GATE AE 2025 Paper 1 — page 16

Questions 46–48 of 65. Imported answers require review unless explicitly marked reviewed.

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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2025 · Paper 1

Question 46

Question 47

Question 48