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 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, Combustor pressure loss = 6% of compressor delivery pressure,