Analysis for alleviation of flow separation on the symmetrical plane of thick airfoil with vortex generators at subsonic speed

Abstract

The flow over the thick airfoil is characterized by the rapid velocity decrease toward the trailing edge, thus flow separates inevitably from the rear surface of the wing. To prevent or reduce the extent of flow separation, vortex generators are attached on the pressure recovery region of the airfoil. The main function of the vortex generators is the production of vortices trailing downstream, enhancing mixing between external flow and boundary layer. As a consequence the separation point of flow is shifted downstream delaying or preventing flow separation depending upon the vortex strength. In this thesis an analysis of flow behavior involving flow separation is carried out using a computer. It is shown qualitatively that flow separation on a thick airfoil under angle of attack can be delayed or prevented by installing the vortex generators.