Consider a turbojet in an airplane flying at standard sea level with a velocity of 800 ft/s. The pressure ratio across the compressor is 12.5:1. The fuel-to-air ratio (by mass) is 0.05. If the nozzle exhausts the flow to ambient pressure, calculate the gas temperature at the exit. (In solving this problem, assume the air in the diffuser is slowed to a very low velocity before entering the compressor. Also assume the heat released per pound of fuel is 1.4 × 107 ft • lb/lbm.)
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