Application of HPCMP CREATE<sup>TM</sup>-AV COFFE for Three-Dimensional Turbulent Flow Cases

Erwin, Jon T.; Glasby, Ryan S.

doi:10.2514/6.2016-1361

Cited by 12 publications

(2 citation statements)

References 10 publications

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“…This session focused on the NACA 0012 airfoil and led to a Special Section on Evaluation of RANS Solvers on Benchmark Aerodynamics Flows in the AIAA journal [18][19][20][21][22]. In 2016, another special session at SciTech was held focusing on more difficult cases such as a subsonic flow over a 3D bump, a supersonic flow in a 3D square duct, and a subsonic flow over a 3D hemisphere cylinder at zero angle of attack [23][24][25][26][27].…”

Section: Introductionmentioning

confidence: 99%

An Investigation of Continuous and Discontinuous Finite-Element Discretizations on Benchmark 3D Turbulent Flows (Invited)

Ahrabi

Brazell

Mavriplis

2018

2018 AIAA Aerospace Sciences Meeting

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Two high-order finite-element solvers are used to simulate two 3D benchmark problems provided by the NASA Turbulence Modeling Resource (TMR) website. The first problem is a subsonic turbulent flow over a hemisphere-cylinder body at angles of attack of 5 and 19 degrees. The second problem is a transonic turbulent flow over an ONERA M6 wing at angles of attack of 3.06 and 6.06 degrees. The first finite-element solver is based on the streamline-upwind Petrov-Galerkin (SUPG) discretization and the second one is based on the discontinuous Galerkin (DG) method. For both problems, second-and higher-order solutions are provided and a detailed mesh convergence study is presented. Also, the linear and nonlinear convergence behavior of the utilized solvers is investigated. The SUPG solver shows a very consistent non-linear convergence behavior across all grids while the DG solver struggles on the coarse grids. Both finite-element solvers demonstrate rapid convergence for high-order simulations when initialized with a second-order accurate solution. For all hemisphere-cylinder cases and the M6 wing at angle of attack of 3.06 degrees, the finiteelement solvers are outperforming the FUN3D finite-volume solver in terms of accuracy per degree of freedom. For the M6 wing at angle of attack of 6.06 degrees, although no reference solutions were provided by the TMR website, simulations were attempted for the finiteelement solvers. For this case, no conclusions can be made about asymptotic convergence of the integrated forces due to lack of consistency between results. This was initially thought to be caused by the provided grids. However, further investigation using custom unstructured grids leads us to believe that the flow conditions, not the grids, make this case challenging.

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Section: Introductionmentioning

confidence: 99%

An Investigation of Continuous and Discontinuous Finite-Element Discretizations on Benchmark 3D Turbulent Flows (Invited)

Ahrabi

Brazell

Mavriplis

2018

2018 AIAA Aerospace Sciences Meeting

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“…In support of the TMR objectives, special sessions on solver technology for turbulent flows were held at the AIAA Science and Technology Forum and Exposition (SciTech) conferences in 2015 [4][5][6][7][8][9][10][11] and 2016. [12][13][14][15][16][17][18][19][20] Advanced solver technologies for the Reynolds-Averaged Navier-Stokes (RANS) equations with a one-equation linear eddyviscosity Spalart-Allmaras (SA) turbulence model 21,22 were demonstrated in application to relatively simple benchmark flows in two dimensions (2D) and three dimensions (3D). Some of the solver-technology advances reported at these sessions, including adaptive and high-order solutions, have been published in a special AIAA Journal publication.…”

Section: Introductionmentioning

confidence: 99%

Grid Convergence for Three Dimensional Benchmark Turbulent Flows

Diskin

Anderson

Pandya

et al. 2018

2018 AIAA Aerospace Sciences Meeting

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Grid convergence studies are performed to establish reference solutions for benchmark three dimensional turbulent flows in support of the ongoing turbulence model verification and validation effort at the Turbulence Modeling Resource website curated by NASA. The benchmark cases are a subsonic flow around a hemisphere cylinder and a transonic flow around the ONERA M6 wing with a sharp trailing edge. The study applies widely-used computational fluid dynamics codes developed and supported at the NASA Langley Research Center: FUN3D, USM3D, and CFL3D. Reference steady-state solutions are computed for the Reynolds-Averaged Navier-Stokes equations with the Spalart-Allmaras turbulence model on families of consistently-refined grids composed of different types of cells. Coarse-to-fine and code-to-code solution variation is described in detail.

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A scalable solution strategy for high-order stabilized finite-element solvers using an implicit line preconditioner

Ahrabi

Mavriplis

2018

Computer Methods in Applied Mechanics and Engineering

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Application of HPCMP CREATE^TM-AV COFFE for Three-Dimensional Turbulent Flow Cases

Cited by 12 publications

References 10 publications

An Investigation of Continuous and Discontinuous Finite-Element Discretizations on Benchmark 3D Turbulent Flows (Invited)

An Investigation of Continuous and Discontinuous Finite-Element Discretizations on Benchmark 3D Turbulent Flows (Invited)

Grid Convergence for Three Dimensional Benchmark Turbulent Flows

A scalable solution strategy for high-order stabilized finite-element solvers using an implicit line preconditioner

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Application of HPCMP CREATETM-AV COFFE for Three-Dimensional Turbulent Flow Cases

Cited by 12 publications

References 10 publications

An Investigation of Continuous and Discontinuous Finite-Element Discretizations on Benchmark 3D Turbulent Flows (Invited)

An Investigation of Continuous and Discontinuous Finite-Element Discretizations on Benchmark 3D Turbulent Flows (Invited)

Grid Convergence for Three Dimensional Benchmark Turbulent Flows

A scalable solution strategy for high-order stabilized finite-element solvers using an implicit line preconditioner

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Product

Resources

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Application of HPCMP CREATE^TM-AV COFFE for Three-Dimensional Turbulent Flow Cases