Summary of Exascale and Remeshing Efforts for the Second Geometry and Mesh Generation Workshop

Woeber, Carolyn; Masters, James S.; McDaniel, David R.

doi:10.2514/6.2019-3458

Cited by 6 publications

(2 citation statements)

References 4 publications

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“…As a basis for this cost comparison, we choose the OpenFOAM simulations reported from the AIAA HLPW3 (Ashton, Denison, & Zastawny, 2018). The RANS calculations are conducted on a 109M cell grid and warm started (initial guesses of the solution are (Woeber et al, 2019).…”

Section: Remarks On Computational Costmentioning

confidence: 99%

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Large eddy simulation of aircraft at affordable cost: a milestone in computational fluid dynamics

Goc

Lehmkuhl

Park

et al. 2021

Flow

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While there have been numerous applications of large eddy simulations (LES) to complex flows, their application to practical engineering configurations, such as full aircraft models, have been limited to date. Recently, however, advances in rapid, high quality mesh generation, low-dissipation numerical schemes and physics-based subgrid-scale and wall models have led to, for the first time, accurate simulations of a realistic aircraft in landing configuration (the Japanese Aerospace Exploration Agency Standard Model) in less than a day of turnaround time with modest resource requirements. In this paper, a systematic study of the predictive capability of LES across a range of angles of attack (including maximum lift and post-stall regimes), the robustness of the predictions to grid resolution and the incorporation of wind tunnel effects is carried out. Integrated engineering quantities of interest, such as lift, drag and pitching moment will be compared with experimental data, while sectional pressure forces will be used to corroborate the accuracy of the integrated quantities. Good agreement with experimental $C_L$ data is obtained across the lift curve with the coefficient of lift at maximum lift, $C_{L,max}$ , consistently being predicted to within five lift counts of the experimental value. The grid point requirements to achieve this level of accuracy are reduced compared with recent estimates (even for wall modelled LES), with the solutions showing systematic improvement upon grid refinement, with the exception of the solution at the lowest angles of attack, which will be discussed later in the text. Simulations that include the wind tunnel walls and aircraft body mounting system are able to replicate important features of the flow field noted in the experiment that are absent from free air calculations of the same geometry, namely, the onset of inboard flow separation in the post-stall regime. Turnaround times of the order of a day are made possible in part by algorithmic advances made to leverage graphical processing units. The results presented herein suggest that this combined approach (meshing, numerical algorithms, modelling, efficient computer implementation) is on the threshold of readiness for industrial use in aeronautical design.

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Section: Remarks On Computational Costmentioning

confidence: 99%

“…The generation of the 157 million cell body-fitted, Voronoi grids is created in ≈2 minutes on 10 3 Ivy Bridge CPU cores. This mesh generator has been effectively utilized to generate grids of O(10 10 ) cells on 40 × 10 3 cores in less than 30 minutes (Woeber, Masters, & McDaniel, 2019).…”

Section: Remarks On Computational Costmentioning

confidence: 99%

Large eddy simulation of aircraft at affordable cost: a milestone in computational fluid dynamics

Goc

Lehmkuhl

Park

et al. 2021

Flow

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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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HLPW-4/GMGW-3: High-Order Discretization Technology Focus Group Workshop Summary

Galbraith

Karman

2023

Journal of Aircraft

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This paper summarizes the High-Order Technical Focus Group (HO-TFG) submissions for the joint 4th AIAA High Lift Prediction (HLPW-4) and 3rd Geometry and Mesh Generation Workshop (GMGW-3). The goal of the workshop was to assess the state-of-the-art in mesh generation and computational fluid dynamics software. The Common Research Model High-Lift (CRM-HL) variant served as the primary focus of the workshop, and a two-dimensional airfoil section from the CRM-HL was used as a verification test case. The HO-TFG was tasked with generating high-order curved meshes for both geometries, and computing high-order solutions using both Reynolds-averaged Navier–Stokes and scale-resolving formulations. While limited by computational resources, the final results demonstrate the potential of higher-order methods to increase solution accuracy with a lower degree-of-freedom count relative to second-order discretizations.

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Summary of Exascale and Remeshing Efforts for the Second Geometry and Mesh Generation Workshop

Cited by 6 publications

References 4 publications

Large eddy simulation of aircraft at affordable cost: a milestone in computational fluid dynamics

Large eddy simulation of aircraft at affordable cost: a milestone in computational fluid dynamics

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

HLPW-4/GMGW-3: High-Order Discretization Technology Focus Group Workshop Summary

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