How to solve

Consider the supersonic airfoil shape with a chord of one shown above; it is composed of straightline segments, with a maximum thickness to chord ratio of $6\%$ at $30\%$ chord. The chord is the reference line from the airfoil's leading edge to its trailing edge. Calculate $p,p_0,T,T_0,,{}_0$ at all stations $(1_{\text{t}\text{o}\text{p}},2_{\text{t}\text{o}\text{p}},3_{\text{t}\text{o}\text{p}},1_{btm},2_{btm},3_{btm}).$ Assume that the airfoil is flying at an angle of attack $$ of $3$ degrees and a Mach number of $2\mathrm{.}5$ at a standard altitude of $36,000ft.$ Use consistent English Engineering Units $(l{b}_f,$slug,$ft,s).$