Wingtip Vortex Simulation by Using Nonequilibrium Eddy Viscosity Model

The wingtip vortex simulation by using nonequilibrium Eddy viscosity model is discussed. The unstructured grid system of hexahedral-based mesh was used with a special cell layer that consisted of grids normal to the solid surface to resolve the boundary layer well. The angle of attack is 10 deg, and the Reynolds number is 4.6 × 106 based on the chord length. The half span of the wing is only 0.75c. A grid convergence test was performed to assure adequate accuracy. The nonequilibrium eddy viscosity model and the two-component-limit (TCL) model predict the very slow decreasing tendency of the vortex core axial velocity in the very near-wake region well. The velocity magnitude of the present nonequilibrium model case is slightly higher than the experimental data, while the rate of decrease is as good as the TCL model case.