$2.$ A diamond$-$wedge airfoil with a half angle of $\backslash (6^\{\backslash$circ$\}\backslash )$ is placed in a Mach $3\mathrm{.}5$ flow $\backslash ((\backslash$alpha$=0)\backslash ).$ A circular cylinder oriented with its axis perpendicular to the flow, is also placed in the flow. The thickness of the airfoil is equivalent to the diameter of the cylinder. If it is given that the drag coefficient of the cylinder $($based on projected frontal area$)$ is $\backslash (4/3\backslash ),$ calculate the ratio of diamond airfoil drag to cylinder drag. Does this result state anything about the aerodynamic performance of a blunt body as compared to sharp$-$nosed, slender body in supersonic flow?