Numerical simulation on blowing method for controlling boundary layer interaction in supersonic inlet at different Mach number

In order to study the shock wave/boundary layer interaction control, two-dimensional flat/wedge structure was used to simplify supersonic inlet, and numerical simulation method was used to study the tendency of blowing effect under different flow Mach number. Furthermore, the effects of the blowing total gas pressure, blowing nozzle height and other parameters on the inhibition of boundary layer airflow separation were discussed. Results show that the blowing method can effectively inhibit the flow separation under a range of flow Mach number, and when the flow condition deviates from the design point, the performance of the blowing method degrades as the increase of Mach number. Increasing the blowing pressure or the blowing nozzle height cannot improve the effect of blowing. With increasing the flow Mach number the flow anti pressure ability is enhanced, and flow separation is reduced.