Date: 08/31/2003 PARTICIPANT INFORMATION ----------------------- Name: Olaf Brodersen (DLR), Mark Rakowitz (DLR), Mark Sutcliffe (Airbus Deutschland) Email: o.brodersen@dlr.de mark.rakowitz@dlr.de mark.sutcliffe@airbus.com Phone: +49 (0)531 2952439 or +49 (0)531 2952415 or +49 (0)421 5383439 Address: DLR, Institute for Aerodynamics and Flow Technology Address: Lilienthalplatz 7 , 38108 Braunschweig , Germany Address: Airbus Deutschland GmbH Address: Aerodynamic Design and Data (EGAG) Address: Huenefeldstr. 1-5 Address: 28199 Bremen , Germany SOLVER INFORMATION -------------------- Method Name: TAU Basic Algorithm: finite volume method for hybrid grids, edge-based, dual grid technique Turbulence Model: Spalart-Allmaras with Edwards modification Residual: L2-norm of density residual Miscellaneous: Upwind and central schemes, unsteady flows, overlapping grids, matrix dissipation, interfaces for coupling (e.g. flight mechanics), optimised for parallel and vector machines GRID INFORMATION -------------------- Grid-Generator Name: Centaur from CentaurSoft Grid Type: unstructured, hybrid (Tetrahedral, pyramidal, prismatic elements) COARSE GRID SIZE WB WBNP ----------------------------------------- Zones: 1 1 Field Nodes: 3812515 5515066 Field Cells: Boundary Nodes: 120689 182443 Boundary Faces: BL 1st-Cell Size: adapted to y-plus = 0.9 BL Max-Growth Rate: approx. 1.2 - 1.3 BL Cells: 25 prismatic layers (approx. 13-16 in BL) Miscellaneous: DLR grids generated with Centaur, adapted with TAU MEDIUM GRID SIZE WB WBNP ----------------------------------------- Zones: 1 1 Field Nodes: 5836028 8202568 Field Cells: Boundary Nodes: 183575 268994 Boundary Faces: BL 1st-Cell Size: adapted to y-plus = 0.9 BL Max-Growth Rate: approx. 1.2-1.3 BL Cells: 25 prismatic layers (approx. 13-16 in BL) Miscellaneous: DLR grids generated with Centaur, adapted with TAU FINE GRID SIZE WB WBNP ----------------------------------------- Zones: 1 1 Field Nodes: 8760472 12321068 Field Cells: Boundary Nodes: 272939 397753 Boundary Faces: BL 1st-Cell Size: adapted to y-plus = 0.9 BL Max-Growth Rate: approx. 1.2-1.3 BL Cells: 25 prismatic layers (approx. 13-16 in BL) Miscellaneous: DLR grids generated with Centaur, adapted with TAU SOLUTION INFORMATION -------------------- Computer Platform: NEC-SX5 (16 proc. 64GB), vector-parallel machine # Processors: 4 processors used here Operating System: NEC-Unix Compiler: Nec C-compiler Run Time CPU: Run Time Wall-Clock: Memory Requirements: up to approx. 10 GB for the finest grid WBNP Miscellaneous: shared memory machine Additional CASE 2 fully turbulent: WING/BODY MACH ALPHA CL_TOT (min, max) CD_TOT (min, max) CD_PR CD_SF CD-CL2/PA CM_TOT (min, max) 0.75 -3.0 0.12732 (-,-) 0.02034 (-,-) 0.00768 0.01266 0.019797 -0.14878 (-,-) 0.75 -2.0 0.24432 (-,-) 0.02184 (-,-) 0.00917 0.01267 0.019840 -0.14474 (-,-) 0.75 -1.5 0.30138 (-,-) 0.02301 (-,-) 0.01037 0.01264 0.019967 -0.14213 (-,-) 0.75 -1.0 0.35624 (-,-) 0.02445 (-,-) 0.01186 0.01259 0.020198 -0.13922 (-,-) 0.75 0.0 0.48786 (-,-) 0.02836 (-,-) 0.01575 0.01260 0.020385 -0.14029 (-,-) 0.75 1.0 0.60201 (-,-) 0.03420 (-,-) 0.02179 0.01241 0.022057 -0.13262 (-,-) 0.75 1.5 0.65773 (-,-) 0.03850 (-,-) 0.02627 0.01223 0.024005 -0.12801 (-,-) WING/BODY/NACELLE/PYLON MACH ALPHA CL_TOT (min, max) CD_TOT (min, max) CD_PR CD_SF CD-CL2/PA CM_TOT (min, max) 0.75 -3.0 0.07966 (-,-) 0.02854 (-,-) 0.01349 0.01504 0.028327 -0.16155 (-,-) 0.75 -2.0 0.19215 (-,-) 0.02771 (-,-) 0.01267 0.01503 0.026473 -0.15416 (-,-) 0.75 -1.5 0.24571 (-,-) 0.02785 (-,-) 0.01283 0.01502 0.025827 -0.15126 (-,-) 0.75 -1.0 0.29297 (-,-) 0.02838 (-,-) 0.01337 0.01501 0.025504 -0.14579 (-,-) 0.75 0.0 0.41590 (-,-) 0.03069 (-,-) 0.01568 0.01500 0.024894 -0.14123 (-,-) 0.75 1.0 0.53353 (-,-) 0.03519 (-,-) 0.02035 0.01484 0.025652 -0.13004 (-,-) 0.75 1.5 0.58948 (-,-) 0.03848 (-,-) 0.02379 0.01469 0.026837 -0.12430 (-,-) NOTES: ------ * Information lines are 80 characters long. * Information blocks allow free-form miscellaneous information. * MACH (F10.2) Mach Number. * ALPHA (F10.3) Angle of Attack in Degrees. * CL_TOT (F10.3) Total Lift Coefficient. * CD_TOT (F10.5) Total Drag Coefficient. * CD_PR (F10.5) Surface-Pressure Integrated Drag Coefficient. * CD_SF (F10.5) Skin-Friction Integrated Drag Coefficient. * CD-CL2/PA (F10.5) CD_TOT - (CL_TOT*CL_TOT)/(PI*AR) * CM_TOT (F10.4) Total Moment Coefficient. * RESID_DROP (F10.5) Initial Residual/Final Residual * D_CL_TOT (F10.3) Increment in CL_TOT due to nacelle * D_CD_TOT (F10.5) Increment in CD_TOT due to nacelle * D_CD_PR (F10.5) Increment in CD_PR due to nacelle * D_CD_SF (F10.5) Increment in CD_SF due to nacelle * D_CM_TOT (F10.4) Increment in CM_TOT due to nacelle * XROOT (F10.0) Upper surface boundary layer transition location at the wing root in % chord * XKINK (F10.0) Upper surface boundary layer transition location at the wing planform break in % chord * XE.844 (F10.0) Upper surface boundary layer transition location at 84.4% span in % chord * XTIP (F10.0) Upper surface boundary layer transition location at the wing tip in % chord * XLO (F10.0) Lower surface boundary layer transition location in % chord * GRID_SIZE (F10.0) Number of grid nodes or cells * FS_BUB (F10.2) Fuselage station at the leading edge of the wing root separation bubble (mm) (measured on the wing) * BL_BUB (F10.2) Buttock line at the outboard edge of the wing root separation bubble (mm) (measured on the wing) * WL_BUB (F10.2) Water line at the top edge of the wing root separation bubble (mm) (measured on the fuselage) * FS_EYE_W (F10.2) Fuselage station at the center of the wing root separation bubble (mm) (measured on the wing) * BL_EYE_W (F10.2) Buttock line at the center of the wing root separation bubble (mm) (measured on the wing) * WL_EYE_W (F10.2) Water line at the center of the wing root separation bubble (mm) (measured on the wing) * FS_EYE_B (F10.2) Fuselage station at the center of the wing root separation bubble (mm) (measured on the fuselage) * BL_EYE_B (F10.2) Buttock line at the center of the wing root separation bubble (mm) (measured on the fuselage) * WL_EYE_B (F10.2) Water line at the center of the wing root separation bubble (mm) (measured on the fuselage)