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Consider a diamond$-$shaped airfoil. The maximum thickness is $0\mathrm{.}04$ and occurs at mid$-$chord. The freestream Mach number is $2\mathrm{.}0,$ and the airfoil is operating at a $5-$degree angle of attack. a$)$ Determine the lift coefficient, drag coefficient, lift$-$to$-$drag ratio, and moment coefficient about the leading edge using Ackert$$s rule. Answers: $0\mathrm{.}2015,0\mathrm{.}0212,9\mathrm{.}47,-0\mathrm{.}1008$ b$)$ Sketch C$\_$p vs x$/$c for the upper and lower surfaces.