<p>The supersonic counter-rotating compressor is considered as a crucial technical path for engine thrust-to-weight improvement. A design method of negative curvature blade profile with constant pressure gradients in the upstream influence region of the shock wave and boundary layer interaction is adopted. This method uses a counter-rotating compressor rotor as the research model to suppress the boundary layer separation induced by the internal extension shock wave at the leading edge of the supersonic compressor rotor. The influence mechanism of local blade profile curvature changes at the design point and the stall inception point on blade surface load, shock wave boundary layer interaction, and radial transport of boundary layer fluid is analyzed by using numerical simulation methods. The results show that at the design point, the root of the trailing shock wave on the suction surface of the rotor blades of the modified compressor has been replaced by a group of compression waves and a weak incident shock wave. The process of generating a significant pressure rise by shock waves is divided into two stages, which reduces the local strong reverse pressure gradient, decreases the disappearance of flow separation, and improves the isentropic efficiency of the compressor rotor as well as the total pressure ratio. At the near-stall point, the detached shock wave is located at the inlet of the blade passage and induces boundary layer separation on the suction surface. The wall elevation formed by the negative curvature of the blade surface has a certain inhibitory effect on the separated fluid. Moreover, since the modification range of the blade profile is within the boundary layer thickness scale, the increase in flow resistance caused by this is almost negligible.</p>