Question: Consider a circular cylinder in a hypersonic flow, with its axis perpendicular to the flow. Let be the angle measured between radii drawn to the

Consider a circular cylinder in a hypersonic flow, with its axis perpendicular to the flow. Let 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 surface is given by Cp = 2 cos2 Φ for 0 < Φ < π/2 and 3π/2 < Φ > 2π and C= 0 for π/2 < Φ < 3 π/2. Calculate the drag coefficient for the cylinder, based on projected frontal area of the cylinder.

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Let us use the formalism surrounding Eq 116 in the text In this case c C and from Eq 116 neglecting ... View full answer

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