Compressible Flow
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 the 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. Determine
(a) the stagnation temperature Tox, in K.
(b) the stagnation pressure pox, in bar.
(c) the pressure px, 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 7.6 x 10-4 m2, and the exit plane pressure is 2.4 bar, determine the mass flow rate, in kg/s, and the exit area, in m2.
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