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] |
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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)
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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: |
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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)
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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 |
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