Department of Aerospace Engineering, University of Glasgow
Abstract
Numerical results are presented for two-dimensional vortex-aerofoil interaction using a grid-free
discrete vortex method. The effects of the passing vortex on the surface pressure distribution
and hence the aerodynamic force and moment of the aerofoil are examined in detail for a
variety of interaction geometries. For some head-on interaction cases, vortex-induced local
flow separation is also predicted on the aft part of the aerofoil surfaces. Extensive comparisons
are made with other numerical results and the results from the Glasgow University BVI windtunnel
test, which show good agreement
