Compressible Flow Air at 3.4 bar, 530 K, and a Mach number

Chapter 9, Problem 137P

(choose chapter or problem)

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 \(M_{\mathrm{x}}=1.8\). The flow is isentropic, except where the shock stands. If the air behaves as an ideal gas with k = 1.4, determine

(a) the stagnation temperature \(T_{\mathrm{ox}}\), in K.

(b) the stagnation pressure \(p_{\mathrm{ox}}\), in bar.

(c) the pressure \(p_{\mathrm{x}}\), in bar.

(d) the pressure \(p_{\mathrm{y}}\), in bar.

(e) the stagnation pressure \(p_{\mathrm{oy}}\), in bar.

(f) the stagnation temperature \(T_{\mathrm{oy}}\), in K.

If the throat area is \(7.6 \times 10^{-4} \mathrm{\ m}^{2}\), and the exit plane pressure is 2.4 bar, determine the mass flow rate, in kg/s, and the exit area, in \(\mathrm{m}^{2}\).

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