A turbojet aircraft is flying with a velocity of 250 m/s at an altitude where the ambient conditions are 20 kPa and -25oC. The pressure ratio across the compressor is 12, and the temperature at the turbine inlet is 1000oC. Air enters the compressor at a rate of 50 kg/s. Determine
(a) The temperature (T) and pressure (p) of the gases at the turbine exit,
(b) The velocity (V) of the gases at the nozzle exit and
(c) The propulsive efficiency of the cycle. Use the PG model.