| 高超声速前缘空腔数值模拟研究 |
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| 引用本文： | 耿云飞,阎超.高超声速前缘空腔数值模拟研究[J].空气动力学学报,2011,29(4). |
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| 作者姓名： | 耿云飞 阎超 |
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| 作者单位： | 北京航空航天大学国家计算流体力学实验室,北京,100191 |
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| 基金项目： | 国家自然科学基金(90716010) |
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| 摘 要： | 介绍了一种前缘空腔高超声速被动流动控制方法并将其应用于轴对称钝锥外形,采用高分辨率的CFD数值模拟方法对不同参数的前缘空腔外形进行了对比研究,阐述了高超声速前缘空腔降低前缘壁面热流的机理,总结了不同空腔参数对空腔外形气动力、热的影响规律。结果表明,合理设计空腔参数可以使空腔外形的前缘壁面热流有较大程度的降低,并且不影响外形的升阻比等气动特性。
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| 关 键 词： | 高超声速 前缘空腔 数值模拟 气动热 |
Numerical simulation on the hypersonic leading edge cavity |
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| GENG Yun-fei,YAN Chao.Numerical simulation on the hypersonic leading edge cavity[J].Acta Aerodynamica Sinica,2011,29(4). |
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| Authors: | GENG Yun-fei YAN Chao |
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| Institution: | GENG Yun-fei,YAN Chao(National laboratory for Computational Fluid Dynamics,Beijing University of Aeronautics and Astronautics,Beijing 100191,China) |
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| Abstract: | Hypersonic flow over the nose of a blunt body with a forward-facing cavity is examined.Comparison analysis is carried out using high resolving CFD numerical simulation method and the mechanism of the cavity heat flux reduction is explained.Operation rules of the different parameters of the cavity are summed up.The results show well designed cavity shape can greatly decrease the leading edge heat flux without affecting the configuration lift-to-drag character. |
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| Keywords: | hypersonic cavity numerical simulation aerodynamic heating |
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