A plane flying at 319 m/s airspeed uses a turbojet engine to provide thrust. At its operational altitude, the air has a

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A plane flying at 319 m/s airspeed uses a turbojet engine to
provide thrust. At its operational altitude, the air has a pressure
of 42 kPa and a temperature of -7 ºC. The fuel-air ratio is 0.6% -
that is, for every kg of air passing through the turbine, 0.006 kg
of fuel is burned – and the jet fuel used has a heating value of 41
MJ/kg. If the compressor pressure ratio is 11, and we assume that
flow speed is negligibly small between the compressor inlet and
turbine outlet, determine the temperature of the exhaust gases to
the nearest Kelvin. Use the same properties for air as in question
10 and treat all components as ideal.