Compressible Flow
Air as an ideal gas with k = 1.4 enters a converging– diverging duct with a Mach number of 2. At the inlet, the pressure is 26 lbf/in.2 and the temperature is 445°R. A normal shock stands at a location in the converging section of the duct, with Mx = 1.5. At the exit of the duct, the pressure is 150 lbf/in.2 The flow is isentropic everywhere except in the immediate vicinity of the shock. Determine temperature, in °R, and the Mach number at the exit.
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