A jet-propelled plane consuming air at the rate of 20 kg/s, is to fly at a Mach number0.6 at an altitude of 5000m where the pressure is 0.55kgf/ c* m ^ 2 and temperature is - 20 deg * C The which has a pressure coefficient of 0.9 decelerates the flow to negligible velocity. The compressor pressure ratio is 5 and the maximum temperature inthe combustion chamber is 1000 deg * C After Expanding in the turbine, the gases continue to expand in the nozzle to a pressure of0.7kgf/c* m^ 2 The isentropic efficiencies of the compressor, turbine, and nozzle are 0.81,0-85 and 0.92. The calorific value of the fuel is 1000kcal/kg. Assuming that the product of combustion have the same properties as air, find (a) the power input to the compressor; (b) the power output of the turbine: (c) the fuel-air ratio; (d) the exit Mach number: (e) the thrust provided by the engine; and (f) the thrust power developed