Date: "August 29, 2003 (Revised)" PARTICIPANT INFORMATION ----------------------- Name: Edward N. Tinoco Email: edward.n.tinoco@boeing.com Phone: 425-234-1147 Address: Boeing Commercial Airplanes Address: Mail Code 67-LK Address: P.O. Box 3707 Address: Seattle, WA 98124 Address: USA SOLVER INFORMATION -------------------- Method Name: CFL3D/Zeus Basic Algorithm: Thin layer, Finite Volume, upwind biased and central difference, multi-grid acceleration Turbulence Model: Menter k-w SST Miscellaneous: Zeus is the driver for Surface Grid Generation, Volume Grid Generation, Navier-Stokes Analysis, and Post-processing" GRID INFORMATION -------------------- Grid-Generator Name: BCA-Advancing Front Grid Type: Structured Block, Point-to-Point Matched COARSE GRID SIZE WB WBNP -------------------- Zones: 11 Field Nodes: 2.2M Field Cells: 2.02M Boundary Nodes: 13716 Boundary Faces: BL 1st-Cell Size: y+~1.25 BL Max-Growth Rate: 1.4 - 1.55 BL Cells: 18 Miscellaneous: Blunt trailing edge block MEDIUM GRID SIZE WB WBNP -------------------- Zones: 13 44 Field Nodes: 4.13M 5.97M Field Cells: 3.88M 5.82M Boundary Nodes: 25940 Boundary Faces: BL 1st-Cell Size: y+~1.0 y+~1.0 BL Max-Growth Rate: 1.17 - 1.24 1.17 -1.24 BL Cells: 36 36 Miscellaneous: Blunt trailing edge block FINE GRID SIZE WB WBNP -------------------- Zones: 29 29 Field Nodes: 13.2M 8974927 Field Cells: Boundary Nodes: Boundary Faces: BL 1st-Cell Size: y+~0.8 y+~1.0 BL Max-Growth Rate: 1.17 - 1.24 1.17 -1.24 BL Cells: 36 36 Miscellaneous: Blunt trailing edge block SOLUTION INFORMATION -------------------- Computer Platform: SGI Origin 3800 # Processors: 7-23 processors in parallel Operating System: IRIX 6.5 Compiler: FORTRAN and C Run Time CPU: Run Time Wall-Clock: Memory Requirements: 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 13223309 0.750 0.11900 0.49990 0.02814 0.01547 0.01267 -0.14164 3896149 0.750 0.12500 0.50000 0.02799 0.01538 0.01261 -0.13327 2100000 0.750 0.11900 0.50010 0.02777 0.01529 0.01248 -0.13069 WING/BODY/NACELLE/PYLON GRID_SIZE MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT 6219855 0.75 0.56328 0.50000 0.03346 0.01870 0.01478 -0.14020 8974927 0.75 0.62100 0.49995 0.03360 0.01883 0.01477 -0.13797 SEPARATION BUBBLE GEOMETRY - WING/BODY - Medium Grid, CL=0.54 FS_BUB BL_BUB WL_BUB FS_EYE_W BL_EYE_W WL_EYE_W FS_EYE_B BL_EYE_B WL_EYE_B 218.0 80.80 3.00000 234.40000 71.60000 ???.?? 231.00000 ???.?? -3.3 SEPARATION BUBBLE GEOMETRY - WING/BODY/NACELLE/PYLON - Medium Grid CL=0.56 FS_BUB BL_BUB WL_BUB FS_EYE_W BL_EYE_W WL_EYE_W FS_EYE_B BL_EYE_B WL_EYE_B 208.0 82.00 6.40000 237.50000 76.00000 ???.?? 243.00000 ???.?? -4.0 CASE 2 - POLAR - MEDIUM GRID (REQUIRED) --------------------------------- WING/BODY MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CD-CL2/PA CM_TOT 0.75 -3.000 0.14299 0.01946 0.00661 0.01284 0.01877 -0.16739 0.75 -2.000 0.26076 0.02106 0.00822 0.01283 0.01878 -0.16168 0.75 -1.000 0.37569 0.02369 0.01092 0.01277 0.01896 -0.15544 0.75 0.125 0.50008 0.02800 0.01539 0.01261 0.01962 -0.14603 0.75 0.490 0.54101 0.02986 0.01732 0.01255 0.02005 -0.14117 0.75 1.000 0.59907 0.03313 0.02070 0.01243 0.02111 -0.13378 0.75 1.500 0.65608 0.03748 0.02521 0.01227 0.02306 -0.12678 WING/BODY/NACELLE/PYLON MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CD-CL2/PA CM_TOT 0.75 0.190 0.44729 0.03204 0.01721 0.01482 0.02534 -0.13950 0.75 0.490 0.48975 0.03314 0.01837 0.01479 0.02510 -0.14026 0.75 0.563 0.50000 0.03346 0.01870 0.01478 0.02508 -0.14020 0.75 1.000 0.55582 0.03571 0.02102 0.01470 0.02536 -0.13806 0.75 1.500 0.61313 0.03901 0.02443 0.01456 0.02641 -0.13165 0.75 1.700 0.63399 0.04051 0.02602 0.01449 0.02704 -0.12791 UPPER SURFACE TRANSITION LOCATIONS (% CHORD) XROOT XKINK XE.844 XTIP 0.10 0.10 0.10 0.10 LOWER SURFACE TRANSITION LOCATION (% CHORD) XLO 0.25 -------------------------------- 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 0.009 0.49999 0.02717 0.01500 0.01216 -0.15190 TRIPPED 0.75 0.125 0.50008 0.02800 0.01539 0.01261 -0.14603 FULLY TURBULENT WING/BODY/NACELLE/PYLON MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT TYPE 0.75 0.267 0.50006 0.03223 0.01776 0.01447 -0.15885 TRIPPED 0.75 0.378 0.49991 0.03327 0.01827 0.01500 -0.15153 FULLY TURBULENT CASE 4 - DRAG RISE (OPTIONAL) ------------------------------------------- WING/BODY MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT 0.60 0.555 0.50023 0.02717 0.01406 0.01311 -0.12986 0.70 0.286 0.50033 0.02756 0.01474 0.01281 -0.14013 0.74 0.155 0.49998 0.02787 0.01519 0.01268 -0.14502 0.75 0.125 0.50008 0.02800 0.01539 0.01261 -0.14603 0.76 0.082 0.49998 0.02813 0.01554 0.01259 -0.14759 0.77 0.049 0.49998 0.02835 0.01582 0.01253 -0.14881 WING/BODY/NACELLE/PYLON MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT 0.60 0.773 0.49989 0.03131 0.01583 0.01548 -0.13536 0.70 0.590 0.50013 0.03214 0.01703 0.01512 -0.14290 0.74 0.539 0.49990 0.03299 0.01810 0.01489 -0.14346 0.75 0.563 0.50000 0.03346 0.01870 0.01478 -0.14020 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)