Abstract: Menter's SST two-equation turbulence model was used to simulate the interaction between oblique shock wave and axisymmetric boundary layer in a supersonic Mach 3 flow, and the results were analyzed qualitatively and quantitatively. The influence of the wedge angle of the shock generator and the unit Reynolds number of the inflow on the interaction was studied, and the evolution regularity of flow separation caused by parameter variation was summarized. More-over, the two-dimensional cases which are equivalent to the incident shock wave on the central symmetry plane in corresponding three-dimensional cases were also calculated, and the results were compared with the three-dimensional cases. The comparison shows that the interference between oblique shock wave and axisymmetric boundary layer is obviously different from that of two-dimensional cases in terms of wall pressure coefficient, separation vortex, vorticity distribution and so on.