3. A simple turbojet is operating with a compressor pressure ratio of 16.0, a turbine inlet temperature of 1500 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 Polytropic efficiencies of turbine Isentropic efficiency of intake Isentropic efficiency of nozzle Isentropic mechanical efficiency Combustor loss Combustor efficiency 0.87 0.87 0.95 0.95 0.99 6% compressor delivery pressure 0.97