Abstract
Recent enhancements and applications of the flow solver FLOWer are presented in this paper. A locally formulated laminar-turbulent transition model is implemented and used for simulations of a steady and pitching finite wing. Corresponding experimental results show good agreement on transition points. In CFD, a separation bubble is observed that triggers laminar-turbulent transition. Furthermore, the paper focuses on CFD simulations conducted on Airbus Helicopters’ compound helicopter RACER and the underlying setup, including flexible main rotor blades, engine boundary conditions and deformable flaps. Finally, interaction phenomena and interesting flow characteristics are described for hovering and cruise conditions.
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Acknowledgements
The provided supercomputing time and technical support of the High Performance Computing Center Stuttgart (HLRS) of the University of Stuttgart within the HELISIM project is gratefully acknowledged. Parts of the research presented in this study were performed in cooperation of the Institute of Aerodynamics and Gas Dynamics of the University of Stuttgart and the Airbus Helicopters division of Airbus SE within the European research framework Clean Sky 2 under Grant 686530. We would like to express our thanks to the European Union for providing us the resources to realize this project. The authors would like to thank Airbus Helicopters Germany and France for the esteemed cooperation within this project and beyond. Furthermore, the investigation is based on the long-standing cooperation with the German Aerospace Center (DLR) making us their CFD code FLOWer available for advancements and research purpose, which we would like to thank for.
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Frey, F., Herb, J., Letzgus, J., Weihing, P., Keßler, M., Krämer, E. (2019). Enhancement and Application of the Flow Solver FLOWer. In: Nagel, W., Kröner, D., Resch, M. (eds) High Performance Computing in Science and Engineering ' 18. Springer, Cham. https://doi.org/10.1007/978-3-030-13325-2_20
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