The influence of vortex strength 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 vortex strength on the aerodynamic coefficients and acoustic field. It was observed that the vortex strength influences both, the aerodynamic coefficients and aeroacoustic field. The amplitudes of aerodynamic coefficients increase with the increase of vortex strength. Also the SPL values associated with BVI increase with the the increase of the vortex strength.