北京航空航天大学学报 ›› 2008, Vol. 34 ›› Issue (12): 1456-1459.

• 论文 • 上一篇    下一篇

背负式S形进气道流场控制技术

李大伟, 马东立   

  1. 北京航空航天大学 无人驾驶飞行器设计研究所, 北京 100191
  • 收稿日期:2007-12-28 出版日期:2008-12-31 发布日期:2010-09-16
  • 作者简介:李大伟(1979-),男,黑龙江齐齐哈尔人,工程师,david@buaa.edu.cn.
  • 基金资助:

    国家十五预研项目

Improving dorsal S-shaped inlet performance by vortex flow control

Li Dawei, Ma Dongli   

  1. Research Institute of Unmanned Aerial Vehicle, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
  • Received:2007-12-28 Online:2008-12-31 Published:2010-09-16

摘要: 通过在已有的S形进气道入口第一弯底部布置一系列类机翼的导流叶片,来改善出口流场分布,抑制旋流,减小出口畸变指数.分析了导流叶片的高度、弦长、攻角和安装位置(轴向位置和横向位置)这几个参数对S形进气道内流的影响,并利用计算流体力学(CFD)方法针对导流叶片的组数展开研究,得到最优结果.结果表明,采用优化后的导流叶片,可以有效抑制内流分离,降低S形进气道出口畸变指数,改善流场品质. 这些分析结果对于涡流发生器的设计有一定的指导意义.

Abstract: In order to effectively reduce flow distortion produced in the S-shaped inlet, a computational fluid dynamics (CFD) procedure was used to design vortex generator installations near the entry of the diffuser. Several parameters, i.e. the ratio of generator blade height to local boundary layer thickness, the locating position, angle against the centerline, that characterize the vortex generator array were discussed to determine their effects. Especially the numbers of blades were varied to minimize total pressure distortion by restructuring the development of secondary flow. The results show that by using a properly designed vortex generator array total pressure distortion can be greatly reduced and flow separation can be totally prevented, the vortex generator with 8 pairs of blades reduced the circumferential distortion from 0.11 to 0.09. These results should provide valuable guidance in designing vortex generator installations in the S-shaped inlet.

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