GATE AE Airplane Performance PYQs & Answers — Page 3

Questions 21–30 of 43. Imported answers require independent review unless marked reviewed.

For a conventional fixed-wing aircraft in a 360° inverted vertical loop maneuver, what is the load factor (

) at the topmost point of the loop? Assume the flight to be steady at the topmost point.

Your answerChoose one option.

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Which of the following statement(s) is/are true?

Your answerSelect all correct options. You can choose more than one.

Service ceiling is higher than absolute ceiling for a piston-propeller aircraft.

For a given aircraft, the stall speed increases with increase in altitude.

Everything else remaining the same, a tailwind increases the range of an aircraft.

For a jet aircraft constrained to fly at constant altitude, there exists an altitude where its range is maximum.

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An airplane weighing 5500 kg is in a steady level flight with a speed of 225 m/s. The pilot initiates a steady pull-up maneuver with a radius of curvature of 775 m. The location of center of gravity (CG), center of pressure on wing (CP) and point of action (T) of tail force are marked in the figure. Use g = 9.81 m/s². Neglect drag on the tail and assume that tail force is vertical. Assuming the engine thrust and drag to be equal, opposite and collinear, the tail force is______________ kN (round off to one decimal place).

Diagram for Aerospace Engineering question 53

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A jet aircraft weighing 10,000 kg has an elliptic wing with a span of 10 m and area 30 m

. The

for the aircraft is 0.025. The maximum speed of the aircraft in steady and level flight at sea level is 100 m/s. The density of air at sea level is 1.225 kg/m

, and take

m/s

. The maximum thrust developed by the engine at sea level is _____ N (round off to two decimal places).

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An airplane of mass 5000 kg is flying at a constant speed of 360 km/h at the bottom of a vertical circle with a radius of 400 m, as shown in the figure. Assuming that the acceleration due to gravity is 9.8 m/s

, the load factor experienced at the center of gravity of the airplane is ______ (round off to two decimal places).

Diagram for Aerospace Engineering question 25

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A single engine, propeller driven, general aviation airplane is flying in cruise at sea-level condition (density of air at sea-level is 1.225 kg/m³) with speed to cover maximum range. For drag coefficient

and wing loading

N/m², the speed of the airplane is ______ m/s (round off to one decimal place).

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An airplane of mass 400 kg and wing reference area 25 m² flying at sea level has a maximum lift coefficient of 1.65. Assume density of air as 1.225 kg/m³ and acceleration due to gravity as 9.8 m/s². Using a factor of safety of 1.25 to account for additional unsteady lift during a sudden pull-up, the speed at which the airplane reaches a load factor of 3.2 is ______ m/s (round off to two decimal places).

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When a propeller airplane in ground-roll during take-off experiences headwind, which of the following statements is FALSE?

Your answerChoose one option.

The drag on the airplane increases.

The thrust from the propellers decreases.

The wing lift increases.

The ground-roll distance increases.

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The power-off glide range for an airplane with a maximum Lift to Drag ratio of 18, when the glide starts at an altitude of 4 km, is ______ km (round off to the nearest integer).

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For an airplane flying in a vertical plane, the angle of attack is 3°, the horizontal and vertical components of velocity in wind axis are 300 km/h and 15.72 km/h, respectively. The pitch attitude of the airplane is ______ degrees (round off to 2 decimal places).

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GATE AE Airplane Performance PYQs

Question 30

Question 35

Question 53

Question 54

Question 25

Question 46

Question 54

Question 8

Question 17

Question 18