Drag Prediction Using NSU3D (Unstructured Multigrid NS Solver)
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Transcript of Drag Prediction Using NSU3D (Unstructured Multigrid NS Solver)
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Drag Prediction Using NSU3D(Unstructured Multigrid NS Solver)
Dimitri J. Mavriplis
National Institute of Aerospace
Hampton, VA 23666 (USA)
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NSU3D Description
• Unstructured Reynolds Averaged Navier-Stokes solver– Vertex-based discertization– Mixed elements (prisms in boundary layer)– Edge data structure– Matrix artificial dissipation
• Option for upwind scheme with gradient reconstruction
– No cross derivative viscous terms• Thin layer in all 3 directions
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Solver Description (cont’d)
• Spalart-Allmaras turbulence model– (original published form)– Optional k-omega model
• Transition specified by zeroing out production term in turbulence model– More robust than S-A trip term– Based on surface patches
• Laminar patches• Laminar normal distance
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Solution Strategy
• Jacobi/Line Preconditioning– Line solves in boundary layer regions
• Releives aspect ratio stiffness
• Agglomeration multigrid– Fast grid independent convergence rates
• Parallel implementation– MPI/OpenMP hybrid model
• DPW runs: MPI on 16 cpu cluster
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Performance• Convergence in 500
multigrid cycles– Grid independent– Poor convergence for
negative alpha nacelle cases
• 16 Pentium IV 1.7GHz: Intermediate grids– 5 hours for 3M pt grid– 7.5 hours for 5M pt grid
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Grid Generation
• Runs based on NASA Langley supplied VGRIDns unstructured grids
• Tetrahedra in Boundary Layer merged into prismatic elements
• Sequence of 3 grids for each configuration
• Transition based on surface patches
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Grid Specifications
Configuration Coarse Medium Fine
Wing-Body
Points
Cells
1,121,301
6,558,758
3,010307
17,635,283
9,133,352
53,653,279
WB+Nacelle
Points
Cells
1,827,470
10,715,204
4,751,207
27,875,222
10,278,588
60,412,948
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Intermediate Grid (WB: 3M pts)
• Transition specified by laminar patches
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Intermediate Grid (WB: 3M pts)
• Transition specified by laminar patches
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Intermediate Grid (WBN: 5M pts)
• Transition specified by laminar patches
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Solution on Intermediate Grid (CL=0.5)
• Matching CL
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Solution on Intermediate Grid (CL=0.5)
• Matching Incidence
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Solution on Intermediate Grid (CL=0.5)
• Matching CL
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Solution on Intermediate Grid (CL=0.5)
• Matching Incidence
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Lift vs. Incidence (Wing-Body)
• Large Lift overprediction (incidence shift)
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Surface Pressure at y/b=0.411(WB)
• Solution converges with grid refinement• Poor match with experiment for specified CL
• Better match for specified incidence
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Lift vs. Incidence (WB-Nacelle)
• Large Lift overprediction (incidence shift)
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Surface Pressure at y/b=0.411(WBNacelle)
• Solution converges with grid refinement• Poor match with experiment for specified CL
• Better match for specified incidence
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Drag Polar (Wing-Body)
• Coarse grid inadequate• Correct shape, slight underprediction
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Drag Polar (Wing-Body-Nacelle)
• Coarse grid inadequate• Correct shape, slight underprediction• Convergence issues at negative incidences
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Moment (Wing-Body)
• Poor moment prediction– Related to incidence shift
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Moment (Wing-BodyNacelle)
• Poor moment prediction– Related to incidence shift
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Incremental Drag
• Within 2 to 4 counts at CL=0.5• Transition effects cancel out• More discrepancies at lower lift
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Incremental Moment
• Good prediction in spite of poor absolute values– Cross over well predicted– Discrepancies at lower lift
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Drag Rise Curves
• Medium grids, transition• General trend, Drag underpredicted• Cl vs incidence issues
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Flow Details
• Separation bubble on WB-Nacelle (fine grid)
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Flow Details
• Strong shock inboard pylon (-2 deg)• Ahead of specified transition region on lower wing
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Conclusions
• CL – Incidence Issues
• Better success at prediction of increments
• Grid Generation approach may be more important than actual resolution
• Aero is still a tough problem– Worthy of funding