A turboprop aircraft is flying at 650 km/h at an altitude where the ambient temperature is -80. The compressor pressure ratio is 9 to 1 and maximum cycle temperature is 850. The intake duct efficiency is 90% and stagnation isentropic efficiency of compressor and turbine are 89% and 93% respectively. Calculate the specific power output and cycle efficiency taking mechanical efficiency of 98%. Neglecting pressure losses in combustion chamber and assuming exhaust gas leave the aircraft at 650 km/h relative to the aircraft.

For product gases, take (CP = 1.15 kJ/kg. K  &   γ=1.333)n
n
For air, take (CP =1.005 kJ/kg. K  &   γ=1.4)