Date: 27 May, 2003 PARTICIPANT INFORMATION ----------------------- Name: Ken Wurtzler Major Scott Morton Email: wurtzler@cobaltcfd.com Scott.Morton@usafa.af.mil Phone: 937-902-6107 719-333-9387 Address: Cobalt Solutions, LLC HQ USAFA/DFANL Address: 4169 Sherel Ln 2410 Faculty Dr., Suite 108 Address: Cincinnati, OH 45209 USAF Academy, CO 80840-6400 Address: Address: Address: SOLVER INFORMATION -------------------- Method Name: Cobalt Basic Algorithm: Euler/Navier-Stokes unstructured grid flow solver. The spatial operator is based on Godunov's first-order accurate finite-volume method. Second-order accuracy is achieved via van Leer's MUSCL ideas. The temporal operator is a point-implicit method with first- and second-order accuracy. Turbulence Model: Menter's SST Miscellaneous: DR/DT - derivative of density with respect to time summed over the whole domain GRID INFORMATION -------------------- Grid-Generator Name: VGRIDns Grid Type: hybrid (tets/prisms) COARSE GRID SIZE WB WBNP ----------------------------------------- Zones: 1 1 Field Nodes: Field Cells: 1,172,913 tets 1,261,231 tets Boundary Nodes: 65,410 73,913 Boundary Faces: 130,816 147,826 Viscous Faces: 122,141 139,600 BL 1st-Cell Size: 0.003 0.003 BL Max-Growth Rate: 1.25 1.25 BL Cells: 4,095,627 tets 4,852,819 Miscellaneous: ifact = 1.30 5,268,540 tets -> 3,802,848 tets/prisms WB 6,114,050 tets -> 4,718,050 tets/prisms WBNP MEDIUM GRID SIZE WB WBNP ----------------------------------------- Zones: 1 1 Field Nodes: Field Cells: 1,610,385 tets 1,731,953 tets Boundary Nodes: 81,608 92,473 Boundary Faces: 163,212 184,946 Viscous Faces: 153,234 175,550 BL 1st-Cell Size: 0.003 0.003 BL Max-Growth Rate: 1.25 1.25 BL Cells: 5,104,437 tets 6,065,574 tets Miscellaneous: ifact = 1.15 6,714,822 tets -> 4,876,014 tets/prisms WB 7,797,527 tets -> 6,042,027 tets/prisms WBNP FINE GRID SIZE WB WBNP ----------------------------------------- Zones: 1 1 Field Nodes: Field Cells: 2,320,810 tets 2,518,535 tets Boundary Nodes: 105,943 121,853 Boundary Faces: 211,882 243,706 Viscous Faces: 200,133 232,572 BL 1st-Cell Size: 0.003 0.003 BL Max-Growth Rate: 1.25 1.25 BL Cells: 6,661,175 tets 8,010,143 Miscellaneous: ifact = 1.00 8,975,988 tets -> 6,574,392 tets/prisms WB 10,528,678 tets -> 8,202,958 tets/prisms WBNP SOLUTION INFORMATION -------------------- Computer Platform: IBM SP3/SP4 # Processors: 256 Processors (IBM SP3 16-way nodes) Operating System: AIX 5.1 Compiler: Run Time CPU: 644 CPU hours (6.5 million cells wing-body grid, Alpha = 0.0) Run Time Wall-Clock: 2.5 hours (6.5 million cells wing-body grid, Alpha = 0.0) Memory Requirements: 1.9Gb (6.5 million cells wing-body grid) 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 3,802,848 0.75 0.299 0.50003 3.0399E-02 2.0793E-02 9.6062E-03 -1.1949E-01 4,876,014 0.75 0.292 0.49932 2.9716E-02 2.0014E-02 9.7027E-03 -1.1922E-01 6,574,392 0.75 0.303 0.50028 2.8888E-02 1.9128E-02 9.7597E-03 -1.2007E-01 WING/BODY/NACELLE/PYLON GRID_SIZE MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT 4,718,050 0.75 0.801 0.49825 3.3932E-02 2.3231E-02 1.0701E-02 -1.1970E-01 6,042,027 0.75 0.810 0.50021 3.3141E-02 2.2367E-02 1.0774E-02 -1.2144E-01 8,202,958 0.75 0.813 0.50026 3.2067E-02 2.1184E-02 1.0884E-02 -1.1959E-01 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 207.867 93.739 3.999 231.552 81.170 -6.920 238.842 67.737 -4.893 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 212.142 83.917 1.973 232.243 75.150 -7.908 237.265 67.579 -5.251 RESIDUAL DROP - DR/DT - 2.719E+02 --> 2.580E-03 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 0.1174 0.020063 0.010160 0.009902 0.019597 -0.13099 0.75 -2.0 0.2356 0.021043 0.011123 0.009919 0.019168 -0.12980 0.75 -1.5 0.2939 0.022068 0.012152 0.009915 0.019151 -0.12835 0.75 -1.0 0.3509 0.023596 0.013713 0.009882 0.019439 -0.12663 0.75 0.0 0.4654 0.027479 0.017685 0.009794 0.020167 -0.12159 0.75 1.0 0.5818 0.033263 0.023647 0.009615 0.021838 -0.11456 0.75 1.5 0.6404 0.037739 0.028262 0.009477 0.023894 -0.11134 WING/BODY/NACELLE/PYLON MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CD-CL2/PA CM_TOT 0.75 -3.0 0.1022 0.027717 0.016735 0.010982 0.027944 -0.14829 0.75 -2.0 0.2024 0.027097 0.016129 0.010968 0.026293 -0.13857 0.75 -1.5 0.2549 0.027110 0.016142 0.010968 0.025496 -0.13608 0.75 -1.0 0.2899 0.027067 0.016112 0.010955 0.024776 -0.13214 0.75 0.0 0.3935 0.029423 0.018514 0.010910 0.025072 -0.12264 0.75 1.0 0.5171 0.033479 0.022693 0.010786 0.025032 -0.11607 0.75 1.5 0.5849 0.036942 0.026249 0.010693 0.025972 -0.11379 UPPER SURFACE TRANSITION LOCATIONS (% CHORD) XROOT XKINK XE.844 XTIP ??. ??. ??. ??. LOWER SURFACE TRANSITION LOCATION (% CHORD) XLO ??. 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)