Utilizing the Reynolds-averaged Navier-Stokes （RANS） method in conjunction with a locally variable γ-Re?θt transition model， an in-depth investigation is conducted on the characteristics of shock wave/boundary layer interaction （SWBLI） for the rotor airfoil. This comprehensive study aims to unravel the intricate features of SWBLI in the vicinity of the rotor blade tip and decipher its implications on both aerodynamic and transition characteristics of rotor airfoils. Furthermore， a detailed exploration into the repercussions of flow parameters on the characteristics of SWBLI is undertaken. The findings reveal that the flow phenomena induced by shock waves and SWBLI， such as deceleration behind the shock wave and flow separation， can reduce the friction drag of airfoils to some extent. However， shock waves and SWBLI themselves can lead to a sharp deterioration in overall drag and lift characteristics， and also cause drastic changes in the moment characteristics. Within the confines of the computational conditions considered in this study， the angle of attack and Mach number have a significant impact on SWBLI. Turbulence intensity also has a certain degree of influence on SWBLI， whereas the Reynolds number has a relatively minor effect. The mechanisms and patterns of influence for each parameter vary considerably.