Investigation on the adaptive control of shock wave/turbulent boundary layer interaction based on the secondary circulation jets

Abstract

The shock wave/turbulent boundary layer interaction (SWBLI) exists widely in the internal and external supersonic flow field. The interaction of shock waves with turbulent boundary layers will induce serious separation. As a result, the flow field structure changes greatly. This leads to an increase in the flow field instability, total pressure loss, local peak heat flux, and other adverse effects. Current research shows that the secondary circulation jet control is effective in the flow field as a passive control method. In this paper, a new secondary circulation jet configuration for variable Mach number flow is designed and optimized. The flow fields of this configuration with the inlet Mach numbers being 2.5, 3, and 3.5 are studied, and an adaptive control method is proposed. For the numerical simulation of the flow field, the three-dimensional implicit Reynolds Averaged Navier-Stokes (RANS) equations coupled with the two-equation shear stress transport (SST) k-ω turbulence model are chosen. The obtained results show that when the inlet Mach number is in the range of 2.5–3.5, the secondary circulation jet configuration and the adaptive control method have positive effects on reducing the volume of the separation zone and the total pressure loss. Meanwhile, the adaptive control method can also be realized by passive control.