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An ideal turbojet powers a Mach 0

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An ideal turbojet powers a Mach 0.92 aircraft that requires 15,500 lbf of thrust at sea level. The compressor ratio is 16.4, and the exit total temperature from the combustion is 2450 ?R. The heating value of the fuel is 18,100 Btu/lbm. Find the required airflow. How large will the nozzle exit diameter be? What is the resulting TSFC and dimensionless thrust?