Abstract
Wall-bounded turbulent flows as those occurring in transportation (e.g. aviation) or industrial applications (e.g turbomachinery), are usually subjected to pressure gradients (PGs). The presence of such PGs affects greatly the development and physics of the turbulent boundary layer (TBL), making it an open research area. An important phenomena associated with the presence of strong adverse PGs (APGs) as appearing in wings, is the separation of the boundary layer, which can lead to stall.
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References
Atzori, M., et al.: In situ visualization of large-scale turbulence simulations in Nek5000 with ParaView catalyst. J. Supercomput. 78(3), 3605–3620 (2022)
Bross, M., Fuchs, T., Kähler, C.J.: Interaction of coherent flow structures in adverse pressure gradient turbulent boundary layers. J. Fluid Mech. 873, 287–321 (2019)
Chin, R.C., et al.: Backflow events under the effect of secondary flow of Prandtl’s first kind. Phys. Rev. Fluids 5(7), 074606 (2020)
Coles, D., Wadcock, A.J.: Flying-hot-wire study of flow past an NACA 4412 airfoil at maximum lift. AIAA J. 17(4), 321–329 (1979)
Fischer, P., Kruse, J., Mullen, J., Tufo, H., Lottes, J., Kerkemeier, S.: Nek5000: Open source spectral element CFD solver. Argonne National Laboratory, Mathematics and Computer Science Division, Argonne, IL (2008)
Frère, A., Hillewaert, K., Chatelain, P., Winckelmans, G.: High Reynolds number airfoil: from wall-resolved to wall-modeled LES. Flow Turbul. Combust. 101(2), 457–476 (2018)
Sato, M., Asada, K., Nonomura, T., Kawai, S., Fujii, K.: High Reynolds number airfoil: Large-eddy simulation of NACA 0015 airfoil flow at Reynolds number of 1.6\(\times \)\(10^6\), AIAA J. 55 (2), 673–679 (2017)
Schlatter, P., Stolz, S., Kleiser, L.: LES of transitional flows using the approximate deconvolution model. Int. J. Heat Fluid Flow 25(3), 549–558 (2004)
Tanarro, A., Mallor, F., Offermans, N., Peplinski, A., Vinuesa, R., Schlatter, P.: Enabling adaptive mesh refinement for spectral-element simulations of turbulence around wing sections. Flow Turbul. Combust. 105, 415–436 (2020)
Vinuesa, R., Örlü, R., Schlatter, P.: Characterisation of backflow events over a wing section. J. Turbulence 18, 170–185 (2017)
Vinuesa, R., Negi, P.S., Atzori, M., Hanifi, A., Henningson, D.S., Schlatter, P.: Turbulent boundary layers around wing sections up to \(Re_c\)= 1,000,000. Int. J. Heat Fluid Flow 72, 86–99 (2018)
Acknowledgements
The simulations were performed on resources provided by both the Swedish National Infrastructure for Computing (SNIC) at the PDC Center for High Performance Computing, in KTH (Stockholm), and by the European High-Performance Computing Joint Undertaking (EuroHPC JU) project EHPC-REG-2021R0088 in LUMI (Finland). This research is funded by the Knut and Alice Wallenberg Foundation.
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Mallor, F. et al. (2024). In-Situ Analysis of Backflow Events and Their Relation to Separation in Wings Through Well-Resolved LES. In: Marchioli, C., Salvetti, M.V., Garcia-Villalba, M., Schlatter, P. (eds) Direct and Large Eddy Simulation XIII. DLES 2023. ERCOFTAC Series, vol 31. Springer, Cham. https://doi.org/10.1007/978-3-031-47028-8_3
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