Results from the Second AIAA CFD High-Lift Prediction Workshop Using Edge

Abstract

The results presented at the Second AIAA High-Lift Prediction Workshop, using the flow-solver Edge, are summarized for the DLR, German Aerospace Center F11 model. A comparative study of the results, using three turbulence models, is carried out, including the Spalart–Allmaras model, an explicit algebraic Reynolds-stress model, and a curvature correction to the explicit algebraic Reynolds-stress model. The comparisons include a grid-convergence study on a simplified model without slat- and flap-track fairings, and polar calculations including the fairings. The grid-convergence study shows relatively small differences due to different grid resolution and turbulence models, but the differences are larger than those obtained in the first workshop for the NASA trap wing. The prediction has fairly large discrepancies from experimental measurements at low Reynolds numbers for which the computations were carried out assuming fully turbulent flow. The explicit algebraic Reynolds-stress model (with or without curvature correction) tends to exaggerate flow separation and to underpredict the lift, as compared to the experiment. The Spalart–Allmaras model, on the other hand, overpredicts the lift at higher incidences. At the higher Reynolds number, the predictions agree well with the experimental measurements for different turbulence models. The curvature correction to the explicit algebraic Reynolds-stress model has an insignificant effect on the computed results in comparison with the explicit algebraic Reynolds-stress-model predictions.