<p>This paper examines how variations in the radial distribution of tip winglets affect high-load compressor stage performance. The study modifies the radial distribution by altering tip winglets’ circumferential widest position and radial height, analyzing twelve distinct configurations. These modifications influence the effective flow area within the compressor stage, subsequently changing the shock wave structure on the blade surfaces. The effectiveness of the tip winglet structures in managing the flow field is linked to their ability to achieve aerodynamic balance with complex flow structures, such as leakage flow and shock waves. Furthermore, as the tip winglets extend towards the rotor root, they redistribute fluid, thereby preventing the concentration of low-energy fluid in the radial region. This adjustment significantly improves the internal flow structure of the compressor and enhances flow stability. The findings reveal that the expansion effect of the tip winglets increases simultaneously with their circumferential widest position moving towards the leading edge and their radial initial position extending towards the rotor root. Therefore, there is a maximum stability margin increase of 44.57%. For this study, the optimal circumferential widest position of the tip winglet is located at 25% chord length, with the radial initial position at 80% span.</p>