A shock wave/boundary layer interaction is a common phenomenon in supersonic (hypersonic) flows, and it usually occurs in an airbreathing propulsion system. It induces a large separation bubble and a local peak heat flux, and means of controlling it have attracted increasing attention. In this paper, the three-dimensional Reynolds-averaged Navier-Stokes equations and the shear stress transfer k-ω model are employed to study the flow control mechanism of a micro vortex generator in a supersonic flow with a freestream at a Mach number of 2.9; the influence of the streamwise location is taken into consideration. At the same time, due to the size of the separation bubble induced by the shock wave/boundary layer interaction, the total pressure recovery coefficient and the wall heat flux density are used to evaluate the control performance. The results show that the size of the separation bubble is greatly reduced, the area of the separation bubble is reduced by 29.63%, and its volume is reduced by 63.27%. However, this entails a total pressure loss and a large peak heat flux, and this should be dealt with through multi-objective design optimization approaches.
The increased and unstable flow field backpressure will cause problems such as the non-starting of the inlet tract, and the widespread shock wave/boundary layer interaction (SWBLI) phenomena in the supersonic flow field exacerbates these problems. Hence, a powerful flow control system is required. In this paper, backpressure is introduced at the flow field outlet, and the effect of different backpressure ratios on the flow field is explored. An adaptive control scheme is also developed by using the optimized secondary flow recirculation configuration. The three-dimensional implicit Reynolds Averaged Navier–Stokes equations are utilized for numerical simulation of the flow field. The results show that the adaptive control of the secondary recirculation jet has a positive control effect on the SWBLI of the flow field when backpressure is applied. Moreover, the adaptive control mechanism under the backpressure condition is analyzed, which is applicable to different backpressure flow fields with Mach numbers between 2.5 and 3.5.
The shock wave/turbulent boundary layer interaction (SWBLI) is widely observed in the supersonic flow field, and it has many adverse effects on the flow field, while the investigation on its control has received more and more attention. In this paper, the secondary recirculation configuration is optimized based on our previous investigations. Six secondary recirculation configurations are designed, and the adaptive control schemes for these configurations are developed for the incoming Mach number being 2.5, 3.0, and 3.5. The three-dimensional implicit Reynolds Averaged Navier-Stokes (RANS) equations coupled with the two-equation shear stress transport (SST) k- ω turbulence model are used to perform simulation calculations for each case. An evaluation approach is developed for the control performances, and it is utilized to perform quantitative calculations and analyze the control effects of the separation zone volume, total pressure recovery coefficient, and peak wall heat flux for different configurations in order to find the best control configuration with the wide operation Mach numbers. At last, a configuration with grid pattern distribution of suction holes, each with a length and width of 2.828 mm, uniformly distributed in the range of 52 < x/D < 124 and -12 < z/D < 12, is obtained for the shock wave/turbulence boundary layer control studied in the current study.
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