Wing design for supersonic transports using integral equation method

摘要

The applicability of an inverse problem solver systemized with other computational tools was demonstrated. The demonstrations have been conducted on the aerodynamic design of wings for two Japanese scaled experimental Supersonic Transport (SST) models. The first model is of a clean configuration which has no propulsion system while the second one has two big engines. The design has been primarily performed by the system of Computational Fluid Dynamics (CFD) tools, which are a Navier-Stokes equation solver, geometry defining software, an inverse problem solver and interface programs between each solver and another. Because of the challenging concept of the wing design for the SSTs, such as a Natural Laminar Flow wing, a new design method was needed. Then, an integrated CFD design system of residual-correction loop was developed utilizing the existing inverse problem solver which solved integral equations. Though the inverse problem solver was based on low order approximation of flow equations, the design system worked successfully for the first model in Navier-Stokes flows. As for the second one that was a fairly complicated design problem affected by a big propulsion system, the preliminary stage of the wing design finished. Through both results, it was shown that we attained synergy effect of each CFD tool by systemizing and the design system using the simple inverse problem was promising for complex three-dimensional design.