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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 …
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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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Why is critical Mach number of a sphere higher than a cylinder ?
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Find the velocity, pressure and temperature at, \((0.07\,m, 0.07\,m)\).
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Find the pressure coefficient at this point.
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