Abstract
The aerodynamic shape of a wing for a SST has been designed by a supersonic inverse method. This method handles a wing-fuselage configuration and provides the section geometry at every span station of the wing. The design system consists of an inverse problem solver and a Navier-Stokes simulation code. The design procedure is based on the iterative residual correction concept with which a baseline shape is successively modified. The inverse problem solver determines the geometrical correction value for the current wing to be updated. The simulation provides the pressure distribution along the updated current wing surface. The residual is defined as the difference between the target and the current pressure distributions. The process is iterated until the pressure distribution of the modified wing geometry converges to a specified target pressure distribution. By means of the present design method, a better wing for the SST has been designed than that by the traditional linear theory.
