| 高超声速粘性激波层高雷诺数流场的数值求解方法 |
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| 引用本文： | 刘执明,吴其芬.高超声速粘性激波层高雷诺数流场的数值求解方法[J].空气动力学学报,1989,7(3):291-297. |
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| 作者姓名： | 刘执明 吴其芬 |
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| 作者单位： | 国防科技大学
(刘执明)，国防科技大学(吴其芬) |
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| 摘 要： | 本文将拉伸变换引入Hosny的高超声速粘性激波层的数值求解方法中,数值计算结果与Little所给出的实验结果相符合。从而不论在雷诺数范围上,或在后身流场的推进计算上,本方法均比Hosny原方法有明显改进。
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| 关 键 词： | 高超声速 流场 粘性流 激波层 |
THE NUMERICAL METHOD FOR SOLVING THE HIGHREYNOLDS HYPERSONIC VISCOUSSHOCK LAYER |
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| Liu Zhiiming Wu Qifen.THE NUMERICAL METHOD FOR SOLVING THE HIGHREYNOLDS HYPERSONIC VISCOUSSHOCK LAYER[J].Acta Aerodynamica Sinica,1989,7(3):291-297. |
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| Authors: | Liu Zhiiming Wu Qifen |
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| Institution: | National University of Defence Technology |
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| Abstract: | In the present paper a mesh stretching transformation is introduced into the numerical integrating method for the hypersonic vis-cous shock layer presented by Hosny, M. W10]. The present method is a little advanced than the Hosny's method in that it can solve the hyper-sonic viscous shock layer flow field for more high Reynolds number and it can march more far along the slender blunt bodies. The numerical results obtained here compare well with the experimental results of Little12]. |
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| Keywords: | high Reynolds number mesh stretching transformation hypersonic flow viscous shock layer |
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