Q$4/$ The airfoil flow with $M_1=2\mathrm{.}0.$ Determine the pressure distribution and the lift$-$to$-$drag ratio of a symmetric two$-$dimensional supersonic airfoil shown in figure below. Solve problem using linear theory and apply your results to the following cases: $-$

$x\frac{1}{c}=0\mathrm{.}5$ and $\frac{t}{c}=0\mathrm{.}05$

$x\frac{1}{c}=0\mathrm{.}3$ and $\frac{t}{c}=0\mathrm{.}06$