北京航空航天大学学报 ›› 2000, Vol. 26 ›› Issue (6): 684-687.

• 论文 • 上一篇    下一篇

后掠翼身干扰区流动显示

张华1, 吕志咏1, 袁辉靖2   

  1. 1. 北京航空航天大学 飞行器设计与应用力学系;
    2. 北京大学 力学与工程科学系
  • 收稿日期:1999-10-18 发布日期:2010-11-19
  • 作者简介:张 华(1958-),男(布依族),贵州贵阳人,副教授,100083,北京.
  • 基金资助:

    国家部委基金资助项目

Flow Visualization of Swept Wing/Body Junctions

ZHANG Hua1, Lü Zhi-yong1, YUAN Hui-jing2   

  1. 1. Beijing University of Aeronautics and Astronautics, Dept. of Flight Vehicle Design and Applied Mechanics;
    2. Peking University, Dept. of Mechanics and Engineering Science
  • Received:1999-10-18 Published:2010-11-19

摘要: 在水槽中利用激光片光源及荧光素纳染色液显示方法,研究了圆柱、机翼与平板交接区及后掠圆柱、后掠机翼变迎角情况下的干扰流场结构、特性及参数影响规律.实验结果表明,除Re数之外,模型迎角、后掠角等参数对干扰区马蹄涡特性有很大影响.研究发现后掠圆柱及后掠机翼在一定条件下存在一类既不同于马蹄涡也不同于卡门涡的空间稳定发展的三维旋涡系即背涡.背涡在一定的迎角及后掠角条件下发生破裂;机翼背涡随迎角变化具有不同于圆柱背涡的特点.讨论了干扰背涡产生的机制及其与马蹄涡的相互关系.此外还给出了对于干扰流场典型截面的PIV测量结果.

Abstract: Flow visualization test of swept wing/body junctions has been performed with laser light sheet technique and sodium-fluorescence dyed liquid method in the water channel of BUAA. The results show that in addition to Reynolds number, the angle of attack and the swept angle are also very important parameters that influence the horseshoe vortex characteristics in the juncture zone. It is found that there exists a new kind of 3-D steady vortex system——back vortex, which is different from the horseshoe vortex and the Karman vortex. The back vortex exists for both swept cylinder and swept wing conditions. It comes from the rear part of the junctions and extends into space. The back vortexes will breakdown under certain angle of attack and the swept angle. The characteristic of swept wing back vortex is different from that of swept cylinder back vortex. The forming mechanism of this back vortex system and its relationship with horseshoe vortex system are also discussed. Finally, some typical sections of the junctions have been measured using PIV technique.

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