Engineering, 15.04.2020 01:08 rhineharttori

Consider a circular cylinder in hypersonic flow, with its axis perpendicular to the flow. Let φ be the angle measured between radii drawn to the leading edge (the stagnation point) and to any arbitrary point on the cylinder. The pressure coefficient distribution along the cylindrical surfaces is given by Cp = 2cos 2φ for 0 ≤ φ ≤ π/2 and 3π/2 ≤ φ ≤ 2π and Cp = 0 for π/2 ≤ φ ≤ 3π/2.
Calculate the drag coefficient for the cylinder, based on the projected frontal area of the cylinder.

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Consider a circular cylinder in hypersonic flow, with its axis perpendicular to the flow. Let φ be t...

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