Determine the thrust of the rocket

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Reference no: EM13707437

Consider a rocket engine with an exit area of 8.5 m². The flow rate of fuel and oxidizer are 75 kg/sec and 8 kg/sec respectively. Determine the thrust of the rocket if it is operating at an altitude of 200 km above sea level. The exhaust velocity and pressure are 2800 m/sec and 750 N/m²

Hint: At 200 km, there is no air, and we have a vacuum pressure.

Reference no: EM13707437

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