F313 航技研小型超音速実験機の CFD 逆問題設計法

概要

論文の詳細を見る
A Computational Fluid Dynamic method is applied to design the wing shape for NAL's experimental supersonic transports (NEXST). The method has successfully designed a natural laminar wing for the first model of the NEXST. The 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 inverse problem solver determines the geometrical correction value for the current wing to be updated. The simulation evaluates the pressure distribution along the wing surface. The system is iterated until the pressure distribution of the modified wing geometry converges to a specified target pressure distribution. By means of the method, a wing of better aerodynamic performance has been designed than that by the traditional linear theory. However, it was not completed to exactly meet the thickness constraint, which conflicted with the given target pressure condition.
日本流体力学会の論文
2001-07-31