Abstract: Navier-Stokes calculation on multi-block is performed to calculate drag of the DLR-F6 wing-body configuration with CFD software TRIP2.0.Structured grids(1-to-1) and test results used are from Drag prediction workshop Ⅱ (DPWⅡ). Referenced numerical results are obtained with CFL3D. Effects of mesh density and turbulent models on aerodynamic characteristics and pressure distribution are carefully studied. Results are verified by experimental data and CFL3D results. Grid refinement leads to convergent results in SST turbulent models. It is demonstrated that turbulent models have little influence on pressure drag, but obvious influence on friction drag. The turbulent model and grid density have little influence on pressure distribution.

Key words: TRIP2.O, DLR-F6, drag prediction workshop Ⅱ, drag, turbulent models