GATE AE year:2025 PYQs & Answers — Page 7 — Exam Papers

Questions 61–65 of 65. Imported answers require independent review unless marked reviewed.

Topic practice 65 questionsPage 7 of 7

An ideal turbofan with a bypass ratio of 5 has core mass flow rate,

kg/s. The core and the fan exhausts are separate and optimally expanded. The core exhaust speed is 600 m/s and the fan exhaust speed is 120 m/s. If the fuel mass flow rate is negligible in comparison to

, the static specific thrust (

) developed by the engine is ____ N s/kg (rounded off to the nearest integer).

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Air at temperature 300 K is compressed isentropically from a pressure of 1 bar to 10 bar in a compressor. Eighty percent of the compressed air is supplied to a combustor. In the combustor, 0.8 MJ of heat is added per kg of air. The specific heat at constant pressure is

J/kg/K and the specific heat ratio is

. The temperature of the air leaving the combustor is ____ K (rounded off to one decimal place).

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A monopropellant liquid rocket engine has 800 injectors of diameter 4 mm each, and with a discharge coefficient of 0.65. The liquid propellant of density 100 kg/m

flows through the injectors. There is a pressure difference of 10 bar across the injectors. The specific impulse of the rocket is 1500 m/s. The thrust generated by the rocket is ____ kN (rounded off to one decimal place).

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An ideal ramjet with an optimally expanded exhaust is travelling at Mach 3. The ambient temperature and pressure are 260 K and 60 kPa, respectively. The inlet air mass flow rate is 50 kg/s. Exit temperature of the exhaust gases is 700 K. Fuel mass flow rate is negligible compared to air mass flow rate. Gas constant is R= 287 J/kg/K, and specific heat ratio is

. The thrust generated by the engine is ____ kN (rounded off to one decimal place).

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A single-stage axial compressor, with a 50 % degree of reaction, runs at a mean blade speed of 250 m/s. The overall pressure ratio developed is 1.3. Inlet pressure and temperature are 1 bar and 300 K, respectively. Axial velocity is 200 m/s. Specific heat at constant pressure,

J/kg/K and specific heat ratio,

. The rotor blade angle at the outlet is ____ degrees (rounded off to two decimal places).

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