The hot gas supply to a propulsion nozzle is at a pressure

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Reference no: EM13345722

The hot gas supply to a propulsion nozzle is at a pressure of 55kpa and temperature of 800K. the ambient pressure is 15kpa. If the ratio of specific heats is 1.33, approximately constant, and the molecular weight of the mixture is 30, determine the ratio of gross thrusts for 2 cases,
a)the nozzle is converging-diverging with a area ratio for correct expansion to ambient pressure.
b)the nozzle is converging only. What is the nozzle exit to throat area for case (a)? the gross thrust is the contribution to engine thrust made by the exit nozzle only.

Reference no: EM13345722

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