The influence of icing on the helicopter blade-vortex interaction mechanism is investigated using large eddy simulation (LES). The simulations were performed for a Reynolds number of Re = 1.3 × 106 based on the chord of the airfoil (NACA0012). Computations are carried out to investigate the influence of icing on the aerodynamic coefficients. Overall larger amplitudes of aerodynamic coefficients were observed for the case of an iced leading edge when compared with the clean NACA0012 case. Also the blade-vortex interactions are stronger in the presence of ice, resulting in larger oscillations of the aerodynamic coefficients.