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Determine the chamber pressure for a rocket engine if the thrust coefficient is 1.8, the throat area is 0.2 m2 and the total thrust is 20000 N.

Determine the chamber pressure for a rocket engine if the thrust coefficient is 1.8, the throat area is 0.2 m2 and the total thrust is 20000 N. Correct Answer 55.56 kPa

Thrust force F = Pc At Cf, where Pc is the chamber pressure, At is the throat area and Cf is the thrust coefficient. Then, Pc = F/(At Cf) = 20000/(0.2×1.8) = 55.56 kPa.

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