Aerospace Engineering > GATE 2021 > Rocket Propulsion
Hot gases are generated at a temperature of 2100 K and a pressure of 14 MPa in a rocket chamber. The hot gases are expanded ideally to the ambient pressure of 0.1 MPa in a convergent-divergent nozzle having a throat area of 0.1 m2. The molecular mass of the gas is 22 kg/kmol. The ratio of specific heats (γ) of the gas is 1.32. The value of the universal gas constant (Ro) is 8314 J/kmol-K. The acceleration due to gravity, g, is 9.8 m/s2. The specific impulse of the rocket is _______ seconds. (round off to two decimal places)

Correct : 216 to 220

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rocket propulsion specific impulse calculation convergent-divergent nozzle hot gases expansion GATE Aerospace Engineering 2021 rocket chamber design specific heat ratio universal gas constant rocket specific impulse GATE aerospace 2021 rocket nozzle design specific impulse rocket aerospace engineering gate specific heat ratio rocket rocket chamber pressure specific impulse calculation convergent-divergent nozzle design

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