Suppression of interaction between shock wave and boundary layer for "X" hypersonic inverted inlet

Aiming at suppression of shock wave and boundary layer interaction in two dimensional hypersonic inverted inlet, numerical simulation based on turbulent k-ω SST was performed. A suppression method was adopted to reduce the effects of the interaction shock wave and boundary layer of missile body based on the flow diverter. Inlet performance was compared and flow mechanism was studied with diverter and without diverter. Computational results indicate that the separation was suppressed with diverter, and the performance of inlet aerodynamic was improved effectively by means of this suppression method. Both the total pressure recovery coefficient and the flow coefficient of inlet increase while total drag coefficient for the wall slightly decreases. This is due to the fact that the intensity of the shock wave/ boundary layer interaction behind the diverter was reduced by the strong shear layer flow. In addition, stable transverse vortex behind the diverter is formed. It can be clearly seen that the fluid in the trail vortex is from the flow above the diverter with higher total pressure so that the capability in the transverse vortex on resisting back pressure is enhanced. Meanwhile, the flow suppression is extended along circumferential direction without diverter and this happens with diverter. This partially contributes to the reduction of drag coefficient. Based on results obtained and its mechanism analysis, it can be concluded that this method can be considered to be effective for suppression of the interaction between the shock wave and boundary layer for hypersonic inverted inlet and its suppression mechanism has been revealed.