超声速边界层三维扰动引起小激波的数值研究  

A numerical study for the generation of shocklet by 3-D disturbances in supersonic boundary layer

作　　者：叶兴福[1] 方一红[1] 

机构地区：[1]天津大学力学系,天津300072

出　　处：《空气动力学学报》2007年第3期281-286,共6页Acta Aerodynamica Sinica

基　　金：国家自然科学基金和重大研究计划资助项目(批准号:19802013;10172066)

摘　　要：通过直接数值模拟的方法,研究了M=4.5的超声速边界层中三维扰动的演化。以某一剖面为入口,加入一个及一对三维T-S波,发现随展向波数的增加,扰动幅值的增长率逐渐减小,证实了M=4.5的超声速边界层中,当三维扰动达到一定幅值时会有小激波出现,为建立可压缩流动稳定性理论提供了依据。Numerical simulation was used to investigate the evolution of 3-D disturbances in a supersonic boundary lay er at M = 4.5, with different spanwise wave numbersβ. At a chosen location, a T-S wave and a couple of T-S waves werefed into the flow field. It was found that when β increased, the growth rate of the disturbance decreased. Shcoklet was found when the disturbance amplitude reached a certain value. Two judgments were employed to detect the shocklet When β〉 1, no shocklet could be found in these two cases.

关 键 词：超声速边界层 T-S波 小激波 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]