Question

4.24 A ramjet uses a hydrocarbon fuel with QR = 42,800 kJ/kg flying at Mach 2 (i.e., M, - 2) in an atmosphere where 0,= 300 m/s. Its exhaust is perfectly expanded and the exhaust velocity is V, = 1200 m/s. Assuming the inlet total pressure. recovery is j = 0.90, the burner losses are no = 0.98 and 1) = 0.96, the nozzle total pressure ratio is = 0.98 and 1 = 1:4 and.c, = 1.004 kJ/kg . K are constant throughout the engine, calculate (a) (b) fuel-to-air ratioſ (e) nondimensional-specific thrust F/(m,ao) (d) propulsive efficiency (e) thermal efficiency FIGURE P 4.24​

Answer 1

Answer:

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Answer 2

Answer:

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Explanation:

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