Investigation of a delta wing Vortex Generator

Abstract

The flow and the effect on a DU08-W-210 airfoil using a conventional and a delta wing vortex generator (VG) has been investigated numerically using ANSYS Fluent and STAR CCM+ CFD solvers. The numerical results from the two CFD programs are very consistent. Both VG geometries delay boundary separation at the trailing edge of the airfoil and thus increase the lift and lift to drag ratio. The overall aerodynamic loads on the airfoil are quite similar for the two different VG geometries, but the created vortices give a slightly different distribution of the skin friction in the wake behind the VGs. The vortex created by the delta wing VG for the same conditions and size as the conventional triangular VG is slightly stronger and probably caused by the fact that the surface creating the vortices is placed higher up in the boundary layer and thus experience a higher inflow velocity. A method to measure the strength and core radius of the created vortices using a Lamb-Ossen vortex is described.