Shock wave/boundary layer interaction (SWBLI) is a common phenomenon occurring in the supersonic/hypersonic flow fields, and it can constrain the performance of the vehicle. In the current study, a combined control device of a micro vortex generator (MVG) and a secondary recirculation jet is numerically simulated by using three-dimensional Reynolds-averaged Navier-Stokes equations (RANS) coupled with the SST k-ω turbulence model to control the SWBLI flow field at the incoming Mach number being 2.9. From the obtained results, the combination is able to significantly reduce the volume of the separation zone while maintaining little change in the peak heat flux, and the volume of separation bubble is reduced by 87.81%. At the same time, the flow field details and control mechanism are also clearly captured. Six combined models of MVG and secondary recirculation jets are considered, and the design parameters are optimized based on the model with the best control performance. The results of the orthogonal experimental design and the range analysis provide the relationship between the geometric design variables and the performance parameters of the combination.

冲击波/边界层相互作用（SWBLI）是超音速/高超音速流场中普遍存在的现象，会限制飞行器的性能。在目前的研究中，利用三维雷诺平均纳维-斯托克斯方程（RANS）与 SST k-ω 湍流模型耦合，对微涡流发生器（MVG）和二次再循环射流的组合控制装置进行数值模拟，以得到控制传入马赫数为 2.9 的 SWBLI 流场。从所得结果来看，该组合能够显着减小分离区的体积，同时保持峰值热通量变化不大，分离气泡体积减少了87.81%。同时，流场细节和控制机制也一目了然。考虑了MVG和二次再循环射流的6种组合模型，并根据控制性能最佳的模型对设计参数进行了优化。正交实验设计和极差分析的结果提供了几何设计变量与组合性能参数之间的关系。