NSU3D Results for the Second AIAA High-Lift Prediction Workshop

Simulation results for the second AIAA CFD High-Lift Prediction Workshop using the unstructured computational fluid dynamics code NSU3D are presented. The solution algorithms employed in NSU3D for this study are described along with examples of convergence history and computational cost. The geometry used for the simulation consists of the DLR-F11 wing-body with high-lift system deployed in a landing configuration. This geometry is representative of a modern transport aircraft high-lift system that has been tested experimentally over a suitable Reynolds number range. Results are presented from two sets of computational studies, the first performed at the University of Wyoming using standard workshop unstructured meshes, and the second performed at Bombardier Aerospace using in-house generated meshes. In both cases, results are presented for two different turbulence models, allowing an assessment of the sensitivity of the results to grid densities, grid types, and turbulence models. Results consist of computed force and moment coefficients across a range of angles of attack and for two different Reynolds numbers, as well as surface pressure profiles and off-body velocity profiles, all of which are compared with experimental data. The results compare favorably with experimental data and generally fall within the standard deviation of the workshop collective results. Computations using the Spalart-Allmaras turbulence model tend to overpredict the maximum lift value and incidence, while results using the k-omega model tend to underpredict the maximum lift value. The best agreement in terms of force coefficients is observed with the k-omega turbulence model using the Bombardier internally generated meshes.