A novel technique regarding the reduction of the influence of helicopter blade-vortex interaction on the aerodynamic coefficients is proposed. The proposed technique is based on the idea of injecting air at the leading edge of the blade to alter the characteristics of the vortex. The numerical investigations are performed using the large-eddy simulation (LES) approach. The simulations were performed for a Reynolds number, Re = 1.3 × 10 6, based on the NACA0012 airfoil chord and free-stream velocity. The present study shows that using the leading edge air mass injection (LEAMI) concept, the influence of blade-vortex interaction on the aerodynamic coefficients is significantly reduced.