咽式高超声速进气道试验与计算研究

Experimental and numerical study on hypersonic jaws inlet

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.