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Determine the nozzle throat area for a rocket engine producing a total thrust of 10 kN, chamber pressure of 5.2 MPa and thrust coefficient of 1.9.

Determine the nozzle throat area for a rocket engine producing a total thrust of 10 kN, chamber pressure of 5.2 MPa and thrust coefficient of 1.9. Correct Answer 10.12 cm2

Nozzle throat area At = F/P1CF, where P1 is the chamber pressure, CF is the thrust coefficient and F is the total thrust provided by the rocket engine. Then At = 10000/(5.2 x 106 x 1.9) = 10.12 cm2.

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