Assuming the following component efficiencies and isa

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Reference no: EM13633186

A simple turbojet is operating with a compressor pressure ratio of 8.0, a turbine inlet temperature of 1200 K and a mass flow of 15 kg/s when the aircraft is flying at 260 m/s at an altitude of 7000 m. Assuming the following component efficiencies, and ISA conditions, calculate the propelling nozzle area required, the net thrust developed and the SFC:

Polytropic efficiencies of compressor and turbine: 0.87

Isentropic efficiency of intake: 0.95

Isentropic efficiency of propelling nozzle: 0.95

Mechanical Efficiency: 0.99

Combustion chamber pressure loss: 6% comp. deliv. press

Combustion efficiency: 0.97

Reference no: EM13633186

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