Aerodynamic Wing Design of NEXST-2 Using Unstructured-Mesh and Supersonic Inverse Problem

An efficient aerodynamic design system is developed and applied to design natural laminar flow wings of the experimental supersonic airplanes of the National Aerospace Laboratory (NAL) in Japan. In the design system developed, an inverse problem solver using integral equations is employed in the design phase, whereas unstructuredmesh computational-fluid-dynamics technology is used in the analysis phase so as to treat full configurations of airplanes efficiently. Interfaces among the design phase, the analysis phase, and the three-dimensional modeling phase are also developed. The rationale for the interface software implementation is described from the viewpoint of a practical aircraft design. The newly developed method has advantages of efficiency and wide applicability to complicated configurations of airplanes. Its capability is demonstrated for the wing design of the NAL NEXST-2 coupled with flow analysis of the full configuration. [PUBLICATION ABSTRACT]