摘要
A computational procedure is proposed for generating a mesh system and for solving the Euler equation for transonic flow around a wing and fuselage combination. An algebraic procedure for the generation of boundary-fitted grids about wing-fuselage configuration is presented. The grid has six exterior surfaces that map into a computational cube. It is determined on the six boundary surfaces and then in the interior. Grid clustering technique is used to control the distribution of surface grids on the configuration, the two-boundary 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), outward derivatives on certain boundary surfaces is included in transfinite interpolation. As an example, an O-C type grid for a model of wing-fuselage configuration is generated.
| 源语言 | 英语 |
|---|---|
| 页（从-至） | 404-407 |
| 页数 | 4 |
| 期刊 | Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University |
| 卷 | 15 |
| 期 | 3 |
| 出版状态 | 已出版 - 1997 |