Numerical simulations of the DLR-F11 wing/body high-lift configuration using the finite-volume-based solver STAR-CCM+ were performed for the 2nd AIAA CFD High Lift Prediction Workshop (HiLiftPW-2). Unstructured polyhedral meshes were generated using STAR-CCM+ based on the provided gridding guidelines, and the effects of grid refinement were assessed. The simulations employed a steady-state RANS approach using both the SST k- turbulence model and a formulation of the standard k- model including the Durbin scale limiter. The effect of Reynolds number was assessed by simulating both low and high Reynolds number flows and comparing the results to the experimental data.
The computational results for the pressure distributions and force and moment measurements compared well with experimental measurements provided as part of the HiLiftPW-2. The simulations showed that including the slat and flap track fairings in the computational model greatly affected the aerodynamics of the wing near max lift, with a defined separation occurring in the wake behind one of the slat track fairings. Additionally, the simulations using the standard k-e turbulence model better predicted the onset of separation near stall than the k-w SST model simulations as compared to the experimental data.