| 飞船高超声速粘性绕流的数值模拟 |
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| 引用本文： | 贺国宏,张涵信.飞船高超声速粘性绕流的数值模拟[J].空气动力学学报,1994,12(3):252-261. |
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| 作者姓名： | 贺国宏 张涵信 |
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| 作者单位： | 中国空气动力研究与发展中心 |
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| 摘 要： | 本文采用稳式ＮＮＤ格式，通过求解三维薄层近似Ｎａｖｉｅｒ－Ｓｔｏｋｅｓ方程，数值模拟了飞船高超声速粘性流场。在计算中充分考虑了网格雷诺数和网格分布对计算结果的影响，不但得到了满意的表面压力、热流分布和流场的物理量分布，而且得到与实验观察一致的表面油流图像和分离结构。
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| 关 键 词： | 高超音速流动 分离流动 宇宙飞船 |
Numerical Simulation of Hypersonic Viscous Flows over Capsule-Type Vehicles |
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| He Guohong, Zhang Hanxin.Numerical Simulation of Hypersonic Viscous Flows over Capsule-Type Vehicles[J].Acta Aerodynamica Sinica,1994,12(3):252-261. |
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| Authors: | He Guohong Zhang Hanxin |
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| Institution: | China Aerodynamics Research and Developtment Centter |
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| Abstract: | The implicit NNDschemc developed by Professor ZhangHanxin is used to solve the thin-layer three-dimensional Number-Stokesequations.The influence of the CellRcynolds Number on the stagnationpoint heat transfer rate is seriously considered,and then the hypersonicfore-and afterbody flow fields over capsule-type vehicles are simulated.Using the appropriately clustered mesh,the numerical results predict thedistributions of the pressure and the heat transfer rate. The complicatedtopology of three-dimensional separations on the afterbody are also pre-sented.It is shown that these numerical results agree well with existingnumerical solutions and experiment data. |
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| Keywords: | hypersonic flow space vehicles NND scheme separationflow difference methods |
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