| 引用本文: | 杨晓辉,王承尧.一种求解飞行器廓线间断处超音速复杂流场的方法.[J].国防科技大学学报,1997,19(3):61-64.[点击复制] |
| Yang Xiaohui,Wang Chengyao.An Approach to the Supersonic Complex Fluid Field Calculation of Vehicle at the Discontinuous Profile Lines[J].Journal of National University of Defense Technology,1997,19(3):61-64[点击复制] |
|
| |
|
|
| 本文已被：浏览 6281次 下载 5986次 |
| 一种求解飞行器廓线间断处超音速复杂流场的方法 |
| 杨晓辉, 王承尧 |
|
(国防科技大学 航天技术系 湖南 长沙 410073)
|
| 摘要: |
| 用有限体积法求解三维完全气体的Navier-Stokes方程, 并将通量守恒的分区计算方法和B-L湍流模型修正结合在一起, 捕捉到了间断处的分离涡、激波、膨胀波等流场信息。 |
| 关键词: 飞行器廓线间断, 分离涡, 激波, 分区网格, 湍流 |
| DOI： |
| 投稿日期：1996-05-20 |
| 基金项目: |
|
| An Approach to the Supersonic Complex Fluid Field Calculation of Vehicle at the Discontinuous Profile Lines |
| Yang Xiaohui, Wang Chengyao |
|
(Department of Astronautic Technology, NUDT, Changsha, 410073)
|
| Abstract: |
| Finite-Volume method was used to solve the three-dimensional Navier-Stokes equations of ideal gas, and combine flux conservative patched method and B-L turbulence model correction to study this problem, capturing fluid field informations such as separation vortex, shock wave, expansion wave. |
| Keywords: discontinuous profile lines of vehicles, separation vortex, shock wave, patched-grid, turbulence |
|
|
|
|
|
