Characteristics of bump induced curved shock/boundary layer interaction under the sideslip condition

The simulation method was used to investigate the flow field around the three-dimensional surface bump at designed Mach number 2 under the sideslip condition. Results show that as the sideslip angle increases, the pressure gradient on the windward side increases, and the high pressure center of the bump surface shifts toward the windward side. As a result, the strength of the vortex near the bump leading edge increases,which causes the loss of the total pressure recovery at windward side and finally makes the distortion of bump downstream flow field increase. At the same time, the surface flow topology of the bump shows that the conical similarity of the windward side separation zone increases as the sideslip angle increase, while the separation region on the bump leeward side evolves from a quasi-conical similarity to a quasi-cylindrical similarity gradually.