Abstract: The residual-correction design method for transonic wings with prescribed pressure distribution developed by Takanashi was modified. In order to guarantee the convergence of the design in supersonic flow, Takanashi method could be modified by introducing some upwind based operator to the governing equation in hyperbolic parts. Results of the redesign of a wing indicate that the improved method can overcome the convergence problem of the original method in supersonic region and then is more practical in engineering application.