Consider a rocket engine with an exit area of 85 m2 the


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.

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Mechanical Engineering: Consider a rocket engine with an exit area of 85 m2 the
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