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