NUMERICAL STUDY OF THE PARALLEL VORTEX AIRFOIL INTERACTION

Abstract

The effect of a strong vortex interacting with an airfoil flow is investigated numerically. The finite volume method for Euler equations is applied. lnstantanous flow patterns, including pressure distributions along the airfoil and lift coefficients, were calculated for various miss distancees of the vortex passing parallely to the airfoil plane. It has been found that the effects of interaction are much stronger
when the vortex approaching the airfoil accelerates the flow at the pressure surface than in the case when the vortex decelerates the flow at the suction surface. The lift coefficient only slightly depends on the vortex core radius if the velocity induced at the airfoil surface by vortices of various cores is constant. In contrast to this the intensity of the acoustic disturbance produced during the interaction strongly depends on the core radius even for a constant induced flow velocity.