力学与实践 ›› 2018, Vol. 40 ›› Issue (4): 357-361.DOI: 10.6052/1000-0879-17-363

• 专题综述 •    下一篇

在超声速流动中激波与边界层的干扰特性

刘沛清1), 郭知飞   

  1. 北京航空航天大学陆士嘉实验室,北京 100191
  • 收稿日期:2017-10-25 出版日期:2018-08-08 发布日期:2018-09-11
  • 通讯作者: 1) E-mail: lpq@buaa.edu.cn

INTERFERENCE OF SHOCK AND BOUNDARY LAYER IN SUPERSONIC FLOW

LIU Peiqing1), GUO Zhifei   

  1. Lu Shi Jia Laboratory, Beihang University, Beijing 100191, China
  • Received:2017-10-25 Online:2018-08-08 Published:2018-09-11

摘要:

激波与物面边界层的干扰涉及可压缩流动的稳定性、转捩、分离等问题,直接影响到飞行器的阻力、表面热防护和飞行性能等工程技术问题。首先总结了前人对于激波与边界层的干扰所做的工作,之后重点研究和对比分析了超声速与跨声速流动中,正激波、斜激波以及头部激波对于飞行器层流和湍流边界层的干扰影响。激波强度的不同对边界层干扰作用不同,在强干扰情况下将会引起边界层分离和翼型失速。

关键词:

激波|边界层|飞行器|超声速流动|干扰

Abstract:

The compression boundary layer transition and separation caused by the interference of the shock and the boundary layer directly affect the drag, surface thermal protection and the flight performance of flying vehicles. This paper first reviews the past work on the interference between the shock wave and the boundary layer. And then, the effects of the forward shock, the oblique shock and the head shock on the laminar flow and the turbulent boundary layer of supersonic and transonic flows are studied and compared. The shock waves of different intensities have different effects on the boundary layer.A strong interference is more likely to cause the separation and the airfoil stall.

Key words:

shock wave|boundary layer|aircraft|supersonic flow|interference

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