Abstract
Transonic flow in the wake of a generic space launch vehicle is investigated using Improved Delayed Detached-Eddy simulations on quasi-structured, partially unstructured and hybrid grids. It is shown that a \(90^\circ \) segment of the full domain can already capture the main afterbody flow dynamics and give a good agreement with experimental results. In order to assess the effect of unstructured grids, simulation results on a grid with an unstructured recirculation region are compared to a quasi-structured and a true hybrid grid. Finally, a comparison between IDDES and zonal DES results are presented and discussed.
Keywords
- Launch Vehicle
- Improved Delayed DES (IDDES)
- Hybrid Grid
- Explicit Algebraic Reynolds Stress Model (EARSM)
- Small Corner Vortex
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.
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Acknowledgements
The authors would like to thank Axel Probst and Silvia Probst from the DLR Göttingen CASE department for providing the ADDES version of the DLR TAU code and their constant help with scale-resolving simulations in TAU.
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Horchler, T., Oßwald, K., Hannemann, V., Hannemann, K. (2018). Hybrid RANS-LES Study of Transonic Flow in the Wake of a Generic Space Launch Vehicle. In: Hoarau, Y., Peng, SH., Schwamborn, D., Revell, A. (eds) Progress in Hybrid RANS-LES Modelling. HRLM 2016. Notes on Numerical Fluid Mechanics and Multidisciplinary Design, vol 137. Springer, Cham. https://doi.org/10.1007/978-3-319-70031-1_24
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DOI: https://doi.org/10.1007/978-3-319-70031-1_24
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