Date: May 26, 2003 PARTICIPANT INFORMATION ----------------------- Name: Thomas Scheidegger Email: tes@fluent.com Phone: 603 643 2600 x236 Name: Greg Stuckert Email: gks@fluent.com Phone: 603 643 2600 x243 Address: Fluent Inc. Address: 10 Cavendish Court Address: Centerra Resource Park Address: Lebanon, NH 03766-1442 SOLVER INFORMATION -------------------- Method Name: Fluent 6.1 Basic Algorithm: unstructured finite-volume, SIMPLE, second-order upwind Turbulence Model: realizable k-epsilon Miscellaneous: GRID INFORMATION -------------------- Grid-Generator Name: ICEM Grid Type: multi-block COARSE GRID SIZE WB WBNP ----------------------------------------- Zones: Field Nodes: Field Cells: 3.37M 4.79M Boundary Nodes: Boundary Faces: BL 1st-Cell Size: BL Max-Growth Rate: BL Cells: Miscellaneous: distributed DPW2 grids MEDIUM GRID SIZE WB WBNP ----------------------------------------- Zones: Field Nodes: Field Cells: 5.72M 8.29M Boundary Nodes: Boundary Faces: BL 1st-Cell Size: BL Max-Growth Rate: BL Cells: Miscellaneous: distributed DPW2 grids FINE GRID SIZE WB WBNP ----------------------------------------- Zones: Field Nodes: Field Cells: 9.97M 13.48M Boundary Nodes: Boundary Faces: BL 1st-Cell Size: BL Max-Growth Rate: BL Cells: Miscellaneous: distributed DPW2 grids SOLUTION INFORMATION -------------------- Computer Platform: PC Intel Pentium, 2.2GHz # Processors: 4 nodes for coarse and medium size grids, 8 nodes for gine grids Operating System: Linux Red Hat 7.2 Compiler: Run Time CPU: WB coarse grid: 25.88 sec/iteration on 4 nodes WBNP fine grid: 55.27 sec/iteration on 8 nodes Run Time Wall-Clock: Memory Requirements: 2.8GB for WB_coarse, 4.8GM for WB_medium, 8.4GB for WB_fine 4.0GB for WBNP_coarse, 6.8GB for WBNP_medium, 11.1GB for WBNP_fine Miscellaneous: CASE 1 SINGLE-POINT GRID CONVERGENCE STUDY (REQUIRED) --------------------------------------- WING/BODY GRID_SIZE MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT 3374848. 0.75 0.201 0.500 0.02965 0.01655 0.01310 -0.1362 5715968. 0.75 0.201 0.502 0.02903 0.01613 0.01289 -0.1377 9966592. 0.75 0.201 0.497 0.02920 0.01596 0.01324 -0.1353 WING/BODY/NACELLE/PYLON GRID_SIZE MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT 4787392. 0.75 0.626 0.501 0.03567 0.01990 0.01577 -0.1353 8290304. 0.75 0.626 0.497 0.03457 0.01859 0.01598 -0.1366 13481984. 0.75 0.626 0.503 0.03370 0.01809 0.01561 -0.1400 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 150.00 ???.?? 14.98 236.15 85.03 -7.83 242.19 71.17 4.19 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 140.00 ???.?? 17.20 235.69 85.11 -7.65 241.00 71.17 -4.18 CASE 2 DRAG POLAR - COARSE GRID (REQUIRED) --------------------------------- WING/BODY MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CD-CL2/PA CM_TOT 0.75 -3.0 0.126 0.02085 0.00749 0.01336 ?.????? -0.1509 0.75 -2.0 0.243 0.02231 0.00898 0.01333 ?.????? -0.1463 0.75 -1.5 0.301 0.02351 0.01021 0.01330 ?.????? -0.1444 0.75 -1.0 0.359 0.02489 0.01164 0.01325 ?.????? -0.1421 0.75 0.0 0.477 0.02871 0.01558 0.01313 ?.????? -0.1377 0.75 1.0 0.600 0.03470 0.02175 0.01295 ?.????? -0.1312 0.75 1.5 0.663 0.03939 0.02658 0.01281 ?.????? -0.1287 WING/BODY/NACELLE/PYLON MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CD-CL2/PA CM_TOT 0.75 -3.0 0.091 0.03039 0.01427 0.01612 ?.????? -0.1678 0.75 -2.0 0.200 0.02978 0.01370 0.01608 ?.????? -0.1586 0.75 -1.5 0.256 0.03003 0.01399 0.01604 ?.????? -0.1542 0.75 -1.0 0.310 0.03071 0.01471 0.01600 ?.????? -0.1493 0.75 0.0 0.425 0.03317 0.01730 0.01587 ?.????? -0.1407 0.75 1.0 0.548 0.03768 0.02197 0.01571 ?.????? -0.1318 0.75 1.5 0.614 0.04138 0.02578 0.01560 ?.????? -0.1274 UPPER SURFACE TRANSITION LOCATIONS (% CHORD) XROOT XKINK XE.844 XTIP 00. 00. 00. 00. LOWER SURFACE TRANSITION LOCATION (% CHORD) XLO 00. 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)