北京航空航天大学学报 ›› 2007, Vol. 33 ›› Issue (01): 1-4.

• 论文 •    下一篇

后掠翼对细长体中段大迎角绕流的影响

李国辉1, 邓学蓥2   

  1. 1. 空军航空大学 军事仿真技术研究所, 长春 130022;
    2. 北京航空航天大学 航空科学与工程学院, 北京 100083
  • 收稿日期:2005-12-21 出版日期:2007-01-31 发布日期:2010-09-19
  • 作者简介:李国辉(1966-),男,湖南永兴人,讲师,ghleebh0368@sina.com.cn.
  • 基金资助:

    航空基础科学基金资助项目(02A5148)

Influence on flow around mid-part of slender at high AOA by sweep wing

Li Guohui1, Deng Xueying2   

  1. 1. Military Simulation Technology Institute, Aviation University of Air Force, Changchun 130022, China;
    2. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
  • Received:2005-12-21 Online:2007-01-31 Published:2010-09-19

摘要: 采用在细长体顶点处添加扰动块的方式使细长体的绕流具有确定性.研究了在大迎角下,后 掠翼对细长体绕流结构和气动力特性的影响.实验结果表明,在30°迎角时,细长体中段背 风侧的流动和压力分布受到后掠翼与头部背涡的双重控制.在迎角α=40°~60°范围内 , 后掠翼对细长体中段绕流起主控作用,使细长体中段背风侧流动呈现完全分离流状态,使得 中段背风侧的压力分布保持为均值.

Abstract: The flow around a slender was fixed in this way which a tiny pert urbation was located on the nose of the slender. The influence on flow str u cture and aerodynamic of a slender by sweep wing at high angle of attack was studied. The experimental results indicate that at angle of attack 30°,the fl ow and pressure distribution of mid-part leeside of a slender are dominated by sweep wing and forebody vortices. At angles of attack α=40°~60°, sweep wing dominates the flow around the mid-part of a slender only, and the flow of mid-p art leeside of a slender becomes full separate flow, the pressure distribution o f mid-part leeside of a slender retains constant.

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