Supersonic flow past a parabol ie-shaped airfoil constitutes a second-order boundary value problem. The supersonic linearized theory is only val id for calculating the flow wi thout any shocks in the near field. The exact solution in the physical domain of the boundary value problem can be obtained using the supersonic far field nonlinear theory. The solution captures successfully the leading and trai ling curved shocks. It can also be shown that the supersonic far field includes its linear solution in the near field.