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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 ms at analtitude where the air is at kpa and deg c Thecompressor has a pressure ratio of and thetemperature of the gases at the turbine inlet is deg c Air enters the compressor at a rate of kgs 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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