I'm trying to write a MATLAB .m-file that will calculate the lift and drag on a supersonic airfoil using only the angle of attack, mach number, and geometry of the airfoil. I'm getting stuck on the oblique shock angle calculation because I cannot find an equation that is solved for the shock angle (beta). Does anyone know what equation I can use for this? Other than that, I think I'm all set. Any help you can give would be greatly appreciated. Thanks!