An axial compressor is a fundamental part of a jet engine. The effectiveness of a jet engine’s compressor has a significant impact on that engine’s performance. In the present study, CFD analysis has been performed to determine the effect of sinusoidal leading-edge tubercles on compressor efficiency. Although there have been a number of research on the impact of tubercles on isolated blades, detailed study of their effect on axial compressor rotor blade has not been performed to the best of author’s knowledge. NASA Rotor 37 has been selected for the analysis in this paper. According to the findings, the modified blade will operate more efficiently than the original blade which is maintained for the entire operating range. The increase in efficiency is due to greater pressure at the outlet in modified case. Greater pressure at outlet is credited to modification in shockwave pattern. The shockwave has modified from normal shockwave to oblique shockwave. Oblique shockwave being less detrimental is evident for reduction in aerodynamic loss. Finally, generation of vortices is observed on the near suction side of tubercle model near mid of chord. Vortices formation has resulted in the redirection of the surrounding flow in axial direction thereby reducing the overall losses.