DLR TAU Results - NASA · 01/07/2009 · DLR AIAA DPW-4, 20th–21st June 2009 Slide 1 DLR TAU...
Transcript of DLR TAU Results - NASA · 01/07/2009 · DLR AIAA DPW-4, 20th–21st June 2009 Slide 1 DLR TAU...
![Page 1: DLR TAU Results - NASA · 01/07/2009 · DLR AIAA DPW-4, 20th–21st June 2009 Slide 1 DLR TAU Results AIAA DPW-4 O. Brodersen, S. Crippa, B. Eisfeld, S. Keye, S. Geisbauer Institute](https://reader034.fdocuments.us/reader034/viewer/2022052100/6039430144250b057b5b53ba/html5/thumbnails/1.jpg)
DLR AIAA DPW-4, 20th–21st June 2009
Slide 1
DLR TAU ResultsAIAA DPW-4
O. Brodersen, S. Crippa, B. Eisfeld, S. Keye, S. Geisbauer
Institute of Aerodynamics and Flow TechnologyDLR
Germany
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DLR AIAA DPW-4, 20th–21st June 2009
Slide 2
Content
• Objectives• Grids• TAU RANS Solver• Case 1.1: Grid Refinement Study• Case 1.2: Downwash Study• Case 3: Reynolds Number Study• Conclusions
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DLR AIAA DPW-4, 20th–21st June 2009
Objectives— DLR Objectives in DPW-4 —
Test DLR-TAU with new Solar grid generation approach(hex-dominant in boundary layer):
Refinement studies using Solar grids
Compare to standard TAU Centaur medium grids results(prism-dominant in boundary layer)
Application of SA,Menter kω-SST, and RSMturbulence models
ih trim interpolation vs.HTP setting modificationin CFD loop (mesh deformation)
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DLR AIAA DPW-4, 20th–21st June 2009
Slide 4
Content
• Objectives• Grids• TAU RANS Solver• Case 1.1: Grid Refinement Study• Case 1.2: Downwash Study• Case 3: Reynolds Number Study• Conclusions
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DLR AIAA DPW-4, 20th–21st June 2009
Grids— Solar —
Solar grid generation system developed byARA, BAE Systems, Airbus, QinetiQ:
Anisotropic quad-dominant unstructuredsurface meshesAdvancing layer near field mesherBuffer layer transitioning to triangulatednear field shellTetrahedral far field meshingConsistent grid familyHere: grid refinement factor ≈1.42 used
60
34076798
Fine
4230 Hexa Layers
116968044074967Nodes
MediumCoarse
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DLR AIAA DPW-4, 20th–21st June 2009
Grids— Centaur 8.1 —
Centaur grid generation system developed byCentaurSoft:
Triangulated surface meshesPrismatic elements for boundary layerresolutionTetrahedral far field meshing
35Prismatic Layers
13331301Nodes
Medium
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DLR AIAA DPW-4, 20th–21st June 2009
Grids— Volume Grid —
X=1400
Y=400
Medium gridsBest practice forCentaur gridsLimited experiencewith Solar grids
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DLR AIAA DPW-4, 20th–21st June 2009
Slide 8
Content
• Objectives• Grids• TAU RANS Solver• Case 1.1: Grid Refinement Study• Case 1.2: Downwash Study• Case 3: Reynolds Number Study• Conclusions
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DLR AIAA DPW-4, 20th–21st June 2009
TAU RANS Solver— Overview —
TAU solves Reynolds-averaged Navier-Stokes equationsFinite Volume Method, node-centered, (cell-centered), dual grid techniqueSeveral discretization schemes,here:
2nd order central with Jameson-type dissipationTime integration: Runge-Kutta, Backward EulerLocal time stepping, residual smoothingMultigridSeveral turbulence models,here:
Spalart-Allmaras original (SA, SAO)Menter kω-SST (kω-SST)Speziale-Sakar-Gatski/Launder-Reece-Rodi, SSG/LRR-ω, (RSM)
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DLR AIAA DPW-4, 20th–21st June 2009
Slide 10
Content
• Objectives• Grids• TAU RANS Solver• Case 1.1: Grid Refinement Study• Case 1.2: Downwash Study• Case 3: Reynolds Number Study• Conclusions
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DLR AIAA DPW-4, 20th–21st June 2009
Case 1.1— Grid Type/Size, Turbulence Model —
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DLR AIAA DPW-4, 20th–21st June 2009
Case 1.1— Grid Type/Size, Turbulence Model —
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DLR AIAA DPW-4, 20th–21st June 2009
Case 1.1— Grid Type/Size, SAO Model —
y/b2 = 0.2009
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DLR AIAA DPW-4, 20th–21st June 2009
Case 1.1— Grid Type/Size, SAO Model —
y/b2 = 0.2009
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DLR AIAA DPW-4, 20th–21st June 2009
Case 1.1— Turbulence Model —
y/b2=0.3971
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DLR AIAA DPW-4, 20th–21st June 2009
Case 1.1— Turbulence Model —
y/b2=0.3971
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DLR AIAA DPW-4, 20th–21st June 2009
Case 1.1— Turbulence Model —
y/b2=0.95
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DLR AIAA DPW-4, 20th–21st June 2009
Case 1.1— Turbulence Model —
y/b2=0.95
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DLR AIAA DPW-4, 20th–21st June 2009
Case 1.1— Grid Size —
SAO, Centaur grid, coarseSAO, Centaur grid, medium
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DLR AIAA DPW-4, 20th–21st June 2009
Case 1.1— Turbulence Model —
Menter kω-SST, Centaur grid, mediumSAO, Centaur grid, medium
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DLR AIAA DPW-4, 20th–21st June 2009
Case 1.1— Grid Type/Size, Turbulence Model —
y/b2=0.2
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DLR AIAA DPW-4, 20th–21st June 2009
Slide 22
Content
• Objectives• Grids• TAU RANS Solver• Case 1.1: Grid Refinement Study• Case 1.2: Downwash Study• Case 3: Reynolds Number Study• Conclusions
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DLR AIAA DPW-4, 20th–21st June 2009
Case 1.2— CL-α, Polar, HTP Settings —
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DLR AIAA DPW-4, 20th–21st June 2009
Case 1.2— CL-α, Polar, HTP Settings, Grid Type —
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DLR AIAA DPW-4, 20th–21st June 2009
Case 1.2— CL-α, Polar, HTP Settings, Grid Type —
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DLR AIAA DPW-4, 20th–21st June 2009
Case 1.2— CL-α, Polar, Turbulence Model, HTP Setting —
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DLR AIAA DPW-4, 20th–21st June 2009
Case 1.2— CDp/f Polar, Turbulence Model, HTP Setting —
CDp
CDf
SAO
kω-SST
RSM
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DLR AIAA DPW-4, 20th–21st June 2009
Case 1.2— CL-α, Polar, Trimmed, Turbulence Model, Grid Type —
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DLR AIAA DPW-4, 20th–21st June 2009
Case 1.2— CL-CM, Grid Type —
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DLR AIAA DPW-4, 20th–21st June 2009
Case 1.2— Flow Features, α=4.0o, Grid Type —
SAO, Centaur medium grid SAO, Solar medium grid
y/b2=0.2009
y/b2=0.3971
y/b2=0.95
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DLR AIAA DPW-4, 20th–21st June 2009
Case 1.2— Flow Features, α=4.0o, Turbulence Model —
Menter kω-SST, Solar medium grid RSM, Solar medium grid
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DLR AIAA DPW-4, 20th–21st June 2009
Case 1.2— Pressure Distribution, α=4.0o, Turbulence Model —
y/b2=0.2009
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DLR AIAA DPW-4, 20th–21st June 2009
Case 1.2— Pressure Distribution, α=4.0o, Turbulence Model —
y/b2=0.2009
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DLR AIAA DPW-4, 20th–21st June 2009
Case 1.2— Pressure Distribution, α=4.0o, Turbulence Model —
y/b2=0.95
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DLR AIAA DPW-4, 20th–21st June 2009
Case 1.2— Pressure Distribution, α=4.0o, Turbulence Model —
y/b2=0.95
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DLR AIAA DPW-4, 20th–21st June 2009
Case 1.2— Delta Drag, Turbulence Model —
Tail-off minustrimmedconfiguration
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DLR AIAA DPW-4, 20th–21st June 2009
Case 1.2— HTP Setting Modification —
ih=-2o
Iterative modification of ihduring CFD calculationstowards CM=0, CL=0.5
Mesh deformation usedbased on radial basisfunctions
Differences to interpolateddata are small
Δih=0.0029o
Δα=0.000018o
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DLR AIAA DPW-4, 20th–21st June 2009
Case 1.2— HTP Setting Modification —
ih=+2o
Iterative modification of ihduring CFD calculationstowards CM=0, CL=0.5
Mesh deformation usedbased on radial basisfunctions
Differences to interpolateddata are small
Δih=0.0029o
Δα=0.000018o
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DLR AIAA DPW-4, 20th–21st June 2009
Case 1.2— HTP Setting Modification —
Iterative modification of ihduring CFD calculationstowards CM=0, CL=0.5
Mesh deformation usedbased on radial basisfunctions
Differences to interpolateddata are small
Δih=0.0029o
Δα=0.000018o
CM for deformed grids nearlyidentical to CM calculated forseparately generated grids.
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DLR AIAA DPW-4, 20th–21st June 2009
Slide 40
Content
• Objectives• Grids• TAU RANS Solver• Case 1.1: Grid Refinement Study• Case 1.2: Downwash Study• Case 3: Reynolds Number Study• Conclusions
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DLR AIAA DPW-4, 20th–21st June 2009
Case 3— Re Influence, Turbulence Model —
Δα ≈ 8-10%, ΔCD ≈ 12-13%, ΔCM ≈ 14-23%
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DLR AIAA DPW-4, 20th–21st June 2009
Slide 42
Content
• Objectives• Grids• TAU RANS Solver• Case 1.1: Grid Refinement Study• Case 1.2: Downwash Study• Case 3: Reynolds Number Study• Conclusions
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DLR AIAA DPW-4, 20th–21st June 2009
Conclusions (Preliminary)— Lessons Learned —
Solar quad-dominant unstructured surface meshes and hex-BL-resolution technique produce very good hierarchy of grids with high quality.
Better leading edge and shock resolution with less overall nodes achievable.
Aerodynamic coefficients and deltas for medium Centaur/Solar grids are similar.
Grid refinement indicates a nearly linear behaviour for 1/N2/3.
Wing fuselage separation is influenced by the grid type/size.
Trailing edge separation size is mainly influenced by the turbulence model.
Trimmed polars: the grid influence is less important than the turbulence model.
Iterative setting variation of HTP in CFD loop towards CM=0 for CL=0.5: Very small differences of ih and α for trimmed configurationcompared to interpolation method based on results from separately generated grids.