A Supersonic Inverse Wing Design Method and Its Application to Japanese SST

摘要

The aerodynamic shape of a wing for the Japanese SST has been numerically designed by a new method. To develop the method, a new inverse problem solver has been devised. The method handles SST wing-fuselage configurations and provides the wing section geometry at every span station. It uses the inverse problem solver and Navier-Stokes simulation. The design target is a natural laminar flow (NLF) wing for the wing-fuselage combination at the speed of M_∞ = 2.0. Several design constraints need to be satisfied. By means of the method, a wing has been designed which has desirable aerodynamic characteristics while using only a small amount of computation time.