Need help answering this problem

M,=3 @ 5o @ @ 7 R / A supersonic airfoil has equilateral triangular shape with tip angles of 5. It is placed at an angle of attack of 5 against an airstream with M; = 3. (a) Sketch the wave pattern around the airfoil. (b) Use the exact (shock-expansion) theory to find the static pressure ratio p/p; in regions 2, 3, and 4. () Using linear theory, find an approximate value for static pressure ratio p/p; in regions 2, 3, and 4. (d) To compute the lift and drag of the airfoil, we first calculate the force (per unit span) acting on each airfoil surface (since these are pressure forces, they act normal to the surface). Summing the force components normal to flow direction gives the lift L. Summing the force components parallel to flow direction gives the drag D). The non-dimensional lift and drag coeflicients are L L Cp = e = o smUic 21 Mic D D = g = 3 2 smUic syYmMic where is the chord length. Compute C; and C; based on (i) the exact theory and (ii) the linear theory