Aerospace Engineering > GATE 2026 > Rocket Propulsion
An ideal rocket has characteristic exhaust velocity of 1200 m/s, mass flow rate of 75 kg/s, thrust coefficient of 1.5, and nozzle throat area of 0.025 m2. The chamber pressure in kPa and the specific impulse due to gravity in seconds are ________, respectively. Assume that the acceleration due to gravity is 9.8 m/s2.
A
3600 and 183.67
B
4600 and 190.51
C
3600 and 175.23
D
3500 and 183.67

Correct : a

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Related Topics

rocket propulsion ideal rocket characteristic exhaust velocity mass flow rate thrust coefficient nozzle throat area chamber pressure kPa specific impulse gravity GATE Aerospace Engineering 2026 rocket thrust calculation specific impulse formula GATE 2026 Aerospace

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