
Find the enthalpy change, internal energy change and entropy change across a shock wave whose upstream air temperature and pressure …
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Find the reservoir pressure for a nozzle of a supersonic wind tunnel which has an exittothroat area ratio of \(4.441\). …
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The upstream Mach number, pressure and temperature of a supersonic flow over an expansion corner having deflection angle \(\theta =25^{^{\circ}}\) …
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An oblique shock wave is generated at a compression corner having a deflection angle of \(20^{^{\circ}}\). The oblique shock wave …
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A flow is passing over a \({20^ \circ }\) halfangle wedge having a upstream Mach number, pressure and temperature of …
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An oblique shock wave is generated with a wave angle of \({30^ \circ }\) in a Mach \(4\) flow, at …
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A flow passes through a normal shock wave has a pressure, temperature and Mach number of \(1\,atm,\,295\,K\) and \(2.8\) upstream …
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Find the speed of sound in air at a temperature of 250 K.
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Find the stalling speed of an airplane which has a wing area of \(17\,m^2\) and is flying at sea level …
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Calculate the lift, drag and moment coefficient about quarter chord per unit span of an airfoil which is at an …
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