Determine the nozzle throat area for a rocket engine producing a tota – McqOptions

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1.	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.
A.	10.12 cm2
B.	12.10 cm2
C.	11.20 cm2
D.	21.10 cm2
Answer» B. 12.10 cm2

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