| 76°/40°双三角翼前缘涡破裂及其控制实验研究 |
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| 引用本文： | 王晋军,刘激瀛,薛启智.76°/40°双三角翼前缘涡破裂及其控制实验研究[J].北京航空航天大学学报,2001,27(1). |
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| 作者姓名： | 王晋军 刘激瀛 薛启智 |
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| 作者单位： | 北京航空航天大学 飞行器设计与应用力学系 |
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| 基金项目： | 高等学校博士学科点专项科研项目，国家部级科研项目 |
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| 摘 要： | 流动显示结果表明，喷流能有效地推迟双三角翼前缘涡的破裂，且随着攻角的增大，前缘涡破裂位置逐渐推后，喷流极大地改善了大攻角情况下前缘涡的非对称破裂特性，能有效地克服可能出现的机翼的“摇滚”现象.另外，后缘喷流可以减弱乃至消除前缘涡混掺现象的发生，进而有利于飞行器的操纵.
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| 关 键 词： | 涡旋流动 流动显示 喷流试验 双三角翼绕流 流动控制 |
Experimental Studies on Leading-Edge Vortex Breakdown and Control of Flow over 76°/40° Double Delta Wing |
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| WANG Jin-jun,LIU Ji-ying,XUE Qi-zhi.Experimental Studies on Leading-Edge Vortex Breakdown and Control of Flow over 76°/40° Double Delta Wing[J].Journal of Beijing University of Aeronautics and Astronautics,2001,27(1). |
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| Authors: | WANG Jin-jun LIU Ji-ying XUE Qi-zhi |
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| Abstract: | The flow visualization techniques has been used to investigate the effects of trailing-edge jets on the leading-edge vortex breakdown and its control of flow over a 76°/40° double Delta wing. The experimental results indicate that the trailing-edge jets can delay the leading-edge vortex breakdown efficiently, and this delay increases with the angle of attack. The trailing-edge jets can greatly improve the asymmetrical characteristics of the leading-edge vortex breakdown at large angle of attack, and the possible occurrence of “rock” phenomenon may be overcome. In addition, the trailing-edge jets may weaken or even eliminate the mixing phenomenon of the leading-edge vortex, which is in advantage of the flight control of aircraft. |
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