Chapter 1, Problem 1.13P

Consider a circular cylinder in a hypersonic flow, with its axis perpendicular to the flow. Let $\varphi$ 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 $C_p=2{\cos }^2\varphi$ for $0\le \varphi \le \pi /2$ and $3\pi /2\le \varphi \le 2\pi$ and $C_p=0$ for $\pi /2\le \varphi \le 3\pi /2$. Calculate the drag coefficient for the cylinder, based on projected frontal area of the cylinder.