摘要
采用试验和计算方法研究了一种三维曲面内收缩咽式进气道的流场结构。从理论、试验、计算结果中给出了咽式进气道流动特征;提供了大内收缩比进气道在常规高超声速风洞进行试验的方法和技术;并对咽式进气道内偏航激波、俯仰激波、附面层之间的复杂作用产生的三维涡旋流场结构的成因进行了解释。
The flow over a hypersonic jaws inlet was experimentally and numerically studied. Flow char- acteristics 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.
出处
《空气动力学学报》
EI
CSCD
北大核心
2012年第6期761-766,共6页
Acta Aerodynamica Sinica
基金
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)
江苏高校优势学科建设工程资助项目
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
hypersonic inward turning inlet
hypersonic wind tunnel test
shock wave/boundary-layer in- teraction
