(Solved): A compression wave hits a triangular airfoil in supersonic flow at angle of attack , as shown be ...

A compression wave hits a triangular airfoil in supersonic flow at angle of attack $?$, as shown below. Assume small disturbances and note that $?=\sqrt{M_{?}^2?1}$. (a) Sketch the flow regimes and identify $c_p$ in each region. (b) Determine the lift and drag coefficients on the airfoil.