翼身组合体的网格生成及EULER方程数值模拟

采用代数方法中的广义无限插值法生成翼身组合体三维Ｏ－Ｃ型贴体网格。该方法使用双边界法和引入了物面外法向导数以保证物面附近网格正交的处理方法，提高了代数方法生成翼身组合体网格的质量。并用中心格式有限体积法求解跨声速ＥＵＬＥＲ方程，以某翼身组合体模型为例，计算结果与实验符合良好。

Grid Generation and Euler Solver for WingFuselage Configurations

Presented here is a computational procedure for generating a mesh system and for solving the Euler equation for transonic flow around a wing and fuselage combination. In the first part, an algebraic procedure for the generation of boundaryfitted grids about wingfuselage configuration is presented. The grid has six exterior surfaces that map into a computational cube. It is first determined on the six boudary surfaces and then in the interior. Grid clustering technique is used to control the distribution of surface grids on the configuration, the twoboundary technique is used to determine the boundary surface grids that are not on the configuration, and transfinite interpolation is used to determine the interior grid. In order to control grid orthogonality to boundaries (both fuselage and wing surface), we include outward derivatives on certain boundary surfaces in transfinite interpolation. As an example, an O-C type grid for a model of wingfuselage configuration is generated. Secondly, an explicit timemarching finitevolume procedure solves the flow equation. The numerical results are in good agreement with experimental data (Fig.1).