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: Spalart-Almaras 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 Field Nodes: 8895409 Field Cells: 8.26M Boundary Nodes: 49580 Boundary Faces: BL 1st-Cell Size: y+~1.0 BL Max-Growth Rate: 1.17 - 1.24 BL Cells: 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 2100000 0.750 -0.011 0.49989 0.02847 0.01514 0.01333 -0.16333 3896149 0.750 -0.046 0.49991 0.02847 0.01516 0.01332 -0.16859 8895409 0.750 -0.026 0.50000 0.02848 0.01531 0.01318 -0.16006 WING/BODY/NACELLE/PYLON GRID_SIZE MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT 6091402 0.75 0.49 0.50078 0.03347 0.01813 0.01534 -0.14413 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 227.2 75.2 -3.3 232.5 70.8 -9.0 230.0 76.1 -6.0 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 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 -0.906 0.39993 0.02496 0.01155 0.01340 0.01960 -0.16205 0.75 -0.046 0.49991 0.02847 0.01516 0.01332 0.02010 -0.15650 0.75 0.490 0.56315 0.03133 0.01811 0.01322 0.02070 -0.15229 0.75 1.000 0.62326 0.03479 0.02171 0.01308 0.02177 -0.14741 0.75 1.500 0.68107 0.03937 0.02646 0.01290 0.02383 -0.14251 WING/BODY/NACELLE/PYLON MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CD-CL2/PA CM_TOT 0.75 -3.000 ?.??? ?.????? ?.????? ?.????? ?.????? ?.???? 0.75 -2.000 ?.??? ?.????? ?.????? ?.????? ?.????? ?.???? 0.75 -1.500 ?.??? ?.????? ?.????? ?.????? ?.????? ?.???? 0.75 -1.000 ?.??? ?.????? ?.????? ?.????? ?.????? ?.???? 0.75 0.000 ?.??? ?.????? ?.????? ?.????? ?.????? ?.???? 0.75 1.000 ?.??? ?.????? ?.????? ?.????? ?.????? ?.???? 0.75 1.500 ?.??? ?.????? ?.????? ?.????? ?.????? ?.???? UPPER SURFACE TRANSITION LOCATIONS (% CHORD) XROOT XKINK XE.844 XTIP 0. 0. 0. 0. LOWER SURFACE TRANSITION LOCATION (% CHORD) XLO 0. -------------------------------- 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 ?.????? ?.????? ?.????? ?.????? ?.????? ?.???? TRIPPED 0.75 ?.????? ?.????? ?.????? ?.????? ?.????? ?.???? 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 0.60 0.467 0.50000 0.02791 0.01406 0.01385 -0.13625 0.70 0.159 0.50001 0.02815 0.01462 0.01352 -0.14935 0.75 -0.046 0.49991 0.02847 0.01516 0.01332 -0.15850 0.76 -0.095 0.49991 0.02859 0.01532 0.01327 -0.16091 0.77 -0.136 0.49993 0.02884 0.01564 0.01320 -0.16317 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) Additional Comments Grid convergence study for Wing-Body configuration only. Runs were made for both CL=0.50 and angle-of-attack=0.49 degrees. An extra-fine grid was also computed for angle-of-attack=0.49 degrees. FINE GRID SIZE WB WBNP -------------------- Zones: 29 Field Nodes: 13.2M Field Cells: Boundary Nodes: Boundary Faces: BL 1st-Cell Size: y+~0.8 BL Max-Growth Rate: 1.17 - 1.24 BL Cells: 36 Miscellaneous: Blunt trailing edge with embedded grid block GRID_SIZE MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT 2100000 0.750 0.490 0.55881 0.03110 0.01787 0.01323 -0.1472 3896149 0.750 0.490 0.56315 0.03133 0.01811 0.01322 -0.1523 8895409 0.750 0.490 0.56033 0.03120 0.01811 0.01308 -0.1441 13223309 0.750 0.490 0.56662 0.03142 0.01834 0.01308 -0.1494 Grid Convergence Study not carried out for Wing/Body/Nacelle/Pylon because of the difficulty in avoiding excessive flow separation on the inboard side of the pylon at CL~0.5. However, for conditions not plagued with excessive flow separation we would expect our solutions to exhibit minimal drag variation with grid size similar to what is seen for the wing/body configuration. Drag polar studies were carried out for both configurations using the Menter k-w SST turbulence model and are reported in a separate results entry.