空气动力学学报2012，Vol.30Issue(6)：761-766,6.
咽式高超声速进气道试验与计算研究
Experimental and numerical study on hypersonic jaws inlet
摘要
Abstract
The flow over a hypersonic jaws inlet was experimentally and numerically studied. Flow characteristics in hypersonic jaws inlets have been presented by theoretic, experimental and numerical methods. The experimental method and technology of high-contraction-ratio jaws inlet in hypersonic wind tunnel was given to acquire the experimental data of starting inlet. Numerical results demonstrated that a pair of three-dimensional vortical structures for mixing enhancement was formed as a result of the pitch and yaw shock waves/boundary-layer interactions, and the mechanism for the 3D flow structure was explained by analyzing the streamlines distributions in boundary layer around the cowl.关键词
高超声速内收缩进气道/高超声速风洞试验/激波-附面层干扰Key words
hypersonic inward turning inlet/ hypersonic wind tunnel test/ shock wave/boundary-layer interaction分类
航空航天引用本文复制引用
王成鹏,董昊,程克明..咽式高超声速进气道试验与计算研究[J].空气动力学学报,2012,30(6):761-766,6.基金项目
国家自然科学基金(90716013)；南京航空航天大学基本科研业务专项科研项目资助(56XZA11060) （90716013）
江苏高校优势学科建设工程资助项目 （）
