| 曲形槽道ABLE概念在超声速翼型减阻中的应用 |
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| 引用本文： | 耿云飞,闫超.曲形槽道ABLE概念在超声速翼型减阻中的应用[J].空气动力学学报,2010,28(1). |
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| 作者姓名： | 耿云飞 闫超 |
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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： | 发展了曲形槽道人工钝前缘(Artificially Blunted Leading Edge,ABLE)的概念并将其应用于菱形超声速翼型减阻,阐述了曲形槽道ABLE构型的优点以及减阻原理,采用数值模拟方法对不同参数的ABLE翼型进行了对比研究,数值结果表明,槽道参数设计合理时,能以较小的驻点热流值增量为代价,使本文所讨论翼型的最大升阻比提高20%左右;初步总结了曲形槽道ABLE用于超声速翼型减阻的规律。
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| 关 键 词： | 人工钝前缘 曲形槽道 超声速 翼型 减阻 |
Application of curved channel ABLE conception to supersonic airfoil drag reduction |
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| GENG Yun-fei,YAN Chao.Application of curved channel ABLE conception to supersonic airfoil drag reduction[J].Acta Aerodynamica Sinica,2010,28(1). |
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| Authors: | GENG Yun-fei YAN Chao |
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| Institution: | National laboratory for Computational Fluid Dynamics/a>;Beijing University of Aeronantics and Astronautics/a>;Beijing 100191/a>;China |
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| Abstract: | This paper applies curved channel ABLE(Artificially Blunted Leading Edge) to a diamond supersonic air-foil for drag reduction,and explains the advantages and drag reduction principle of the curved channel ABLE configuration.Studies of ABLE airfoils with different parameters are made using numerical simulation method.The outcomes indicate that,with a slight increase of stagnation heat transfer,the highest lift-to-drag ratio increases about 20% if it is designed reasonable.The deflection direction of the chan... |
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| Keywords: | ABLE curved channel supersonic airfoil drag reduction |
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