
The reservoir of a supersonic windtunnel has a total temperature and total pressure of \(600\,K\) and \(11\,atm\). If the flow …
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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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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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Find the neutral point and static margin of an airplane if the location of the aerodynamic center is at \( …
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Consider wing body combination of an airplane. Find the coefficient of lift of this wing body if the coefficient of …
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Find the turn radius and turn rate of an airplane, flying at a velocity of \(403.2\, km/h\) and has a …
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Find the gliding distance of an aircraft flying at an altitude of \(1500\,m\) with a maximum lift to drag ratio …
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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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