4th AIAA CFD High Lift Prediction Workshop results using metric-based anisotropic mesh adaptation

Alauzet, Frédéric; Clerici, Francesco; Loseille, Adrien; Maunoury, Matthieu; Rochery, Lucien; Tarsia-Morisco, Cosimo; Tenkes, Lucille-Marie; Vanharen, Julien

doi:10.2514/6.2022-3521

Cited by 3 publications

(2 citation statements)

References 15 publications

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“…The evaluation of this phenomenon on the NASA Common Research Model Wing-Body (CRM) configuration is rather challenging for solvers based on the Reynolds-Averaged Navier-Stokes (RANS) equations.In this paper, it is proposed to show the benefits of anisotropic mesh adaptation [2], even in the presence of separated flows. Previous works [3], [5] highlighted that it is possible to achieve very accurate prediction on fully-unstructured adapted meshes composed only of tetrahedra. Moreover, the same accuracy can be obtained with a reduction of the mesh size by a factor between 20 and 100 with respect to the best-practice expert-created meshes [4].Numerous computations from the DPW-7 have been carried out and grid convergence was obtained thanks to anisotropic mesh adaptation on both steady and alpha sweep configurations.…”

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confidence: 99%

“…In this paper, it is proposed to show the benefits of anisotropic mesh adaptation [2], even in the presence of separated flows. Previous works [3], [5] highlighted that it is possible to achieve very accurate prediction on fully-unstructured adapted meshes composed only of tetrahedra. Moreover, the same accuracy can be obtained with a reduction of the mesh size by a factor between 20 and 100 with respect to the best-practice expert-created meshes [4].…”

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confidence: 99%

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7th AIAA CFD Drag Prediction Workshop (DPW-7) results using anisotropic mesh adaptation

Vanharen,

Tarsia Morisco,

Alauzet

2023

Progress in Canadian Mechanical Engineering. Volume 6

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The AIAA CFD Drag Prediction Workshop (DPW) Series was initiated in 2000 by a working group of members from the Applied Aerodynamics Technical Committee of the American Institute of Aeronautics and Astronautics. Since then, numerous workshops have been held providing participants a unique way to compare their results on several different test cases. The 7 th Drag Prediction Workshop (DPW-7) focuses on predicting the effect of shock-induced separation on the variation of lift and pitching moment with increasing angle-of-attack at transonic conditions. The evaluation of this phenomenon on the NASA Common Research Model Wing-Body (CRM) configuration is rather challenging for solvers based on the Reynolds-Averaged Navier-Stokes (RANS) equations.In this paper, it is proposed to show the benefits of anisotropic mesh adaptation [2], even in the presence of separated flows. Previous works [3], [5] highlighted that it is possible to achieve very accurate prediction on fully-unstructured adapted meshes composed only of tetrahedra. Moreover, the same accuracy can be obtained with a reduction of the mesh size by a factor between 20 and 100 with respect to the best-practice expert-created meshes [4].Numerous computations from the DPW-7 have been carried out and grid convergence was obtained thanks to anisotropic mesh adaptation on both steady and alpha sweep configurations. Goaloriented mesh adaptation provided much better results than their feature-based counterparts and proves to be the proper strategy to tackle this kind of configuration.

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7th AIAA CFD Drag Prediction Workshop (DPW-7) results using anisotropic mesh adaptation

Vanharen,

Tarsia Morisco,

Alauzet

2023

Progress in Canadian Mechanical Engineering. Volume 6

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Fourth High-Lift Prediction/Third Geometry and Mesh Generation Workshops: Overview and Summary

Rumsey

Slotnick

Woeber

2023

Journal of Aircraft

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The Fourth AIAA Computational Fluid Dynamics (CFD) High Lift Prediction Workshop and the Third Geometry and Mesh Generation Workshop were held collaboratively with the common goal of assessing the numerical prediction capability of current-generation computational fluid dynamics technology for swept medium-/high-aspect-ratio wings in high-lift configurations. A key aspect of this joint endeavor was the use of technology focus groups: an innovative new approach for workshops involving close collaboration between participants. These groups, which included both mesh-generation and flow-solver experts, worked to accelerate advancements for their particular methodologies by addressing key questions of importance before the workshop. The high-lift version of the NASA Common Research Model (CRM-HL) configuration was the focus of this workshop. Measured experimental wind-tunnel data were available for comparison. The workshop also included a two-dimensional turbulence model verification exercise based on the CRM-HL wing shape. Altogether, 44 participants submitted a total of 184 datasets of CFD results. This paper provides a high-level summary of the results and conclusions from the workshop. Like at past workshops, fixed-grid Reynolds-averaged Navier–Stokes methods continued to be inaccurate and inconsistent for predicting high-lift flow physics near maximum lift conditions. However, mesh adaptation definitively brought more consistency. Scale-resolving methods appeared most promising for predicting high-lift flow physics near maximum lift.

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Free-Air Simulation Sensitivities on NASA’s High-Lift Common Research Model

Zauner,

Sansica,

Matsuzaki

et al. 2024

AIAA Journal

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To reduce the time-to-market of future aircraft, it is crucial to predict the flight envelope accurately before building prototypes for flight tests. The High-Lift Prediction Workshop series aims to assess the numerical prediction capability of current computational fluid dynamics technology considering the high-lift version of the NASA’s Common Research Model. The present work contributes to these collaborative efforts, quantifying sensitivities for Reynolds-averaged Navier–Stokes (RANS)–based steady, unsteady, and hybrid RANS/large-eddy-simulation scale-resolving approaches. Uncertainties associated with the choice of turbulence model, initialization strategies, grid resolution, and iterative convergence at free-air conditions are covered. Near stall, a large spread of RANS results was observed for different turbulence models and initialization strategies, while iterative convergence appeared less crucial for the present simulations. Steady and unsteady RANS simulations were unable to predict the correct flow physics near [Formula: see text], even for large grids. Delayed detached-eddy simulations (DDES), however, showed good accuracy compared with wind-tunnel experiments and predicted [Formula: see text] with an error of around 5%. Compared to steady RANS, the computational cost of DDES was a factor of 10 higher. Lessons learned and potential best-practice strategies are shared to aid future studies. While warm-started RANS simulations using Spalart–Allmaras models are recommended at lower angles of attack, scale-resolving methods are required near stall.

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4th AIAA CFD High Lift Prediction Workshop results using metric-based anisotropic mesh adaptation

Cited by 3 publications

References 15 publications

7th AIAA CFD Drag Prediction Workshop (DPW-7) results using anisotropic mesh adaptation

7th AIAA CFD Drag Prediction Workshop (DPW-7) results using anisotropic mesh adaptation

Fourth High-Lift Prediction/Third Geometry and Mesh Generation Workshops: Overview and Summary

Free-Air Simulation Sensitivities on NASA’s High-Lift Common Research Model

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