Abstract
The enhancement of the structured Computational Fluid Dynamics solver FLOWer in the field of flux computation and its advantage to numerical helicopter simulations is presented. The improvement includes the replacement of the second order spatial scheme with a fifth order scheme for flow state reconstruction and the implementation of different Riemann solvers for flux computation. Aim of the implementation is to reduce the numerical dissipation and to achieve a high vortex preservation essential for numerical investigations of helicopter flows, such as rotor-fuselage interaction and noise emission of the rotor due to blade vortex interactions. For these phenomena which are sensitive to the rotor wake preservation, an investigation with the second order and the fifth order scheme is performed to compare the numerical results as well as the computational performance. The results show significant improvements in the rotor wake conservation, especially in case of an acoustic evaluation. It is shown that the Riemann solver has a high influence to the vortex conservation with low additional computational cost.
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Acknowledgements
We greatly acknowledge the provision of supercomputing time and technical support by the High Performance Computing Center Stuttgart (HLRS) for our project HELISIM.
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Kowarsch, U., Oehrle, C., Hollands, M., Keßler, M., Krämer, E. (2013). Computation of Helicopter Phenomena Using a Higher Order Method. In: Nagel, W., Kröner, D., Resch, M. (eds) High Performance Computing in Science and Engineering ‘13. Springer, Cham. https://doi.org/10.1007/978-3-319-02165-2_29
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DOI: https://doi.org/10.1007/978-3-319-02165-2_29
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