2. Convert TAS into feet per second, multiply by total drag in Ibf then divide by 550 ft Ibflsec. 3. Convert EAS into feet per second, multiply by total drag in Ibf then divide by 550 ft Ibflsec. 4. Convert TAS into feet per minute, multiply by total drag in Ibf then divide by 33000 ft Ibf lmin.

1 only.

3 only.

2 and 4.

1 and 3.

#27. An aircraft weighing 50000 Ibf requires a thrust of 20000 Ibf when flying straight and level at 250 Kts IAS. If it were to climb to 40000 ft what would be its power available in comparison to that at ISA msl?

1/4

1/3

1/2

1/5

#28. What would be the effect of sweeping back the wings of a variable geometry aircraft in gliding flight?

Profile drag would reduce unless glide angle was reduced.

Induced drag would increase unless glide angle was increased.

Glide range and rate of descent would be increased.

Glide range and rate of descent would be decreased.

#29. How is maximum rate of emergency descent achieved in a high speed jet aircraft?

Pitch down, retract flaps, spoilers and undercarriage and increase thrust,

Deploy spoilers, reduce thrust to idle, use pitch to maintain speed within limits

Deploy high lift device, retract undercarriage and spoilers. Increase thrust to maximum, pitch 45.degrees nose dcwn.

Thrust to idle, increase pitch to stalling angle, maintain nose up attitude to hold aircraft in the stall.

#30. What do points A and B represent on the whole aircraft polar diagram right?

Best L;D ratio Minimum drag.

Minimum drag Minimum power.

Best L:D ratio Stalling.

Stalling Best L:D ratio.

#31. An aircraft weighing 50000 Ibf is able to achieve a maximum rate of climb of 1500 ft / min when climbing at 250 Kts TAS. How much Excess Power will be required to achieve this rate of climb?

45000000 ft lbf / min.

55000000 ft lbf / min.

6500d000 ft Ibf / min.

75000000 ft lbf / min.

#32. An aircraft weighing 50000 Ibf is able to achieve a maximum rate of climb of 1500 ft / min when climbing at 250 Kts TAS. What will be the maximum all up weight at which it can achieve a 5% climb gradient at this speed assuming its power available and total drag do not change during the climb?

40000 Ibf.

50000 lbf.

60000 Ibf.

70000 Ibf

#33. Increased weight reduces the rate of climb and climb gradient but?

Vx increases and Vy decreases.

Vx and Vy increase.

Vx and Vy decrease.

Vx decreases and Vy increases.

#34. Best climb gradient is achieved by flying at approximately?

1.1 Vs.

1.2 Vs.

Best CL² : CD

BestCL:CD.

#35. Absolute ceiling occurs when?

ROC is 300 ft/min.

ROC is 750 ft/min.

For a jet ROC is 100 ft/min and 500 ft/min for a propeller aircraft.

ROC is zero for both jets and propeller aircraft.

#36. What airspeed will produces the greatest glide endurance?

VMP which is higher than VMD.

VMP which is lower than VMDs

VMD.

VMp or VMD depending on engine type.

#37. What factors determine maximum glide range?

Wind, CL :CD ratio and weight.

Wind, CL:CD ratio and height.

Wind, Speed and weight.

Wind, CL:CD and altitude.

#38. What are VMCAa nd VMDR?

Maximum and minimum speeds for gliding.

minimum and maximum speeds for gliding.

Speed for shallowest glide path and speed for lowest rate of descent.

Speed for maximum glide range and speed for minimum glide range.

#39. How do VMGA and VMDR compare?

VMGA is greater than VMDR.

VMGA is less than VMDR.

VMGA is the same as VMDR.

Depends on aspect ratio.

#40. Which of the following is equal to lift in a steady climb or descent?

W Cos angle of climb or descent.

W Sin angle of climb or descent.

W Tan angle of climb or descent.

None of the above.

#41. What proportion of thrust is employed in supporting the weight of an aircraft in a steady climb?

W Sin angle of climb.

W Cos.angle of climb.

W Tan angle of climb.

None of the above.

#42. What provides maximum glide range?

Strong headwind.

Light headwind.

Strong tailwind.

Light tailwind.

#43. What would give maximum glide range in a headwind?

Flying faster than VMD.

Flying slower than VMP.

Flying slower than VMD.

Flying faster than VMp.

#44. What would give maximum glide range in a tailwind?

Flying faster than VMB

Flying slower than VMD

Flying faster than VMp

Flying slower than Vs.

#45. Which of the points on the CL:CD polar would give maximum glide range?

A

B

C

D

#46. In a steady climb?

Lift is less than weight and thrust is less than drag

Lift is less than drag and weight is less than thrust.

Weight is less than lift and drag is more than thrust.

Weight is more than lift and drag is less than thrust.

#47. What is the speed for minimum sink rate?

VMSR.

VMD.

VMP.

VNE.

#48. What flap position would give maximum glide range?

Maxº.

Minº.

25º.

40º.

#49. What speed gives best angle of climb in a jet aircraft?

VMP.

VMD.

VMCL.

VMCA.

#50. Which of the following occur at VMD? 1. L:D Max. 2. Max jet endurance. 3. ax prop range. 4. Max jet climb angle. 5. Max glide range all types.

1,2,3.

2,3,4.

3,4,5.

All of the above.

#51. What will be the effect of an increase in weight? 1. VMD will increase. 2. Glide range will decrease. 3. Glide angle will increase. 4. Glide range and angle will be unaffected.

1,2,3.

2,3,4.

None of the above.

1,4.

#52. In what direction does lift act in a steady climb?

Upwards.

Vertically.

At right angles to the flight path.

None of the above.

#53. What is the absolute ceiling of an aircraft? 1. The altitude where the low speed and high speed stall lines cross. 2. The altitude at which power required is equal to power available. 3. The altitude at which thrust available is equal to drag. 4. The altitude at which rate of climb is zero.

1,2,3.

2,3,4.

None of the above.

All of the above.

#54. Increasing aircraft weight. .. .... . ..glide speed and... .... rate of descent?

Increases, Decreases.

Increases, Increases.

Decreases, Decreases.

Decreases, Increases.

#55. To descend at constant glide angle and IAS, the pitch attitude must.. .. .......?

Increase.

Decrease.

Increase then decrease.

Remain constant.

#56. For a constant mach number descent, gradient must ...... ?

Decrease.

Increase.

Increase then decrease.

Remain constant.

#57. For a constant IAS descent, gradient must ...... ?

Decrease.

Increase.

Increase then decrease.

Remain constant.

#58. A headwind in a constant mach number climb will ............ angle of climb?

Decrease.

Increase.

Not affect.

Increase or decrease depending on mach number:

#59. For maximum glide range, TAS must ..... ?

Decrease in a headwind.

Decrease in a tailwind.

Increase in a tailwind.

Remain constant.

#60. To descend at constant IAS the ............m ust be ..........?

pitch down, Increased. ..

Pitch down, Maintained constant.

Pitch up, Increased.

pitch up, Decrease.

#61. Best cHtnb angle is achieved at.............. ?

VMP

VMD.

Vx.

Vy.

#62. Maximum rate of climb occurs at ........... speed?

Maximum excess thrust.

Minimum drag.

Minimum thrust.

Maximum excess power.

#63. Maximum glide range is achieved at. ...........?

CL4 : CD MAX.

CL3 : CD MAX.

CL : CD MAX.

CL2 : CD MAX.

#64. Load factor in a steady climb will be.... ... ?

1.

More than 1

Less than 1.

More or less than 1 depending on climb angle.

#65. Lift in a steady climb is equal to ........ ?

Thrust.

Weight.

W Cos angle of climb.

W Sin angle of climb

#66. The correct procedure for an emergency descent is?

Maximise drag, minimise thrust, push the nose hard down.

Minimise drag, maximise thrust, push the nose hard down.

Maximise drag, minimise thrust, control speed with pitch attitude.

Maximise drag, minimise thrust, bank steeply.

#67. Which of the following is correct for a jet aircraft?

V2 > VMP > VMD > VY.

V2 < VMD < VMP < VY.

VY > VMD > VMP > V2.

VMD < VMP V2.

#68. Rate of climb is .......... by a headwind?

Increased.

Decreased.

Not affected.

Increased or decreased depending on load factor

#69. Angle of climb is .......... by a headwind?

Increased.

Decreased.

Not affected.

Increased or decreased depending on load factor.

#70. Climb gradient is ........ try a headwind?

Increased.

Decreased.

Not affected.

Increased or decreased depending on load factor.

#71. Power required is .......... as altitude increases in a steady climb?

Increased.

Decreased.

Not affected.

Increased or decreased depending on load factor.

#72. Load factor is ....... in a steady climb?

Increased.

Decreased.

Not affected.

Increased or decreased depending on weight.

#73. If excess power is 25000 ft Ibflmin and aircraft weight is 10000 Ibf what will be the maximum rate of climb?

2.5 ftlmin.

25 ftlmin.

250 ftlmin.

2500 ftlmin.

#74. If maximum thrust is 25000 Ibf, drag is 15000 Ibf and weight is 10000 Ibf what will be the maximum angle of climb?

10°

50°

70°

90°

#75. If at 250 Kts, excess power is 50,000,000 ft Ibflmin, and weight is 10000 Ibf, what is maximum angle of climb?

1.5°

11.5°

21.5°

31.5°

#76. What might the points C and D represent on the whole aircraft polar Diagram right?

Best L;D ratio Minimum drag.

Jet aircraft Vy Prop aircraft Vy.

Best L:D ratio Stalling.

Prop aircraft Vy Jet aircraft Vy.

#77. What might points C and D represent on the whole aircraft polar Diagram right?

Prop aircraft Vy Prop aircraft Vx.

Prop aircraft Vx VMP.

VMD. Prop aircraft Vx.

Prop aircraft Vy VMD.

#78. Increasing weight will ........ glide speed and ........ maximum glide endurance?

Increase Increase.

Increase Decrease.

Decrease Decrease.

Decrease Increase.

#79. Increasing weight will ......... VMD, and .......... rate of descent for best glide range?

Increase Increase.

Increase Decrease.

Decrease Decrease.

Decrease Increase.

#80. Deploying landing flap will ........ 'Vx, and .......... maximum angle of climb?

Increase Increase.

Increase Decrease.

Decrease Decrease.

Decrease Increase.

#81. Use of reheat in a climb will ........ maximum angle of climb, and ......... maximum rate of climb?

Increase Increase.

Increase Decrease.

Decrease Decrease.

Decrease Increase.

#82. If use of reheat doubles thrust available this will .......... the maximum angle of climb?

Half.

Double.

More than double.

Less than double.

#83. If TAS is 200 Kts and rate of climb is 1000 fttmin, what is the climb gradient?

5%

10%

50%

15%

#84. If climb gradient is 15% and TAS is 250 Kts, what is the rate of climb?

1750 ft/min.

2750 ft/min.

3750 ft/min.

4750 ft/min.

#85. For maximum rate of descent use .... thrust, .......... Drag, and ........... to maintain airspeed within limits?

Maximum Minimum Spoilers.

Maximum Minimum Attitude.

Minimum Maximum Spoilers.

Minimum Maximum Attitude.

#86. In a constant IAS climb ....... might be inadvertently exceeded?

VNE.

VMO.

VS.

MMO.

#87. In a constant TAS climb ........ might be inadvertently exceeded?

VMO.

VNE.

VS.

MMO.

#88. In a constant mach climb ....... might be inadvertently exceeded?

VMO.

VNE.

VS.

MMO.

#89. In a constant mach descent ....... might be inadvertently exceeded?

VMO.

VNE.

VS.

MMO.

#90. When climbing at constant 1/2PV² IAS will .......? .

Increase.

Decrease.

Remain constant.

Increase up to 36000 ft then remain constant.

#91. If at 40000 feet altitude air density is 1/4 of its sea level value, how will best climb TAS compare with best climb IAS?

The same.

Double.

Quadruple.

Less than.

#92. If maximum thrust is 10000 Ibf, drag is 500 Ibf and weight is 5000 lbf, what will be the maximum rate of climb at the absolute ceiling?

100 ft/min.

500 ft/min.

zero.

More than 500 ft/min.

#93. How does Vx compare with Vy at the absolute ceiling?

The same.

More than.

Less than.

More or less than depending on aircraft type.

#94. How does the angle of climb of a propeller aircraft vary with increasing airspeed?

Decreases.

Increases.

Remains constant.

Increases up to VMD then decreases.

#95. How does maximum angle of climb for a jet aircraft vary with increasing airspeed?

Decreases.

Increases.

Remains constant.

Increases up to VMD then decreases.

#96. How does maximum rate of climb for a jet aircraft vary with increasing airspeed?

Decreases.

Increases up to VMP then decreases.

Remains constant.

Increases up to 1.3 VMD then decreases.

#97. If weight is 15000 Ibf, maximum thrust is 25000 Ibf and drag is 5000 lbf, what will be the maximum climb angle?

13.6 °

23.6°.

33.6°.

90°.

#98. If excess power is 350 THP when TAS is 250 Kts and weight is 10000 Ibf, what will be the maximum rate of climb at that speed?

1155 FT/MIN.

2155 FT/MIN.

3155 FT/MIN.

4155 FT/MIN.

#99. If the weight of the aircraft in question 98 is doubled how will this affect maximum rate of climb?

Double it.

Half it.

Increase it.

Decrease it by 41%.

#100. If airspeed is maintained constant as aircraft weight reduces due to fuel use the aircraft will be in a ............ ?

Constant rate climb.

Cruise climb.

Zoom climb.

Constant altitude flight.

Dgca Question Bank For Pilots

Results

#1. What speed is required to achieve maximum endurance in a piston engine powered and jet engine powered aircraft respectively?

#3. Select the correct words to complete the following statement. To achieve the maximum possible glide range it is necessary to fly at ........... This is achieved by flying the aircraft in a .................... condition and at .........?

#4. What speed is required to achieve maximum angle of climb in a jet aircraft and a piston aircraft respectively and for what purpose might this be required?

#5. What is the effect of increasing altitude on best rate of climb IAS and best climb TAS respectively?

#6. What happens to the range between minimum and maximum flight speeds for a subsonic aircraft as altitude increases?

#8. When flying at VMD an aircraft has a C1, of 0.45 and a CD of 0.0225. If its engines fail when flying at 36000 feet what will be its maximum glide range?

#9. When flying at VMD an aircraft weighing 400000 Ibf has a CL of 0.45 and a CD of 0.0225. If its engines fail when flying at 36000 feet what will be its maximum glide range if the pilot immediately dumps 100000 lbf of fuel? What effect will the reduced weight have on VMD?

#10. What is the available rate of climb at service ceiling for a piston and jet aircraft respectively?

#11. What speed is required to achieve best rate of climb in a piston and jet aircraft respectively?

#12. How is the absolute ceiling indicated on a power available / power required graph for a piston and jet aircraft respectively?

#13. What will be the effect of a headwind on glide range and glide angle respectively?

#14. What will be the effect of a tailwind on glide range and rate of descent?

#15. Which of the following best describes the effect of flap deployment?

#16. Best endurance for a piston aircraft is achieved at VMP, whilst that for a jet aircraft is achieved at (VMD) Why is this so?

#17. Which of the following best describes the effect of increasing altitude on maximum rate of climb?

#18. Which of the following best describes the manner in which best climb speed varies with altitude?

#19. How will a headwind and a tailwind respectively affect best range glide speed?

#20. If an aircraft enters a banked turn whilst climbing to cruising altitude what effect will this have on rate of climb at constant power setting?

#22. An aircraft weighing 200000 Ibf has a maximum excess power available of 1500 Thrust Horse Power. What will be its maximum rate of climb?

#23. An aircraft weighing 50000 lbf requires a thrust of 20000 Ibf when flying straight and level at 250 Kts IAS. What will be its maximum angle of climb at this speed assuming its maximum thrust at this speed is 40000 lbf and the total drag force does not change during the climb?

#24. In tlie climb described in question 23 what will be the lift force generated by the aircraft?

#25. An aircraft weighing 50000 Ibf requires a thrust of 20000 Ibf when flying straight and level at 250 Kts IAS. How many Thrust Horse Power will it be developing when flying straight and level at this speed? (Assume 1 nm = 6000 ft)

#27. An aircraft weighing 50000 Ibf requires a thrust of 20000 Ibf when flying straight and level at 250 Kts IAS. If it were to climb to 40000 ft what would be its power available in comparison to that at ISA msl?

#28. What would be the effect of sweeping back the wings of a variable geometry aircraft in gliding flight?

#29. How is maximum rate of emergency descent achieved in a high speed jet aircraft?

#30. What do points A and B represent on the whole aircraft polar diagram right?

#31. An aircraft weighing 50000 Ibf is able to achieve a maximum rate of climb of 1500 ft / min when climbing at 250 Kts TAS. How much Excess Power will be required to achieve this rate of climb?

#32. An aircraft weighing 50000 Ibf is able to achieve a maximum rate of climb of 1500 ft / min when climbing at 250 Kts TAS. What will be the maximum all up weight at which it can achieve a 5% climb gradient at this speed assuming its power available and total drag do not change during the climb?

#33. Increased weight reduces the rate of climb and climb gradient but?

#34. Best climb gradient is achieved by flying at approximately?

#35. Absolute ceiling occurs when?

#36. What airspeed will produces the greatest glide endurance?

#37. What factors determine maximum glide range?

#38. What are VMCAa nd VMDR?

#39. How do VMGA and VMDR compare?

#40. Which of the following is equal to lift in a steady climb or descent?

#41. What proportion of thrust is employed in supporting the weight of an aircraft in a steady climb?

#42. What provides maximum glide range?

#43. What would give maximum glide range in a headwind?

#44. What would give maximum glide range in a tailwind?

#45. Which of the points on the CL:CD polar would give maximum glide range?

#46. In a steady climb?

#47. What is the speed for minimum sink rate?

#48. What flap position would give maximum glide range?

#49. What speed gives best angle of climb in a jet aircraft?

#50. Which of the following occur at VMD? 1. L:D Max. 2. Max jet endurance. 3. ax prop range. 4. Max jet climb angle. 5. Max glide range all types.

#51. What will be the effect of an increase in weight? 1. VMD will increase. 2. Glide range will decrease. 3. Glide angle will increase. 4. Glide range and angle will be unaffected.

#52. In what direction does lift act in a steady climb?

#53. What is the absolute ceiling of an aircraft? 1. The altitude where the low speed and high speed stall lines cross. 2. The altitude at which power required is equal to power available. 3. The altitude at which thrust available is equal to drag. 4. The altitude at which rate of climb is zero.

#54. Increasing aircraft weight. .. .... . ..glide speed and... .... rate of descent?

#55. To descend at constant glide angle and IAS, the pitch attitude must.. .. .......?

#56. For a constant mach number descent, gradient must ...... ?

#57. For a constant IAS descent, gradient must ...... ?

#58. A headwind in a constant mach number climb will ............ angle of climb?

#59. For maximum glide range, TAS must ..... ?

#60. To descend at constant IAS the ............m ust be ..........?

#61. Best cHtnb angle is achieved at.............. ?

#62. Maximum rate of climb occurs at ........... speed?

#63. Maximum glide range is achieved at. ...........?

#64. Load factor in a steady climb will be.... ... ?

#65. Lift in a steady climb is equal to ........ ?

#66. The correct procedure for an emergency descent is?

#67. Which of the following is correct for a jet aircraft?

#68. Rate of climb is .......... by a headwind?

#69. Angle of climb is .......... by a headwind?

#70. Climb gradient is ........ try a headwind?

#71. Power required is .......... as altitude increases in a steady climb?

#72. Load factor is ....... in a steady climb?

#73. If excess power is 25000 ft Ibflmin and aircraft weight is 10000 Ibf what will be the maximum rate of climb?

#74. If maximum thrust is 25000 Ibf, drag is 15000 Ibf and weight is 10000 Ibf what will be the maximum angle of climb?

#75. If at 250 Kts, excess power is 50,000,000 ft Ibflmin, and weight is 10000 Ibf, what is maximum angle of climb?

#76. What might the points C and D represent on the whole aircraft polar Diagram right?

#77. What might points C and D represent on the whole aircraft polar Diagram right?

#78. Increasing weight will ........ glide speed and ........ maximum glide endurance?

#79. Increasing weight will ......... VMD, and .......... rate of descent for best glide range?

#80. Deploying landing flap will ........ 'Vx, and .......... maximum angle of climb?

#81. Use of reheat in a climb will ........ maximum angle of climb, and ......... maximum rate of climb?

#82. If use of reheat doubles thrust available this will .......... the maximum angle of climb?