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The reservoir of a supersonic wind-tunnel has a total temperature and total pressure of \(600\,K\) and \(11\,atm\). If the flow is isentropic through the nozzle of this wind tunnel, find the nozzle’s exit temperature and density if its exit pressure is \(1\,atm\).
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Find the reservoir pressure for a nozzle of a supersonic wind tunnel which has an exit-to-throat area ratio of \(4.441\). The test section pressure measured by a pitot tube is \(1.5\, atm\).
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A flow is passing over a \({20^ \circ }\) half-angle wedge having a upstream Mach number, pressure and temperature of \(2.8,\,1\,atm\,\) and \(310\,K\). Find the wave angle and downstream Mach number, pressure and temperature.
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