北京航空航天大学学报 ›› 2000, Vol. 26 ›› Issue (2): 171-173.

• 论文 • 上一篇    下一篇

某型号飞机简化模型大攻角流态初步研究

王晋军, 薛启智, 白涛, 冯亚南   

  1. 北京航空航天大学 飞行器设计与应用力学系
  • 收稿日期:1998-09-02 出版日期:2000-02-29 发布日期:2010-09-27
  • 作者简介:王晋军(1963-),男,山西寿阳人,教授,100083,北京.
  • 基金资助:

    国家部委基金资助项目

Experimental Study on the Flow Patterns of a Simplified Aircraft Model at High Angles of Attack

WANG Jin-jun, XUE Qi-zhi, BAI Tao, FENG Ya-nan   

  1. Beijing University of Aeronautics and Astronautics,Dept. of Flight Vehicle Design and Applied Mechanics
  • Received:1998-09-02 Online:2000-02-29 Published:2010-09-27

摘要: 在水洞中应用染色液流动显示技术对某型号飞机简化模型机头流动状况随攻角和来流速度的演化进行了观测和分析.实验结果表明,在本实验条件下,对于不同的来流速度或雷诺数,每种流动现象所对应的攻角确实发生了变化,说明雷诺数的影响确实存在;另外,对自由转捩条件下,俯仰力矩曲线在α=35°~70°之间很分散的风洞实验结果进行了初步的解释:α=35°基本上对应于边条涡非对称破裂的开始;而α=70°则对应于机头迎风面流动向前、向后的临界点.

Abstract: The dye-injection flow visualization technique has been used to study the changes of flow patterns for a simplified aircraft model with the variation of angles of attack and the incoming flow velocity in a water tunnel. In this experiment, the changes of flow patterns do not have essential difference at several incoming flow velocities, but the variation of the relevant angles of attack occurs indeed, which means that there exists the Re-dependence. Moreover, for the scatter of the experimental pitch-up moment curve in the case of natural transition, the explanation has been made. α=35° corresponds the start of asymmetric breakdown of the strake vortex and α=70° is the critical point of the flow forth and back in the up wind side of the nose.

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