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This work assesses the capability of the partially averaged Navier-Stokes (PANS) method to accurately reproduce self-sustained shock oscillations, also known as transonic buffet, occurring on supercritical aerofoils at high Reynolds numbers. Attention is paid to the comparison with unsteady Reynolds-averaged Navier Stokes (URANS) results to show the benefits of PANS, in resolving flow unsteadiness on affordable CFD grids. The role of the mesh metrics in the formulation of the PANS model is emphasized, as well as the relation of the mesh metrics with the spatiotemporal discretisation used for the numerical simulations. The aim is to extend the use of PANS to flow cases involving shock-wave boundary layer interactions to obtain accurate predictions without the need for very expensive computations. | This work assesses the capability of the partially averaged Navier-Stokes (PANS) method to accurately reproduce self-sustained shock oscillations, also known as transonic buffet, occurring on supercritical aerofoils at high Reynolds numbers. Attention is paid to the comparison with unsteady Reynolds-averaged Navier Stokes (URANS) results to show the benefits of PANS, in resolving flow unsteadiness on affordable CFD grids. The role of the mesh metrics in the formulation of the PANS model is emphasized, as well as the relation of the mesh metrics with the spatiotemporal discretisation used for the numerical simulations. The aim is to extend the use of PANS to flow cases involving shock-wave boundary layer interactions to obtain accurate predictions without the need for very expensive computations. | ||
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| + | == Abstract == | ||
| + | <pdf>Media:Draft_Sanchez Pinedo_930261986236_abstract.pdf</pdf> | ||
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| + | == Full Paper == | ||
| + | <pdf>Media:Draft_Sanchez Pinedo_930261986236_paper.pdf</pdf> | ||
Latest revision as of 16:06, 25 November 2022
Summary
This work assesses the capability of the partially averaged Navier-Stokes (PANS) method to accurately reproduce self-sustained shock oscillations, also known as transonic buffet, occurring on supercritical aerofoils at high Reynolds numbers. Attention is paid to the comparison with unsteady Reynolds-averaged Navier Stokes (URANS) results to show the benefits of PANS, in resolving flow unsteadiness on affordable CFD grids. The role of the mesh metrics in the formulation of the PANS model is emphasized, as well as the relation of the mesh metrics with the spatiotemporal discretisation used for the numerical simulations. The aim is to extend the use of PANS to flow cases involving shock-wave boundary layer interactions to obtain accurate predictions without the need for very expensive computations.
Abstract
Full Paper
Document information
Published on 24/11/22
Accepted on 24/11/22
Submitted on 24/11/22
Volume Special Technology Sessions on Aeronautics and Manufacturing, 2022
DOI: 10.23967/eccomas.2022.278
Licence: CC BY-NC-SA license
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