In a turbo-prop engine, the compressor pressure ratio is 6/1 and the maximum cycle temperature is 760oC. The stagnation isentropic efficiencies of compressor and turbine are 85% and 88% respectively. The mechanical efficiency of the drive is 99%. The aircraft velocity is 725 km//h and it is at an altitude with ambient condition of temperature = -7oC. Taking intake direct efficiency of 90%. Neglecting the pressure loss in the combustion chamber and assuming that the gases in the turbine expand to atmospheric pressure leaving the aircraft at 725 km/h relative to the aircraft.
For product gases, (CP = 1.15 kJ/kg. K & γ=1.333) & For air, (CP =1.005 kJ/kg. K & γ=1.4)
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