Influence of a Reverse Delta Type Add On Device on Wake Vortex Alleviation
Particle image velocimetry was used in a low speed wind tunnel to investigate the effect of interactions of vortices produced by a wingtip of a half span wing (NACA 23012 in landing configuration) and a slender reverse delta type add on device placed near the tip on the upper surface of the half span wing. This work investigates the characteristics of the vortex interactions generated downstream in planes perpendicular to the freestream direction and their dependence on angles of attack at a chord based Reynolds number of Rec=2.75x105. It was found that the add on device significantly reduced the tangential velocity, vorticity, and circulation magnitude by up to 82.9, 92.6, and 42.8% respectively, and increased the resultant vortex core radius by a factor of 6.57. A six component force balance was used to obtain the aerodynamic performance of the half span wing model with a reverse delta type add on device. It was found that the reverse delta type add on device marginally affected the aerodynamic perform.