| 超临界翼型Gurney襟翼增升实验研究 |
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| 引用本文： | 李亚臣,王晋军,樊建超,张林.超临界翼型Gurney襟翼增升实验研究[J].北京航空航天大学学报,2003,29(6):471-474. |
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| 作者姓名： | 李亚臣 王晋军 樊建超 张林 |
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| 作者单位： | 1.北京航空航天大学 飞行器设计与应用力学系 |
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| 摘 要： | 在FL-21风洞中进行了高速情况下Gurney襟翼对超临界翼型增升实验研究.0.5%C、1.0%C、1.5%C和2.0%C高度的Gurney襟翼分别使翼型最大升力系数提高了6.0%、12.4%、21.7%和22.3%,其中,1.5%C高度的Gurney襟翼使翼型获得了33.2%的最大升阻比增量.其增升机理则是由于Gurney襟翼前表面压力增强,而其下游底部吸力增加,此压力梯度直接导致翼型总环量增加.
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| 关 键 词： | 超临界机翼 增升装置 风洞试验 Gurney襟翼 |
| 文章编号： | 1001-5965(2003)06-0471-04 |
| 收稿时间： | 2002-03-11 |
| 修稿时间： | 2002年3月11日 |
Experimental Investigation into Effects of Gurney Flaps on Supercritical Airfoil |
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| Li Yachen,Wang Jinjun.Experimental Investigation into Effects of Gurney Flaps on Supercritical Airfoil[J].Journal of Beijing University of Aeronautics and Astronautics,2003,29(6):471-474. |
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| Authors: | Li Yachen Wang Jinjun |
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| Institution: | 1.Dept. of Flight Vehicle Design and Applied Mechanics, Beijing University of Aeronautics and Astronautics2. China Aerodynamic Research and Development Center |
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| Abstract: | An experimental study was performed on a supercritical airfoil in the FL 21 wind tunnel to investigate the lift enhancement effects of the Gurney flaps at high speed conditions. The 0.5% C , 1.0% C , 1.5% C and 2.0% C height Gurney flap increased the maximum lift coefficient by 6.0%, 12.4%, 21.7% and 22.3% separately, and the 1.5% C height Gurney flap increased the maximum lift to drag ratio by 33.2%. The mechanism of this increment in lift is that the pressure upstream of the Gurney flap was increased and the base suction downstream of it was increased also, and this difference in pressure led to an increment in circulation. |
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| Keywords: | supercritical wings high lift devices wind tunnel tests Gurney flap |
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