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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 …
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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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- 1 answers
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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 \(4.441\). …
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- 1 answers
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Find the lift and wave drag coefficients for an infinitely thin flat plate at an angle of attack of \(8^{\circ}\) …
- 327 views
- 1 answers
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An oblique shock wave is generated with a wave angle of \({30^ \circ }\) in a Mach \(4\) flow, at …
- 321 views
- 1 answers
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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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- 1 answers
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What are expansion waves ? How does it originates ?
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What are shock waves ? How does it originates ?
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Calculate the wave drag on the wings of an airplane which is flying at a Mach number of \(2.1\) at …
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- 1 answers
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What is a Mach wave ? How does it forms ?
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Calculate lift, wave-drag and pressure coefficients of an infinitely thin flat plate which is in a Mach \(2.5\) freestream flow at an angle of attack of \(5^{^{\circ}}\), using linearized theory.
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Find the velocity, pressure and temperature at, \((0.07\,m, 0.07\,m)\).
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