Numerical study of helicopter blade–vortex mechanism of interaction using large-eddy simulation

A novel approach, large-eddy simulation, is proposed for the numerical investigation of helicopter blade–vortex mechanism of interaction. The novel approach overcomes all the issues, posed by the other CFD approaches, associated with the vortex dissipation due to the turbulence modeling (RANS, URANS) and computational limitations of DNS. The influence of vertical miss distance and vortex core size on the helicopter blade–vortex mechanism of interaction is subject of investigation. It was observed that the magnitude of the aerodynamic coefficients decreases with the increase of vertical miss distance and the decrease of vortex core size.