LAUSR

The shock wave/boundary layer interaction phenomenon is harmful to the performance improvement of the hypersonic vehicle, and the microjet flow control scheme was introduced to minimize the total volume of the separation bubble and maximize the total pressure recovery coefficient simultaneously. In this paper, the dual microjets for the shock wave/boundary layer interaction control are optimized by the range analysis approach, and their flow field structures are explored and compared comprehensively. The obtained results show that the range analysis approach is a method for the optimization of the dual microjets, and the optimized models show better performances when compared with the basic configurations. In the range considered in this study, Case 5a obtained by taking the minimum total volume of the separation bubble as the target has a large total pressure loss, and its total volume of the separation bubble is 960.65 mm2, with its total pressure loss being 15.38%.