Date: 080103 PARTICIPANT INFORMATION ----------------------- Name: Tony Sclafani Email: tony.sclafani@boeing.com Phone: 714-896-1074 Address: The Boeing Company Address: 5301 Bolsa Avenue Address: Huntington Beach, CA Address: 92647 Address: Address: SOLVER INFORMATION -------------------- Method Name: OVERFLOW MPI v1.8s Basic Algorithm: Roe Upwind Turbulence Model: Spalart-Allmaras 1-equation Residual: RHS L2 Norm Miscellaneous: MPI - Message Passing Interface GRID INFORMATION -------------------- Grid-Generator Name: Surface Grids - ZONI3G/SURGRD, Volume Grids - HYPGEN/LEGRID/PEGASUS5 Grid Type: Structured Overset COARSE GRID SIZE WB WBNP ----------------------------------------- Zones: 12 23 Field Nodes: Field Cells: Boundary Nodes: Boundary Faces: BL 1st-Cell Size: 0.0015 BL Max-Growth Rate: 1.25 BL Cells: Miscellaneous: MEDIUM GRID SIZE WB WBNP ----------------------------------------- Zones: 12 23 Field Nodes: Field Cells: Boundary Nodes: Boundary Faces: BL 1st-Cell Size: 0.0010 BL Max-Growth Rate: 1.25 BL Cells: Miscellaneous: FINE GRID SIZE WB WBNP ----------------------------------------- Zones: 12 23 Field Nodes: Field Cells: Boundary Nodes: Boundary Faces: BL 1st-Cell Size: 0.0007 BL Max-Growth Rate: 1.25 BL Cells: Miscellaneous: SOLUTION INFORMATION -------------------- Computer Platform: Linux PC Cluster # Processors: 8 for WB/Medium, 10 for WBNP/Medium Operating System: Compiler: 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 RESID_DROP 1969356. 0.75 0.050 0.5001 0.02988 0.01604 0.01384 -0.13791 -5.49 6861912. 0.75 0.159 0.5004 0.02886 0.01562 0.01324 -0.13673 -1.99 23150448. 0.75 0.257 0.5000 0.02886 0.01579 0.01307 -0.13527 -2.13 WING/BODY/NACELLE/PYLON GRID_SIZE MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT RESID_DROP 3111239. 0.75 0.649 0.5003 0.03577 0.01942 0.01635 -0.12803 -1.71 10778107. 0.75 0.781 0.4998 0.03427 0.01855 0.01572 -0.12586 -1.83 35867679. 0.75 0.881 0.5000 0.03430 0.01881 0.01549 -0.12346 -2.00 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 151.9 105.4 16.8 233.3 83.8 -7.1 239.4 72.2 8.1 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 144.8 108.7 20.0 232.4 85.4 -6.5 236.7 72.5 9.5 CASE 2 DRAG POLAR - MEDIUM GRID (REQUIRED) --------------------------------- WING/BODY MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CD-CL2/PA CM_TOT 0.75 -3.0 0.1402 0.01910 0.00634 0.01276 0.01844 -0.15522 0.75 -2.0 0.2586 0.02074 0.00798 0.01277 0.01850 -0.15136 0.75 -1.5 0.3176 0.02198 0.00922 0.01276 0.01860 -0.14945 0.75 -1.0 0.3762 0.02348 0.01076 0.01273 0.01874 -0.14746 0.75 0.0 0.4935 0.02745 0.01482 0.01264 0.01929 -0.14272 0.75 1.0 0.6144 0.03354 0.02107 0.01246 0.02089 -0.13633 0.75 1.5 0.6744 0.03818 0.02587 0.01231 0.02294 -0.13293 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 0.1013 (.0988, .1038) .02915 (.02891, .02945) .01423 .01492 .02881 -0.16151 (-.16240, -.16054) 0.75 -2.0 0.2106 (.2090, .2131) .02850 (.02837, .02867) .01331 .01519 .02701 -0.15331 (-.15410, -.15268) 0.75 -1.5 0.2654 (.2649, .2657) .02868 (.02865, .02869) .01363 .01505 .02632 -0.14945 (-.14955, -.14931) 0.75 -1.0 0.3184 (.3184, .3184) .02913 (.02913, .02913) .01409 .01504 .02573 -0.14569 (-.14569, -.14569) 0.75 0.0 0.4250 (.4247, .4255) .03115 (.03112, .03118) .01620 .01496 .02510 -0.13760 (-.13785, -.13735) 0.75 1.0 0.5379 (.5371, .5385) .03522 (.03513, .03530) .02042 .01480 .02553 -0.12874 (-.12935, -.12836) 0.75 1.5 0.5991 (.5984, .5999) .03874 (.03862, .03880) .02401 .01473 .02671 -0.12398 (-.12451, -.12362) UPPER SURFACE TRANSITION LOCATIONS (% CHORD) XROOT XKINK XE.844 XTIP 5. 15. 15. 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 0.050 0.4994 0.02769 0.01506 0.01263 -0.14246 TRIPPED 0.75 0.159 0.5004 0.02886 0.01562 0.01324 -0.13673 FULLY TURBULENT WING/BODY/NACELLE/PYLON MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT TYPE 0.75 0.682 0.5004 0.03360 0.01870 0.01490 -0.13145 TRIPPED 0.75 0.781 0.4998 0.03427 0.01855 0.01572 -0.12586 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) CASE 2 DRAG POLAR - MEDIUM GRID (ADDITIONAL RUNS) --------------------------------- WING/BODY MACH ALPHA CL_TOT CD_TOT CM_TOT TURB MODEL/SCHEME 0.75 -1.00 0.3559 0.02349 -0.14263 Spalart-Allmaras/Central 0.75 0.280 0.5000 0.02873 -0.13563 Spalart-Allmaras/Central 0.75 1.50 0.6319 0.03751 -0.12839 Spalart-Allmaras/Central ------------------------------------------------------------------------ 0.75 -1.00 0.3457 0.02261 -0.13833 Baldwin-Barth/Central 0.75 0.370 0.4995 0.02819 -0.12935 Baldwin-Barth/Central 0.75 1.50 0.6210 0.03619 -0.11945 Baldwin-Barth/Central WING/BODY/NACELLE/PYLON MACH ALPHA CL_TOT CD_TOT CM_TOT TURB MODEL/SCHEME 0.75 -1.00 0.2867 0.02932 -0.14183 Spalart-Allmaras/Central 0.75 0.903 0.5001 0.03465 -0.13090 Spalart-Allmaras/Central 0.75 1.50 0.5285 0.03934 -0.12759 Spalart-Allmaras/Central ------------------------------------------------------------------------ 0.75 -1.00 0.2923 0.02938 -0.13341 Baldwin-Barth/Central 0.75 1.106 0.4996 0.03480 -0.11829 Baldwin-Barth/Central 0.75 1.50 0.5060 0.03838 -0.11575 Baldwin-Barth/Central UPPER SURFACE TRANSITION LOCATIONS (% CHORD) XROOT XKINK XE.844 XTIP 5. 15. 15. 5. LOWER SURFACE TRANSITION LOCATION (% CHORD) XLO 25.