In a turbo-prop engine, the compressor pressure ratio is 6/1 and the maximum cycle temperature is 760^oC. 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 = -7^oC. 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, (C_P = 1.15 kJ/kg. K  &   γ=1.333) & For air, (C_P =1.005 kJ/kg. K  &   γ=1.4)

Calculate;

(a) Specific power output

(b) Cycle efficiency