| 绕翼型分离流结构的数值研究 |
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| 引用本文： | 刘沛清,邓学蓥.绕翼型分离流结构的数值研究[J].航空学报,1997,18(4):385-389. |
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| 作者姓名： | 刘沛清 邓学蓥 |
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| 作者单位： | 北京航空航天大学五系流体所 |
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| 摘 要： | 利用大涡模拟技术，对不同来流迎角下的NACA0012翼型绕流结构进行了数值模拟，详细地给出了翼型绕流分离流结构随迎角的变化特征和翼型在分离绕流中的气动力参数。在数值模拟中，采用了弱压缩流的控制方程，用贴体坐标技术进行了网格生成。
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| 关 键 词： | 翼型 分离流动 大涡模拟 |
| 收稿时间： | 1996-10-18; |
NUMERICAL STUDY OF SEPARATED FLOWS OVER AN ISOLATED AIRFOIL |
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| Liu Peiqing,Deng Xueying.NUMERICAL STUDY OF SEPARATED FLOWS OVER AN ISOLATED AIRFOIL[J].Acta Aeronautica et Astronautica Sinica,1997,18(4):385-389. |
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| Authors: | Liu Peiqing Deng Xueying |
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| Institution: | Institute of Fluid Mechanics, Beijing University of Aeronautics and Astronautics, Beijing, 100083 |
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| Abstract: | The large eddy simulation is used to solve the separated flows over an NACA0012 isolated airfoil at different angles of attack. Separated flow structures over the isolated airfoil at different angles of attack and corresponding aerodynamic parameters are presented in details. In the numerical simulation, a weakly compressible flow model and the body fitted grid technique are used. |
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| Keywords: | airfoil separated flow large eddy simulation |
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