8.48. A jet fighter is flying at M = 2 in still air which has a temperature of 0°F and a pressure of 4.0 psia. The air inlet to the jet engine is a converging-diverging duct. Inside the engine the flow is subsonic. The cross-sectional area at the throat is 2.0 ft². What is the mass flow rate through this diffuser, assuming isentropic flow?
8.48. A jet fighter is flying at M = 2 in still air which has a temperature of 0°F and a pressure of 4.0 psia. The air inlet to the jet engine is a converging-diverging duct. Inside the engine the flow is subsonic. The cross-sectional area at the throat is 2.0 ft². What is the mass flow rate through this diffuser, assuming isentropic flow?
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Transcribed Image Text:8.48. A jet fighter is flying at M = 2 in still air which has a temperature of 0°F and a
pressure of 4.0 psia. The air inlet to the jet engine is a converging-diverging duct.
Inside the engine the flow is subsonic. The cross-sectional area at the throat is
2.0 ft². What is the mass flow rate through this diffuser, assuming isentropic flow?
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