北京航空航天大学学报 ›› 2001, Vol. 27 ›› Issue (1): 51-53.

• 论文 • 上一篇    下一篇

76°/40°双三角翼前缘涡破裂及其控制实验研究

王晋军, 刘激瀛, 薛启智   

  1. 北京航空航天大学 飞行器设计与应用力学系
  • 收稿日期:1999-08-24 出版日期:2001-01-31 发布日期:2010-11-19
  • 作者简介:王晋军(1963-),男,山西寿阳人,教授,100083,北京.
  • 基金资助:

    国家教育部博士点基金资助项目(9713); 国家部委基金资助项目

Experimental Studies on Leading-Edge Vortex Breakdown and Control of Flow over 76°/40° Double Delta Wing

WANG Jin-jun, LIU Ji-ying, XUE Qi-zhi   

  1. Beijing University of Aeronautics and Astronautics, Dept. of Flight Vehicle Design and Applied Mechanics
  • Received:1999-08-24 Online:2001-01-31 Published:2010-11-19

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.

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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