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 CASE 1 SINGLE-POINT GRID CONVERGENCE STUDY (REQUIRED) --------------------------------------- WING/BODY GRID_SIZE MACH ALPHA CL_TOT (min, max) CD_TOT (min, max) CD_PR CD_SF CM_TOT (min, max) RESID_DROP coarse 0.75 0.0205 0.4991 (-,-) 0.02896 (-,-) 0.01633 0.01263 -0.1427 (-,-) 1, 0.5e-03 medium 0.75 0.0546 0.4993 (-,-) 0.02874 (-,-) 0.01614 0.01260 -0.1415 (-,-) 1, 0.5e-03 fine 0.75 0.0449 0.4996 (-,-) 0.02853 (-,-) 0.01590 0.01263 -0.1421 (-,-) 1, 0.5e-03 WING/BODY/NACELLE/PYLON GRID_SIZE MACH ALPHA CL_TOT (min, max) CD_TOT (min, max) CD_PR CD_SF CM_TOT (min, max) RESID_DROP coarse 0.75 0.5004 0.4991 (-,-) 0.03350 (-,-) 0.01853 0.01497 -0.1581 (-,-) 1, 0.5e-03 medium 0.75 0.5374 0.4992 (-,-) 0.03306 (-,-) 0.01812 0.01495 -0.1429 (-,-) 1, 0.5e-03 fine 0.75 0.5206 0.5001 (-,-) 0.03282 (-,-) 0.01791 0.01491 -0.1447 (-,-) 1, 0.5e-03 SEPARATION BUBBLE GEOMETRY - WING/BODY - FINE GRID FS_BUB BL_BUB WL_BUB FS_EYE_W BL_EYE_W WL_EYE_W FS_EYE_B BL_EYE_B WL_EYE_B 203.5 -89.7 9.6 237.0 -78.8 -9.2 239.7 -70.1 0.8 SEPARATION BUBBLE GEOMETRY - WING/BODY/NACELLE/PYLON - FINE GRID FS_BUB BL_BUB WL_BUB FS_EYE_W BL_EYE_W WL_EYE_W FS_EYE_B BL_EYE_B WL_EYE_B 214.5 -83.1 7.9 238.4 -77.2 -10.0 240.7 -69.1 -1.9 CASE 2 DRAG POLAR - MEDIUM GRID (REQUIRED) --------------------------------- WING/BODY, tripped 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 0.13858 (-,-) 0.01933 (-,-) 0.00721 0.01211 0.018687 -0.15570 (-,-) 0.75 -2.0 0.25624 (-,-) 0.02101 (-,-) 0.00887 0.01213 0.018810 -0.15124 (-,-) 0.75 -1.5 0.31512 (-,-) 0.02227 (-,-) 0.01014 0.01212 0.018943 -0.14929 (-,-) 0.75 -1.0 0.37405 (-,-) 0.02382 (-,-) 0.01171 0.01210 0.019132 -0.14740 (-,-) 0.75 0.0 0.49141 (-,-) 0.02783 (-,-) 0.01580 0.01203 0.019739 -0.14301 (-,-) 0.75 1.0 0.60776 (-,-) 0.03380 (-,-) 0.02192 0.01188 0.021423 -0.13595 (-,-) 0.75 1.5 0.66446 (-,-) 0.03825 (-,-) 0.02653 0.01171 0.023457 -0.13154 (-,-) WING/BODY/NACELLE/PYLON, tripped 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 0.10318 (-,-) 0.02862 (-,-) 0.01412 0.01450 0.028263 -0.16250 (-,-) 0.75 -2.0 0.20801 (-,-) 0.02751 (-,-) 0.01301 0.01449 0.026060 -0.15616 (-,-) 0.75 -1.5 0.25484 (-,-) 0.02718 (-,-) 0.01270 0.01447 0.025004 -0.15506 (-,-) 0.75 -1.0 0.31065 (-,-) 0.02781 (-,-) 0.01335 0.01447 0.024577 -0.15105 (-,-) 0.75 0.0 0.41722 (-,-) 0.03048 (-,-) 0.01609 0.01440 0.024647 -0.13984 (-,-) 0.75 1.0 0.53148 (-,-) 0.03486 (-,-) 0.02059 0.01426 0.025395 -0.13000 (-,-) 0.75 1.5 0.59122 (-,-) 0.03828 (-,-) 0.02412 0.01415 0.026568 -0.12476 (-,-) UPPER SURFACE TRANSITION LOCATIONS (% CHORD) XROOT XKINK XE.844 XTIP 0.05 0.15 0.15 0.5 LOWER SURFACE TRANSITION LOCATION (% CHORD) XLO 0.25 CASE 3 TRIPPED VS. FULLY TURBULENT DRAG (OPTIONAL) -------------------------------- WING/BODY MACH ALPHA CL_TOT (min, max) CD_TOT (min, max) CD_PR CD_SF CM_TOT (min, max) TYPE 0.75 0.1014 0.4999 (-,-) 0.02826 (-,-) 0.01626 0.01200 -0.1416 (-,-) TRIPPED 0.75 0.0546 0.4993 (-,-) 0.02874 (-,-) 0.01614 0.01260 -0.1415 (-,-) FULLY TURBULENT WING/BODY/NACELLE/PYLON MACH ALPHA CL_TOT (min, max) CD_TOT (min, max) CD_PR CD_SF CM_TOT (min, max) TYPE 0.75 0.7490 0.4997 (-,-) 0.03351 (-,-) 0.01922 0.01429 -0.1318 (-,-) TRIPPED 0.75 0.5374 0.4992 (-,-) 0.03306 (-,-) 0.01812 0.01495 -0.1429 (-,-) FULLY TURBULENT UPPER SURFACE TRANSITION LOCATIONS (% CHORD) XROOT XKINK XE.844 XTIP 0.05 0.15 0.15 0.5 LOWER SURFACE TRANSITION LOCATION (% CHORD) XLO 0.25 CASE 4 DRAG RISE (OPTIONAL) ------------------------------------------- WING/BODY, tripped MACH ALPHA CL_TOT (min, max) CD_TOT (min, max) CD_PR CD_SF CM_TOT (min, max) 0.50 0.722 0.500 (-,-) 0.02712 (-,-) 0.01441 0.01271 -0.1172 (-,-) 0.60 0.539 0.500 (-,-) 0.02724 (-,-) 0.01476 0.01248 -0.1242 (-,-) 0.70 0.272 0.500 (-,-) 0.02771 (-,-) 0.01553 0.01218 -0.1344 (-,-) 0.72 0.204 0.500 (-,-) 0.02788 (-,-) 0.01577 0.01211 -0.1372 (-,-) 0.74 0.139 0.500 (-,-) 0.02812 (-,-) 0.01608 0.01204 -0.1400 (-,-) 0.75 0.101 0.500 (-,-) 0.02826 (-,-) 0.01626 0.01200 -0.1416 (-,-) 0.76 0.058 0.500 (-,-) 0.02845 (-,-) 0.01650 0.01196 -0.1436 (-,-) 0.77 0.019 0.500 (-,-) 0.02875 (-,-) 0.01686 0.01189 -0.1456 (-,-) WING/BODY/NACELLE/PYLON, tripped MACH ALPHA CL_TOT (min, max) CD_TOT (min, max) CD_PR CD_SF CM_TOT (min, max) 0.50 1.148 0.500 (-,-) 0.03069 (-,-) 0.01538 0.01531 -0.1149 (-,-) 0.60 0.999 0.500 (-,-) 0.03075 (-,-) 0.01573 0.01502 -0.1227 (-,-) 0.70 0.761 0.500 (-,-) 0.03150 (-,-) 0.01686 0.01464 -0.1350 (-,-) 0.72 0.792 0.499 (-,-) 0.03244 (-,-) 0.01797 0.01447 -0.1307 (-,-) 0.74 0.785 0.500 (-,-) 0.03310 (-,-) 0.01876 0.01434 -0.1308 (-,-) 0.75 0.749 0.500 (-,-) 0.03351 (-,-) 0.01922 0.01429 -0.1318 (-,-) 0.76 0.705 0.500 (-,-) 0.03365 (-,-) 0.01944 0.01421 -0.1348 (-,-) 0.77 0.655 0.499 (-,-) 0.03409 (-,-) 0.01995 0.01414 -0.1371 (-,-) UPPER SURFACE TRANSITION LOCATIONS (% CHORD) XROOT XKINK XE.844 XTIP 0.05 0.15 0.15 0.5 LOWER SURFACE TRANSITION LOCATION (% CHORD) XLO 0.25 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)