Date: August 4 2003 PARTICIPANT INFORMATION ----------------------- Name: Florian Menter Email: florian.menter@ansys.com Phone: ++ 49 (0)8024 9054 15 Address: AEA Technology GmbH ANSYS CFX Address: Staudenfeldweg 12 Address: 83624 Otterfing Address: Germany SOLVER INFORMATION -------------------- Method Name: Coupled Algebraic Multi-grid Basic Algorithm: Unstructured conservative time implicit pressure based finite volume, Colocated Rhie-Chow pressure velocity coupling, Barth and Jesperson bounded high resolution advection scheme Coupled algebraic multi-grid method developed by Raw Turbulence Model: Menter SST Residual: RMS Residual of continuity normalized by the range of the solution quantity and the center coefficient of the linearized equation. As a result, the residual definition is independant of the time step and initial conditions. Miscellaneous: Turbulence model modified so that laminar regions can be specified in the solver. This is accomplished by zeroing the positive production term (Pk) in the turbulent kinetic energy equation. GRID INFORMATION -------------------- Grid-Generator Name: ICEM Hexa Grid Type: Standard ICEM Hexahedral meshes Provided to the Workshop COARSE GRID SIZE WB WBNP ----------------------------------------- Zones: Field Nodes: 3456601 4885352 Field Cells: 3374848 4787392 Boundary Nodes: Boundary Faces: 162720 195072 BL 1st-Cell Size: 0.001 (mm) 0.002 (mm) BL Max-Growth Rate: 1.25 1.32 BL Cells: 25 21 Miscellaneous: MEDIUM GRID SIZE WB WBNP ----------------------------------------- Zones: Field Nodes: 5831289 8433416 Field Cells: 5715968 8290304 Boundary Nodes: Boundary Faces: 229760 285312 BL 1st-Cell Size: 0.001 (mm) 0.002 (mm) BL Max-Growth Rate: 1.25 1.25 BL Cells: 33 25 Miscellaneous: FINE GRID SIZE WB WBNP ----------------------------------------- Zones: Field Nodes: 10135689 13682200 Field Cells: 9966592 13481984 Boundary Nodes: Boundary Faces: 337024 399360 BL 1st-Cell Size: 0.001 (mm) 0.001 (mm) BL Max-Growth Rate: 1.2 1.2 BL Cells: 41 33 Miscellaneous: SOLUTION INFORMATION (medium WB grid) -------------------- Computer Platform: HPC linux cluster # Processors: 16 Operating System: Linux Compiler: Run Time CPU: 23.6 hrs / processor Run Time Wall-Clock: 31.1 hrs Memory Requirements: 6 GB (Total), 377 Meg. / CPU Miscellaneous: 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 INITIAL_RESIDUAL FINAL_RESIDUAL 3456601. 0.75 0.500 0.501 (0.???, 0.???) 0.03018 (?.?????, ?.?????) 0.01756 0.01261 -0.1263 1.5E-3 1.4E-5 5831289. 0.75 0.500 0.500 (0.???, 0.???) 0.02983 (?.?????, ?.?????) 0.01717 0.01267 -0.1272 8.0E-4 3.5E-5 10135689. 0.75 0.540 0.501 (0.???, 0.???) 0.02967 (?.?????, ?.?????) 0.01687 0.01277 -0.1262 6.8E-4 3.6E-6 WING/BODY/NACELLE/PYLON GRID_SIZE MACH ALPHA CL_TOT (min, max) CD_TOT (min, max) CD_PR CD_SF CM_TOT INITIAL_RESIDUAL FINAL_RESIDUAL 4885352. 0.75 1.297 0.504 (0.???, 0.???) 0.03672 (?.?????, ?.?????) 0.02183 0.01489 -0.1101 ?.??? ?.??? 8433416. 0.75 1.225 0.500 (0.???, 0.???) 0.03616 (?.?????, ?.?????) 0.02124 0.01491 -0.1125 4.5E-4 2.0E-5 13682200. 0.75 1.175 0.510 (0.???, 0.???) 0.03516 (?.?????, ?.?????) 0.01998 0.01518 -0.1153 1.7E-2 1.6E-5 SEPARATION BUBBLE GEOMETRY - WING/BODY - MEDIUM GRID (mm) FS_BUB BL_BUB WL_BUB FS_EYE_W BL_EYE_W WL_EYE_W FS_EYE_B BL_EYE_B WL_EYE_B Visible 144.86 112.76 13.83 235.84 -97.15 -5.61 213.68 -72.27 7.71 Numerical 110.13 SEPARATION BUBBLE GEOMETRY - WING/BODY/NACELLE/PYLON - MEDIUM GRID (mm) FS_BUB BL_BUB WL_BUB FS_EYE_W BL_EYE_W WL_EYE_W FS_EYE_B BL_EYE_B WL_EYE_B Visible 135.90 115.20 14.60 235.84 -97.15 -5.61 219.56 -72.58 8.07 Numerical 101.70 CASE 2 DRAG POLAR - MEDIUM GRID (REQUIRED) --------------------------------- 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 0.113 (0.109, 0.113) 0.01970 (0.01938, 0.01972) 0.00737 0.01233 0.01921 -0.1505 (-0.1461, -0.1515) 0.75 -2.0 0.223 (?.???, ?.???) 0.02094 (?.?????, ?.?????) 0.00859 0.01235 0.01902 -0.1446 (?.????, ?.????) 0.75 -1.5 0.279 (0.277, 0.280) 0.02211 (0.02199, 0.02213) 0.00975 0.01235 0.01911 -0.1423 (?.????, ?.????) 0.75 -1.0 0.334 (0.333, 0.334) 0.02327 (0.02320, 0.02330) 0.01095 0.01232 0.01898 -0.1391 (?.????, ?.????) 0.75 0.0 0.448 (?.???, ?.???) 0.02687 (?.?????, ?.?????) 0.01461 0.01226 0.01917 -0.1332 (?.????, ?.????) 0.75 1.0 0.561 (0.560, 0.563) 0.03234 (0.03224, 0.03246) 0.02020 0.01214 0.02024 -0.1249 (?.????, ?.????) 0.75 1.5 0.622 (0.618, 0.624) 0.03670 (0.03632, 0.03680) 0.02468 0.01201 0.02186 -0.1221 (?.????, ?.????) 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 0.086 (0.083, 0.089) 0.02952 (0.02928, 0.03038) 0.01471 0.01480 0.02923 -0.1564 (-0.1528, -0.1630) 0.75 -2.0 0.194 (0.187, 0.195) 0.02885 (0.02867, 0.02944) 0.01405 0.01480 0.02741 -0.1484 (?.????, ?.????) 0.75 -1.5 0.238 (?.???, ?.???) 0.02877 (?.?????, ?.?????) 0.01397 0.01480 0.02659 -0.1392 (?.????, ?.????) 0.75 -1.0 0.294 (0.290, 0.305) 0.02925 (0.02910, 0.03001) 0.01449 0.01476 0.02595 -0.1347 (?.????, ?.????) 0.75 0.0 0.400 (?.???, ?.???) 0.03140 (?.?????, ?.?????) 0.01670 0.01470 0.02526 -0.1290 (?.????, ?.????) 0.75 1.0 0.484 (?.???, ?.???) 0.03413 (?.?????, ?.?????) 0.01954 0.01459 0.02514 -0.1156 (?.????, ?.????) 0.75 1.5 0.544 (0.542, 0.551) 0.03733 (0.03705, 0.03749) 0.02283 0.01450 0.02596 -0.1128 (?.????, ?.????) UPPER SURFACE TRANSITION LOCATIONS (% CHORD) XROOT XKINK XE.844 XTIP 5. 15. 7.6 5. LOWER SURFACE TRANSITION LOCATION (% CHORD) XLO 25. CASE 3 TRIPPED VS. FULLY TURBULENT DRAG (OPTIONAL) -------------------------------- WING/BODY MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT TYPE 0.75 ?.??? 0.50? ?.????? ?.????? ?.????? ?.???? TRIPPED 0.75 ?.??? 0.50? ?.????? ?.????? ?.????? ?.???? FULLY TURBULENT WING/BODY/NACELLE/PYLON MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT TYPE 0.75 ?.??? 0.50? ?.????? ?.????? ?.????? ?.???? TRIPPED 0.75 ?.??? 0.50? ?.????? ?.????? ?.????? ?.???? FULLY TURBULENT CASE 4 DRAG RISE (OPTIONAL) ------------------------------------------- WING/BODY MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT 0.50 ?.??? 0.50? ?.????? ?.????? ?.????? ?.???? 0.60 ?.??? 0.50? ?.????? ?.????? ?.????? ?.???? 0.70 ?.??? 0.50? ?.????? ?.????? ?.????? ?.???? 0.72 ?.??? 0.50? ?.????? ?.????? ?.????? ?.???? 0.74 ?.??? 0.50? ?.????? ?.????? ?.????? ?.???? 0.75 ?.??? 0.50? ?.????? ?.????? ?.????? ?.???? 0.76 ?.??? 0.50? ?.????? ?.????? ?.????? ?.???? 0.77 ?.??? 0.50? ?.????? ?.????? ?.????? ?.???? WING/BODY/NACELLE/PYLON MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT 0.50 ?.??? 0.50? ?.????? ?.????? ?.????? ?.???? 0.60 ?.??? 0.50? ?.????? ?.????? ?.????? ?.???? 0.70 ?.??? 0.50? ?.????? ?.????? ?.????? ?.???? 0.72 ?.??? 0.50? ?.????? ?.????? ?.????? ?.???? 0.74 ?.??? 0.50? ?.????? ?.????? ?.????? ?.???? 0.75 ?.??? 0.50? ?.????? ?.????? ?.????? ?.???? 0.76 ?.??? 0.50? ?.????? ?.????? ?.????? ?.???? 0.77 ?.??? 0.50? ?.????? ?.????? ?.????? ?.???? 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. * 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)