Abstract
In this study, we apply a numerical strategy, based on high-accurate finite volume numerical schemes and advanced turbulence models, to calculate the mean and fluctuating pressure in the recirculation zone of a mock up of the Ariane 5 space launcher, which is one of our advanced validation test cases for the FLUSEPA solver, developed by Airbus Safran Launchers.
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Acknowledgements
The authors gratefully acknowledge the ESA TRP on Launcher Base Flows and Shock Interactions Regions Improved Load Characterisation for the experimental results.
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Pont, G., Puech, D., Brenner, P. (2018). Hybrid RANS/LES Simulation of a Space Launcher Using a High Order Finite Volume Scheme and Grid Intersections Technique. 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_29
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DOI: https://doi.org/10.1007/978-3-319-70031-1_29
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