$5\mathrm{.}27$ The airfoil on the Lockheed F$-104$ straight$-$wing supersonic fighter is a thin, symmetric airfoil with a thickness ratio of $3\mathrm{.}5\%.$ Consider this airfoil in a flow at an angle of attack of $5$o$.$ The incompressible lift coefficient for the airfoil is given approximately by cl$=2$$,$ where is the angle of attack in radians.$$ Estimate the airfoil lift coefficient for $($a$)$ M $=0\mathrm{.}2,($b$)$ M $=0\mathrm{.}7,$ and $($c$)$ M $=2\mathrm{.}0.$