dpw3 results for the dlr f6 wb and wbf - nasa · dpw3 results for the dlr f6 wb and wbf e. van der...
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DPW3 results for the DLR F6 WB and WBFDPW3 results for the DLR F6 WB and WBF
E. van der Weide, J.J. Alonso
Department of Aeronautics & AstronauticsStanford University
E. Arad, M. Bercovici, Y. Shechner
Rafael
Haifa, Israel
Third Drag Prediction Workshop
San Francisco, CA, June 3-4, 2006
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Outline
• Numerical algorithm
• Turbulence models
• Platforms/Wall clock times
• Results
• Future work
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Numerical algorithm• Cell-centered Finite Volume discretization.
• Central discretization of the advective terms plus scalar artificial dissipationfor the mean flow.
• Upwind discretization of the advective terms for the turbulence equations,either 1st or 2nd order (with MinMod limiter).
• Compact central discretization of the viscous fluxes.
• Geometrical multigrid in combination with Runge-Kutta type explicitsmoothers for the mean flow.
• Segregated solution of the turbulence equations using DD-ADI schemes.No multigrid for the turbulence.
• “Automatic” parallelization ⇒ #processors independent of #blocks
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Turbulence models
• Spalart-Allmaras.– Used in fully turbulent mode.
• v2-f, 4-equation model developed by Durbin.– k-ε model extended with two additional equations.– v: fluctuation energy normal to the wall (channel flow)– f: models non-local effects, in particular the influence of the wall– solved as two 2X2 coupled systems.– free-stream eddy-viscosity ratio ≥ 3.6 to avoid negative k.
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Platforms/Wall clock times
• Linux cluster, 3.6 GHz dual Xeon processors.– Wall clock time, 32 processors, medium mesh (9.5 million cells): 5-10 hours
• ASCI QSC (Los Alamos), 1.25 GHz Dec Alpha processors.– Wall clock time, 64 processors, medium mesh (9.5 million cells): 7-14 hours
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Grid (modified Icem grid)• Higher resolution on the wing and fuselage• Less points in the farfield• 3-level multigrid• Coarse grid: 3 million cells. Medium grid: 9.5 million cells.
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Convergence Wing Body plus FX2B fairingM∞ = 0.75, α = -3.0°, Rec = 5•106, c = 141.2 mm, Spalart-Allmaras model
Coarse grid Medium grid
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Convergence Wing Body plus FX2B fairingM∞ = 0.75, α = -3.0°, Rec = 5•106, c = 141.2 mm, Spalart-Allmaras model
Coarse grid Medium grid
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Pressure distributionsM∞ = 0.75, CL = 0.5, Rec = 5•106, c = 141.2 mm, Spalart-Allmaras model
Wing body Wing body plus FX2B fairing
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Coefficients Wing BodyM∞ = 0.75, Rec = 5•106, c = 141.2 mm
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Coefficients Wing Body plus FX2B fairingM∞ = 0.75, Rec = 5•106, c = 141.2 mm
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Oilflow Patterns (1)Wing body, M∞ = 0.75, α = -3.0°, Rec = 5•106, c = 141.2 mm
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Oilflow Patterns (2)Wing body, M∞ = 0.75, α = 1.5°, Rec = 5•106, c = 141.2 mm
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Oilflow Patterns (3)Wing body, M∞ = 0.75, CL = 0.5, Rec = 5•106, c = 141.2 mm
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Oilflow patterns (4)Wing body FX2B fairing, M∞ = 0.75, CL = 0.5, Rec = 5•106, c = 141.2 mm
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Future work
• Vertex-centered discretization (possibly higher order) underdevelopment.
• DD-ADI schemes for the mean flow to speed up convergence.
• Use other turbulence models, e.g. k-ω, Menter’s SST.
• Perform the fine grid computations.
• Abstract submitted for Reno 2007.