does anyone know, how I can find a transonic airfoil (high subsonic, Ma=0.88) with a high critical mach number?
I know that if I know c,0,min = minimal pressure coefficient of the airfoil, then I can calculate the critical mach number.
But when I use Xfoil for plotting the pressure distribution, I only get a nice picture, but I can not write out the data for the pressure distribution. otherwise I could determine the critical mach number.
Maybe someone has some hints for me?