| 一种求解飞行器廓线间断处超音速复杂流场的方法 |
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| 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. |
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| 作者姓名： | 杨晓辉 王承尧 |
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| 作者单位： | 国防科学技术大学航天技术系 |
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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
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| 关 键 词： | 飞行器廓线间断，分离涡，激波，分区网格，湍流 |
| 收稿时间： | 1996/5/20 0:00:00 |
An Approach to the Supersonic Complex Fluid Field Calculation of Vehicle at the Discontinuous Profile Lines |
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| Yang Xiaohui and 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. |
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| Authors: | Yang Xiaohui and Wang Chengyao |
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| Institution: | Department of Astronautic Technology, NUDT, Changsha, 410073;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. |
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| Keywords: | discontinuous profile lines of vehicles separation vortex shock wave patched grid turbulence |
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