马赫数对后掠激波和湍流边界层干扰特性的影响  

Effects of Mach Number on Surface Features of Interaction Between Swept Shock and Turbulent Boundary Layer

作　　者：王宇[1] 王世芬[1] 

机构地区：[1]中国科学院力学研究所

出　　处：《空气动力学学报》1994年第3期313-319,共7页Acta Aerodynamica Sinica

基　　金：国家自然科学基金

摘　　要：本文介绍了尖前缘翼诱导激波和湍流边界层干扰流场壁面特性，着重强调马赫数影响。给出２．０≤Ｍ＿∞≤８．２、α≤３５°分离流场中，锥型干扰区内主分离线和再附线位置与无粘激波角β和迎角α的相关式，证实无粘条件是控制锥型区尺度的主要因素。而高超声速与超声速干扰流中二次分离随激波强度的不同发展，表明干扰流场的细致结构与可压缩性有关。This paper presents the surface characteristics of the inter-action between shock wave and turbulent boundary layer induced by sharp fin with emphasis on Mach number effects.The positions of primary separation lines and attachment lines in conical seoaration flow field were well correlated with the inviscid shock wave angle and attack angle under the conditions of 2.0≤M_∞≤8.2 and a≤35°. Again, inviscid paran1eters provcd of the main factors dominating the scales of conical interaction zone. The different developments of secondary separation with the strength of shock wave between hypersonic and supersonic inter-action fields show that the delicate structures of the flow field are affected by compressibility.

关 键 词：分离流动 激波 飞机 高超音速流动 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程]