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