尖前缘翼干扰区的壁面压力和热流率分布  

Distributions of Wall Pressure and Heating Rate in Sharp Fin-Induced Shock Wave/Turbulent Boundary Layer Interactions

作　　者：王世芬[1] 王宇[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》1995年第4期447-451,共5页Acta Aerodynamica Sinica

基　　金：国家自然科学基金

摘　　要：本文给出Ｍ＿∞＝７．８和６．７２，Ｒｅ＝３．５×１０￣７／ｍ和５．４×１０￣７／ｍ气流绕迎角为２０°、３０°和３５°尖前缘翼运动时，平板锥型干扰区的壁面压力和热流率分布。结果表明：（１）平板锥型干扰区的特征几何尺度与无粘激波角β＿０和翼迎角α相关，而壁面压力和热流率的峰值与法向马赫数Ｍ＿ｎ相关。（２）翼面压力和热流率分布由于受拐角涡影响，前者在翼根部呈波谷状，而后者呈波峰状，影响尺度与翼前缘处来流边界层厚度有关。This paper presents the distributions of wall pressure and heating rate on the flat plate and fin surface for 20°,30° and 35°un-swept sharp fins at freestream Mach numbers of 7.8 and 6.72, unit Rey-nolds number of 3.5× 10￣7/m and 5.4× 10￣7/m.The results show that the characteristic geometry scales of the conical interaction region can be correlated with inviscid shock angleβ_0 and attack angle α. The peak values of wall pressure and heating rate can be simply accounted for by M_n,the component of freestream Mach number in the direction normal to shock wave.On the fin surface there are pronounced minimum pressure and maximum heating rate near the corner, caused by a corner vortex.The upward extent of disturbance has relation to the incoming boundary layer thickness.

关 键 词：高超声速 分离流 前缘翼 壁面压力 热流率 

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]