A turbo-prop aircraft is flying at 650 km/h at an altitude where the ambient temperature is -18^oC. The compressor pressure ratio is 9/1. The maximum cycle temperature is 850^oC. The intake duct efficiency is 90% and stagnation efficiency of the compressor and turbine are 89% and 90% respectively. Calculate the work output and cycle efficiency.

Neglecting the pressure loss in the combustion chamber, assume that the exhaust gases leave the aircraft at 650 km/h relative to the aircraft.

For product gases, take (C_P = 1.15 kJ/kg. K  &   γ=1.333)

For air, take (C_P =1.005 kJ/kg. K  &   γ=1.4)