2) Turbojet Engine A standard turbojet engine dries an airplane traveling with a velocity of 290 m/s at a height where the pressure is 28 kPa and the temperature is -40 C. The compressor pressure ratio is 11 and the turbine inlet temperature is 1300 K. The mass flow through the engine is 60 kg/s. Assume isentropic efficiencies of 0.82 for the compressor and turbine, 0.95 for the nozzle and 100% for the diffuser. Determine the velocity of the exhaust gas, the propulsive power, the rate of fuel consumption when the heating value of the fuel is 42 MJ/kg, the propulsive efficiency, and the Froude efficiency. Assume air is the working fluid and is an ideal gas.