At an altitude where the air is at 35 kPa and -40°C a turbojet aircraft flies...

At an altitude where the air is at 35 kPa and -40°C a turbojet aircraft flies with a velocity of 260 m/s. Compressor has a pressure ratio of 10, and the temperature of the gases at the turbine inlet is 1100°C. Air enters the compressor at a rate of 45 kg/s.

*Part(A)* Use *hot air standard assumptions* to find

(a) the temperature and pressure of the gases at the turbine exit

(b) the velocity of the gases at the nozzle exit

(c) the propulsive efficiency of the cycle

*Part(B)* Use *cold air standard assumptions* to find

(a) the temperature and pressure of the gases at the turbine exit

(b) the velocity of the gases at the nozzle exit

(c) the propulsive efficiency of the cycle

Expert Solution

samet mamat answered 2 years ago

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