Simulation of parallel blade-vortex interaction using a discrete vortex method

Numerical results are presented for two-dimensional vortex-aerofoil interac tion using a grid-free discrete vortex method. The effects of the passing v ortex on the surface pressure distribution and hence the aerodynamic force and moment of the aerofoil are examined in detail for a variety of interact ion geometries. For some head-on interaction cases, vortex-induced local fl ow separation is also predicted on the aft part of the aerofoil surfaces. E xtensive comparisons are made with other numerical results and the results from the Glasgow University BVI wind-tunnel test, which show good agreement .