高超声速二维钝楔边界层参数分析  

Analysis of boundary layer parameters about hypersonic 2D blunt wedge

作　　者：张红军[1] 沈清[1] 

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《空气动力学学报》2015年第2期259-265,共7页Acta Aerodynamica Sinica

基　　金：国家自然科学基金(90816026);航天技术自主研发基金

摘　　要：为了指导二元高超声速进气道型面设计,基于两类高超声速二维钝楔外形,采用高精度CFD方法计算了四种典型工况下二维钝楔边界层参数,分析了前缘半径、壁面温度、压力梯度对边界层参数的影响,得出了边界层位移厚度、边界层总压恢复及壁面压力梯度沿流向的变化规律。研究表明,前缘半径及壁面温度对边界层参数影响较大,在两者一定的情况下,逆压梯度使边界层位移厚度增速放缓,顺压梯度会使边界层位移厚度快速增长。To guide the design of two-dimensional hypersonic inlet surface, boundary layer parameters had been calculated using high precision CFD method for two types of two-dimension- al hypersonic blunt wedges. The effects of leading edge radius, wall temperature and pressure gradient on boundary layer parameters had been analyzed. The streamwise variation of displace- ment thickness, total pressure recovery and pressure gradient had been obtained. The research show that leading edge radius and wall temperature affect boundary layer parameters significant- ly, if fix them, reverse pressure gradient will decelerate the increasing rate of boundary layer, while favorable pressure gradient accelerate the increasing of boundary layer.

关 键 词：高超声速 二维钝楔 CFD 边界层参数 

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]