进气道激波-边界层两种控制方法数值模拟研究

In order to reduce the influence of shock waves and boundary layer interactions in high-speed inlet, a numerical simulation is conducted respectively on a 2D inlet with passive blowing and bleeding control and pressure relief control. Firstly, variations of field structure and field quality after applying two control methods at inlet throat, where the large-scale separation zone caused by shock waves-boundary layer interactions exists, are analyzed. It is found that both control methods can reduce the range of separation zone, can decrease the pressure and the speed of reflow in the separation zone, and can improve the uniformity of flow field. Then the performances of two control methods at different Mach numbers are compared. The results show that both control methods can significantly reduce the unstart Mach number and improve the total pressure recovery coefficient, and the pressure relief control has a better performance than the passive blowing and bleeding control, but the latter does not bring the influence of flow loss and static-pressure-ratio reduction.