GATE AE year:2025 PYQs & Answers — Page 5

Questions 41–50 of 65. Imported answers require independent review unless marked reviewed.

Topic practice 65 questionsPage 5 of 7

(answer in integer).

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The equation of a closed curve in two-dimensional polar coordinates is given by

. The area enclosed by the curve is

(answer in integer).

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Consider the ordinary differential equation:

. If

, then the value of

(rounded off to the nearest integer).

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An approximate solution of the equation

is to be obtained using the Newton-Raphson method. If the initial guess is

, the value at the end of the first iteration is

(rounded off to two decimal places).

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and

denote unit vectors in the

and

directions, respectively. The outward flux of the two-dimensional vector field

over the unit circle centered at the origin is

(rounded off to two decimal places).

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An aircraft is flying at an altitude of 4500 m above sea level, where the ambient pressure, temperature and density are 57 kPa, 259 K and 0.77 kg/m

, respectively. The speed of the aircraft (

) is 230 m/s. Gas constant

J/kg/K, and specific heat ratio

. If the stagnation pressure is

, and static pressure is

, the value of

(rounded off to two decimal places).

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A rectangular wing of 1.2 m chord length and aspect ratio 5 is tested in a wind tunnel at an air speed of 60 m/s. The density and the dynamic viscosity of air are 1.3 kg/m

and

kg/m-s, respectively. A second rectangular wing of the same span, but with an aspect ratio of 6, is to be tested in the same tunnel at the same Reynolds number. The air speed at which the second test should be performed is

m/s (answer in integer).

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In a low-speed airplane, a venturimeter with 1.3:1 area ratio is used for airspeed measurement. The airplane’s maximum speed at sea level is 90 m/s. If the density of air at sea level is 1.225 kg/m

, the maximum pressure difference between the inlet and the throat of the venturimeter is

kPa (rounded off to two decimal places).

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A supersonic stream of an ideal gas at Mach number

is turned by a ramp, as shown in the figure. The ramp angle is 20°. The pressure ratio is

and the specific heat ratio is

. The pressure coefficient on the ramp surface is

(rounded off to two decimal places).

Diagram for Aerospace Engineering question 49

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A perfect gas flows through a frictionless constant-area duct with heat addition. The inlet conditions are as follows: pressure 100 kPa, density 1 kg/m

, and velocity 100 m/s. At a particular downstream location, the gas velocity is 200 m/s. The static pressure at the downstream location is

kPa (answer in integer).

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GATE AE year:2025 PYQs

Question 41

Question 42

Question 43

Question 44

Question 45

Question 46

Question 47

Question 48

Question 49

Question 50