At an altitude where the air is at 35 kPa and -40°C a turbojet
aircraft flies...
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Mechanical Engineering
At an altitude where the air is at 35 kPa and -40°C a turbojetaircraft flies with a velocity of 260 m/s. Compressor has apressure ratio of 10, and the temperature of the gases at theturbine inlet is 1100°C. Air enters the compressor at a rate of 45kg/s.
*Part(A)* Use *hot air standard assumptions* to find
(a) the temperature and pressure of the gases at the turbineexit
(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 turbineexit
(b) the velocity of the gases at the nozzle exit
(c) the propulsive efficiency of the cycle
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