Grid-Adapted FUN3D Computations for the Second High-Lift Prediction Workshop

Lee-Rausch, Elizabeth M.; Rumsey, Christopher L.; Park, Michael A.

doi:10.2514/1.c033192

Cited by 18 publications

(6 citation statements)

References 34 publications

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“…As previously shown in Ref. 11, the SA computations on the D Grid predict a large area of wedge-shaped separation on the main element behind SB6 as early as α = 18.5 • .…”

Section: Ve Surface Flow Comparisonsmentioning

confidence: 72%

“…Lee-Rausch et al 11 presented results from FUN3D with the SA and SA-RC models on workshop-provided grids (Grid System D), as well as on adapted grids. For the workshop, grid refinement studies were performed on the simplified Config 2 and only medium-size grids based on "best-practices" were generated for Configs 4 and 5.…”

Section: Vb Computational Meshesmentioning

confidence: 97%

“…LeeRausch et al 11 showed that SA model results could be improved near C L,max with adaptive mesh refinement.…”

Section: Vd Force and Moment Comparisonsmentioning

confidence: 97%

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Application of a Full Reynolds Stress Model to High Lift Flows

Lee-Rausch

Rumsey

Eisfeld

2016

46th AIAA Fluid Dynamics Conference

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A recently developed second-moment Reynolds stress model was applied to two challenging high-lift flows: (1) transonic flow over the ONERA M6 wing, and (2) subsonic flow over the DLR-F11 wing-body configuration from the second AIAA High Lift Prediction Workshop. In this study, the Reynolds stress model results were contrasted with those obtained from one-and two-equation turbulence models, and were found to be competitive in terms of the prediction of shock location and separation. For an ONERA M6 case, results from multiple codes, grids, and models were compared, with the Reynolds stress model tending to yield a slightly smaller shock-induced separation bubble near the wing tip than the simpler models, but all models were fairly close to the limited experimental surface pressure data. For a series of high-lift DLR-F11 cases, the range of results was more limited, but there was indication that the Reynolds stress model yielded less-separated results than the one-equation model near maximum lift. These less-separated results were similar to results from the one-equation model with a quadratic constitutive relation. Additional computations need to be performed before a more definitive assessment of the Reynolds stress model can be made. Nomenclature a speed of sound, m/s A wing reference area, m 2 AR wing aspect ratio b wing reference span, m c ref wing reference chord, mcomponent of diffusion tensor, m 2 /s 3 d distance to the nearest wall, m F 1 Menter's blending function F T fully turbulent g alternate scale-determining variable, 1/ω, s 1/2 k specific kinetic turbulence energy, m 2 /s 2 M ∞ freestream Mach number O ij normalized rotation tensor used in quadratic constitutive relation correction P two-equation model production term, τ ij (∂û i /∂x j ), kg/(ms 3 ) P ij Cartesian component of Reynolds-stress production tensor, m 2 /s 3 * Research Engineer, Computational AeroSciences Branch, E.Lee-Rausch@nasa.gov. Associate Fellow AIAA.

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“…As previously shown in Ref. 11, the SA computations on the D Grid predict a large area of wedge-shaped separation on the main element behind SB6 as early as α = 18.5 • .…”

Section: Ve Surface Flow Comparisonsmentioning

confidence: 72%

Section: Vb Computational Meshesmentioning

confidence: 97%

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Application of a Full Reynolds Stress Model to High Lift Flows

Lee-Rausch

Rumsey

Eisfeld

2016

46th AIAA Fluid Dynamics Conference

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“…The employment of low-Mach number correction suggests improved lift predictions, thus also improving the lift to drag ratio see Table 6. The over-prediction of the drag coefficient compared to the experiment has been reported in several papers dealing with the same configuration at 16 degrees [79][80][81]. The discrepancies between drag predictions and computations have been partially attributed to installations effects of the model in the wind tunnel [82].…”

Section: Dlr-f11mentioning

confidence: 90%

Assessment of high-order finite volume methods on unstructured meshes for RANS solutions of aeronautical configurations

2017

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This version is available at https://strathprints.strath.ac.uk/59947/ Strathprints is designed to allow users to access the research output of the University of Strathclyde. Unless otherwise explicitly stated on the manuscript, Copyright © and Moral Rights for the papers on this site are retained by the individual authors and/or other copyright owners. Please check the manuscript for details of any other licences that may have been applied. You may not engage in further distribution of the material for any profitmaking activities or any commercial gain. You may freely distribute both the url (https://strathprints.strath.ac.uk/) and the content of this paper for research or private study, educational, or not-for-profit purposes without prior permission or charge.Any correspondence concerning this service should be sent to the Strathprints administrator: strathprints@strath.ac.ukThe Strathprints institutional repository (https://strathprints.strath.ac.uk) is a digital archive of University of Strathclyde research outputs. It has been developed to disseminate open access research outputs, expose data about those outputs, and enable the management and persistent access to Strathclyde's intellectual output. Assessment of High-Order Finite Volume Methods on Unstructured Meshes for RANS Solutions of Aeronautical Configurations.Antonis F. Antoniadis a, * ,P a n a g i o t i sT s o u t s a n i s referenced data and discussed in terms of accuracy, grid dependence and computational budget.

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“…FUN3D is a finite volume node-centered unstructured-grid RANS solver, which is also widely used for high-fidelity analysis and adjoint-based design of complex turbulent flows [16,[20][21][22][23][24][25][26]. FUN3D solves governing flow equations on mixed-element grids; the elements are tetrahedra, pyramids, prisms, and hexahedra.…”

Section: A Cfl3dmentioning

confidence: 99%

Grid-Convergence of Reynolds-Averaged Navier–Stokes Solutions for Benchmark Flows in Two Dimensions

et al. 2016

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A detailed grid-convergence study has been conducted to establish reference solutions corresponding to the oneequation linear eddy-viscosity Spalart-Allmaras turbulence model for two-dimensional turbulent flows around the NACA 0012 airfoil and a flat plate. The study involved the three widely used codes CFL3D (NASA), FUN3D (NASA), and TAU (DLR, The German Aerospace Center), as well as families of uniformly refined structured grids that differed in the grid density patterns. Solutions computed by different codes on different grid families appeared to converge to the same continuous limit but exhibited strikingly different convergence characteristics. The grid resolution in the vicinity of geometric singularities, such as a sharp trailing edge, was found to be the major factor affecting accuracy and convergence of discrete solutions; the effects of this local grid resolution were more prominent than differences in discretization schemes and/or grid elements. The results reported for these relatively simple turbulent flows demonstrated that CFL3D, FUN3D, and TAU solutions were very similar on the finest grids used in the study, but even those grids were not sufficient to conclusively establish an asymptotic convergence order.

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Grid-Adapted FUN3D Computations for the Second High-Lift Prediction Workshop

Cited by 18 publications

References 34 publications

Application of a Full Reynolds Stress Model to High Lift Flows

Application of a Full Reynolds Stress Model to High Lift Flows

Assessment of high-order finite volume methods on unstructured meshes for RANS solutions of aeronautical configurations

Grid-Convergence of Reynolds-Averaged Navier–Stokes Solutions for Benchmark Flows in Two Dimensions

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