GATE AE Airplane Performance PYQs & Answers — Page 4

Questions 31–40 of 43. Imported answers require independent review unless marked reviewed.

The airplane shown in figure starts executing a symmetric pull-up maneuver from steady level altitude with a constant nose-up pitch acceleration of 20 deg/s

. The vertical load factor measured at this instant at the centre of gravity (CG) is 2. Given that the acceleration due to gravity is 9.81 m/s

, the vertical load factor measured at point P on the nose of the airplane, which is 2 m ahead of the CG, is ______ (round off to 2 decimal places).

Diagram for Aerospace Engineering question 40

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Consider an airplane with a weight of 8000 N, wing area of 16 m

, wing zero-lift drag coefficient of 0.02, Oswald’s efficiency factor of 0.8, and wing aspect ratio of 6, in steady level flight with wing lift coefficient of 0.375. Considering the same flight speed and ambient density, the ratio of the induced drag coefficient during steady level flight to that during a 30° climb is ______ (round off to 2 decimal places).

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A propeller driven airplane has a gross take-off weight of 4905 N with a wing area of 6.84 m

. Assume that the wings are operating at the maximum

ratio, the propeller efficiency is 0.9 and the specific fuel consumption of the engine is 0.76 kg/kW-hr. Given that the density of air at sea level is 1.225 kg/m

and the acceleration due to gravity is 9.81 m/s

, the weight of the fuel required for an endurance of 18 hours at sea level is ______ N (round off to the nearest integer).

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A jet aircraft is initially flying steady and level at its maximum endurance condition. For the aircraft to fly steady and level, but faster at the same altitude, the pilot should

Your answerChoose one option.

increase thrust alone.

increase thrust and increase angle of attack.

increase thrust and reduce angle of attack.

reduce angle of attack alone.

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An airplane requires a longer ground roll to lift-off on hot summer days because

Your answerChoose one option.

the thrust is directly proportional to free-stream density.

the thrust is directly proportional to weight of the aircraft.

the lift-off distance is directly proportional to free-stream density.

the runway friction is high on hot summer days.

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The highest limit load factor experienced by a civil transport aircraft is in the range

Your answerChoose one option.

0.0 – 2.0

2.0 – 5.0

5.0 – 8.0

8.0 – 10.0

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An aircraft with mass of 400,000 kg cruises at 240 m/s at an altitude of 10 km. Its lift to drag ratio at cruise is 15. Assuming g as 9.81 m/s

, the power (in MW) needed for it to cruise is ______ (accurate to two decimal places).

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An aircraft with a gross weight of 2000 kg, has a speed of 130 m/s at sea level, where the conditions are: 1 atmosphere (pressure), 288 K (temperature), and 1.23 kg/m

(density). The speed (in m/s) required by the aircraft at an altitude of 9000 m, where the conditions are: 0.31 atmosphere, 230 K, and 0.47 kg/m

, to maintain a steady, level flight is ______ (accurate to two decimal places).

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A pitot probe on an aircraft in a steady, level flight records a pressure of 55,000 N/m

. The static pressure and density are 45,280 N/m

and 0.6 kg/m

, respectively. The wing area and the lift coefficient are 16 m

and 2, respectively. The wing load (in N/m

) on this aircraft is ________ (accurate to one decimal place).

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Gross weight of an airplane is 700 N, wing area is 16 m

, and the maximum lift coefficient is 2.0. Assuming density at the altitude as 1.23 kg/m

, the stall speed (in m/s) of the aircraft is _______ (accurate to two decimal places).

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GATE AE Airplane Performance PYQs

Question 40

Question 41

Question 43

Question 4

Question 7

Question 16

Question 40

Question 42

Question 43

Question 48