三面压缩式高超声速进气道流动结构研究  

Research on the flow pattern of three dimensional compression hypersonic inlet

作　　者：肖雅彬[1] 岳连捷[1] 龚鹏[1] 王世芬[1] 陈立红[1] 张新宇[1] 

机构地区：[1]中国科学院力学研究所高温气体动力学重点实验室,北京100080

出　　处：《实验流体力学》2008年第2期64-67,共4页Journal of Experiments in Fluid Mechanics

基　　金：国家自然科学基金(90716014)

摘　　要：采用油滴显示技术结合数值模拟方法对三面压缩式高超声速进气道的流场进行了深入研究。结果揭示由于激波-边界层干扰,三面压缩进气道内存在边界层分离、溢流和三维涡结构等复杂流动现象,尤其是唇口诱发的较大强度的斜激波引起了侧壁和顶面的边界层分离,并在顶面附近形成大尺度的流向涡,造成隔离段内存在明显的分层现象,形成低总压区,需要在进气道设计时对这一现象进行有效控制。Oil flow visualization and numerical simulation were conducted to investigate the flow pattern of a type of three-dimensional compression hypersonic inlet. It is revealed that there are some complicated features inside the inlet flow field due to the shock-boundary layer interaction, such as boundary layer separation, 3-D vortex structure and spillage. The cowl induced strong shock results in the separation of the top and sidewall boundary layer. A large-scale streamwise vortices pair is therefore developed near the top - wall, contributing to the low total pressure region and the flow stratification in the isolator. These phenomena need to be controlled in the hypersonic inlet design.

关 键 词：超声速进气道 流动结构 油滴显示 数值模拟 

分 类 号：V235.11[航空宇航科学与技术—航空宇航推进理论与工程]