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Abstract
High-resolution computational fluid dynamics (CFD) simulations were performed using Unsteady Reynolds-averaged Navier-Stokes (URANS) and Delayed Detached Eddy Simulation (DDES) models for the static and dynamic stall of a finite-span OA209 wing. The flow was modeled as both fully turbulent and laminar with transition to turbulence. NASA OVERFLOW and ONERA elsA flow solvers were used for the simulations. A comprehensive, comparative study was carried out between the predictions and the ONERA finite-wing test data for pre- and post-stall measurements that included blade section loads, surface pressure, velocity field at chord and span planes, and spanwise flow. The high spatial and temporal resolutions employed in the present simulations resulted in good correlations with the test data. In particular, the inclusion of a transition model reduced the overprediction of the static stall angle generally seen in CFD predictions, and, as a result, also led to the observed improvements in the dynamic stall correlations. Transition locations were not measured, and, therefore, the computed transition locations were qualitatively compared against the measurements on a 2-D OA209 wing with reasonable agreement between the two. The validity of the present CFD models was subsequently tested for deep and light dynamic stall cases, and very good agreement between the computed loads and the test data was obtained. Finally, simulation cost reduction strategies were investigated that included Adaptive Mesh Refinement (AMR) in the wing CFD grid in combination with a temporal error control in order to mitigate the high cost associated with the 3-D dynamic stall simulations. A 40% cost savings was achieved during the initial studies with opportunities for further savings.

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  High-resolution CFD Predictions for Static and Dynamic Stall of a Finite-span OA209 Wing

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