| 引用本文: | 柳军,瞿章华.再入飞行器高超声速三维粘性流场的数值模拟.[J].国防科技大学学报,1996,18(2):1-4.[点击复制] |
| Liu Jun,Qu Zhanghua.Numerical Simulation of 3-D Hypersonic Viscous Flowfield over a Capsule[J].Journal of National University of Defense Technology,1996,18(2):1-4[点击复制] |
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| 再入飞行器高超声速三维粘性流场的数值模拟 |
| 柳军, 瞿章华 |
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(国防科技大学 航天技术系 湖南 长沙 410073)
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| 摘要: |
| 用数值方法研究大钝头倒锥体再入飞行器高超声速完全气体有攻角绕流的流场特性。控制方程为完全气体三维Navier-Stokes 方程，数值方法采用激波捕捉的 NND 隐式算法，计算区域为含底部的全流场。文中给出了流场特性和气动力系数，并与实验结果进行了对比。 |
| 关键词: 高超声速，完全气体，三维流场，激波捕捉 |
| DOI： |
| 投稿日期：1995-10-17 |
| 基金项目:国家自然科学基金资助项目 |
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| Numerical Simulation of 3-D Hypersonic Viscous Flowfield over a Capsule |
| Liu Jun, Qu Zhanghua |
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(Department of Aerospace Technology，NUDT，Changsha，410073)
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| Abstract: |
| The three dimensional hypersonic viscous flow of perfect gas over a capsule is calculated numerically. The Navier-Stokes equations are taken as the governing equations. The implicit NND scheme is used for the shock capture. The computation region is involved with the full flowfíeld from the nose to the base. The flowfield properties and the areodynamic force coefficients thus obtained are good compared with the experiment results. |
| Keywords: hypersonic,perfect gas,3-D flowfield,shock capture |
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