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A turbojet aircraft flies with a velocity of 2 6 0 m / s at analtitude where the air is at 3 5 kpa and

A turbojet aircraft flies with a velocity of 260m/s at analtitude where the air is at 35kpa and -40\deg c. Thecompressor has a pressure ratio of 10, and thetemperature of the gases at the turbine inlet is 1100\deg c Air enters the compressor at a rate of 45kg/s Utilizing the Air - standard assumptions, determine (a) thetemperature and pressure of the gases at the turbineexit, (b) the velocity of the gases at the nozzle exit,and (c) the propulsive efficiency of the cycle

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