Three-dimensional curved conical shock wave/plate boundary layer interactions

Three-dimensional curved shock wave/boundary layer interaction with streamwise and spanwise curvatures widely exists in practical aerodynamic design. To explore the effects of composite shock curvatures on boundary layer separation, a canonical model with a cone placed above plate was utilized as a reference. Configurations of straight, convex, and concave conical shock waves inducing the curved conical shock wave/boundary layer interactions were studied, using CFD based on Reynolds-averaged numerical simulation method. The flow structure and separation region of each case were discussed quantitively on the symmetry plane, flat plate, and plane perpendicular to flow direction, respectively. The focus of the analysis was on the characteristic patterns of separation scale variation in the streamwise and spanwise directions, which were observed to consistently change with respect to both directions with alterations in the incident shock wave shape. A simplified control volume model was established to qualitatively discuss the influence source of curved shock waves on separation scales, based on mass conservation equations. The results suggest that the curved shock wave has a holistic effect on separation, which is not solely dependent on the shock foot strength.