In the present study, a numerical investigation has been undertaken to evaluate lift enhancement technique of an airfoil using leading edge triangular protuberances for low Reynolds number applications. Triangular protuberances of amplitudes (A) 0.03c, 0.06c and 0.11c and wavelengths (W) 0.11c, 0.21c and 0.43c, where c is chord of the airfoil were modelled in SOLIDWORKS. Grid independent study was performed to generate a fine mesh of grid size 10⁶ using sphere of influence technique in ANSYS Mesher. All simulations were performed at a Reynolds number of 10⁵ with SST k-ω turbulence model. The results showed an increase in maximum lift coefficient by 16.5% and delay in stall by up to 8° and the working principle was found to be the generation of stream-wise vortices thereby energizing the boundary layer to delay the separation.