Research On The Separation Of Boundary Layer Induced By Shock Waves

Shock-Wave/Boundary-Layer Interaction is ubiquitous in high-speed flight, occurring in an almost limitless number of external and internal flow problems relevant to aircraft, missiles, and rockets. That the separation of boundary layer induced by shock wave causes a series of problems such as flowing block in air passage is worth studying.The separation of boundary layer induced by different intensity of impinging shock wave generated by 2D wedge/plate configuration is numerically studied in the present paper. Mach number of coming flow and wedge angle determine the intensity of shock wave. The interaction between shock waves, which are varied with Mach number of coming flow and wedge angle, and flat boundary layer is compared and analyzed.The separation conditions of laminar and turbulent boundary layer, the distribution of the parameters along wall, the configuration of shock waves and the change of thickness for turbulent boundary layer behind the interaction plot are illustrated in details. The results show, the thickness of turbulent boundary layer is the crucial factor of the state of separation, besides the intensity of impinging shock wave; the separation makes the thickness of turbulent boundary layer at the downstream zone of impinging point may increase, may equal, or may decrease; the temperature along wall surface at the impinging point may decrease; with the increase of mach number for the coming flow under the condition of the same wedge angle, the relative position of the first and the second reflection shock waves become intersecting instead of paralleling.Based on hereinbefore research, the interaction of shock wave/boundary in inlet for scramjet is simulated here. The study can be used as theoretical reference on relative issues in the field of aviation and aerospace.