Engineering, 15.11.2019 04:31, samgirl2000

Air at 3.4 bar, 530 k, and a mach number of 0.4 enters a converging-diverging nozzle operating at steady state. a normal shock stands in the diverging section at a location where mach number is mx = 1.8. the flow is isentropic, except where the shock stands. the air behaves as an ideal gas with k = 1.4. d determine (a) the stagnation temperature tox, in k. (b) the stagnation pressure po, in bar (c) the pressure p, in bar (d) the pressure py, in bar (e) the stagnation pressure poy, in bar (f) the stagnation temperature toy, in k. (g) if the throat area is 7.6x10 m2, and the exit plane pressure is 2.4 bar, determine the mass flow rate, in kg/s, and the exit area, in mt answerl (a) 547.0k; (b) 3.796 bar; (c) 0.6607 bar; (d) 2.387 bar; (e) 3.086 bar; (f) 547.0k; (g) 0.498 kg/s and 10.99x10* m2.

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Air at 3.4 bar, 530 k, and a mach number of 0.4 enters a converging-diverging nozzle operating at st...