NSU3D Results for the First AIAA High-Lift Prediction WOrkshop

Simulation results for the rst AIAA CFD High Lift Prediction Workshop using the unstructured computational uid 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 is the NASA threeelement swept wing (Trap Wing) model with experimental data taken in the 14x22 foot wind tunnel at NASA Langley. Computational grids for the study were prepared by the authors with the VGRIDns package using CAD geometry provided by the workshop committee. A grid convergence study was performed using a family of three grids to assess sensitivity to grid resolution. A range of angle-of-attack values from 6 to 37 was completed on the medium grid and the resulting lift, drag and longitudinal moments are compared to the experimental results. The e ect of changing the ap angle is investigated with a second model using an equivalent medium grid. Comparisons of surface pressure to experimental data are presented for both con gurations. Flow features are also presented using surface constrained and volume streamlines for selected cases.

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