The influence of icing effect on the helicopter blade-vortex mechanism of interaction is investigated using large eddy simulation (LES). The simulations were performed for a Reynolds number, Re = 1.3 × 10^6, based on the chord, c, of the airfoil (NACA0012). Computations are carried out to investigate the influence of the icing effect on the aerodynamic coefficients and acoustic field. It was observed that the icing effect influences the aerodynamic coefficients in a specific manner. Larger amplitudes of aerodynamic coefficients were observed for the case of an iced leading edge when compared with the clean NACA0012 case.