Date: 05/23/03 PARTICIPANT INFORMATION ----------------------- Name: Hong Luo Email: hong.luo@saic.com Phone: (703) 676-5957 Address: 1710 SAIC Dr., MS 2-6-9 Address: Address: Address: Address: Address: SOLVER INFORMATION -------------------- Method Name: FEFLO Basic Algorithm: Matrix-free implicit unstructured tetrahedral grid method Turbulence Model: Spart-Allmaras one-equation model Miscellaneous: GRID INFORMATION -------------------- Grid-Generator Name: Grid Type: unstructured tetrahedral grid COARSE GRID SIZE WB WBNP ----------------------------------------- Zones: Field Nodes: 1121301 1827470 Field Cells: 6558758 10715204 Boundary Nodes: 38879 58803 Boundary Faces: 77754 117606 BL 1st-Cell Size: BL Max-Growth Rate: BL Cells: Miscellaneous: coarse grid by LARC MEDIUM GRID SIZE WB WBNP ----------------------------------------- Zones: Field Nodes: 1779420 2419388 Field Cells: 10504337 14304595 Boundary Nodes: 57009 70580 Boundary Faces: 114014 141160 BL 1st-Cell Size: BL Max-Growth Rate: BL Cells: Miscellaneous: coarse grid by Swansea FINE GRID SIZE WB WBNP ----------------------------------------- Zones: Field Nodes: 2390716 3682535 Field Cells: 13977040 21564720 Boundary Nodes: 93663 134802 Boundary Faces: 187322 269604 BL 1st-Cell Size: BL Max-Growth Rate: BL Cells: Miscellaneous: coarse mesh by DLR SOLUTION INFORMATION -------------------- Computer Platform: IBM SP4 # Processors: 8 Operating System: IBM AIX Compiler: IBM xlf 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 1121301 0.75 0.376 0.499 0.03165 0.01873 0.01292 -0.1244 1779420 0.75 0.280 0.500 0.03038 0.01775 0.01263 -0.1281 2390716 0.75 0.275 0.499 0.03034 0.01803 0.01231 -0.1332 WING/BODY/NACELLE/PYLON GRID_SIZE MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT 1827470 0.75 0.950 0.497 0.03719 0.02161 0.01558 -0.1205 2419388 0.75 0.843 0.498 0.03658 0.02062 0.01596 -0.1216 3682535 0.75 0.800 0.501 0.03631 0.02081 0.01550 -0.1242 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 495.30 101.73 20.19 580.23 86.61 -6.61 585.00 71.05 3.79 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 523.41 84.54 2.92 583.21 77.60 -9.25 587.93 67.16 -6.38 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 0.128 0.02170 0.00891 0.01279 0.02115 -0.1483 0.75 -2.0 0.242 0.02299 0.01022 0.01278 0.02103 -0.1423 0.75 -1.5 0.298 0.02408 0.01131 0.01278 0.02110 -0.1394 0.75 -1.0 0.354 0.02543 0.01269 0.01274 0.02123 -0.1364 0.75 0.0 0.469 0.02916 0.01643 0.01273 0.02179 -0.1305 0.75 1.0 0.585 0.03458 0.02212 0.01246 0.02311 -0.1222 0.75 1.5 0.645 0.03887 0.02655 0.01232 0.02493 -0.1184 WING/BODY/NACELLE/PYLON MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CD-CL2/PA CM_TOT 0.75 -3.0 0.088 0.03303 0.01742 0.01561 0.03277 -0.1495 0.75 -2.0 0.172 0.03128 0.01558 0.01570 0.03029 -0.1428 0.75 -1.5 0.230 0.03078 0.01512 0.01566 0.02900 -0.1352 0.75 -1.0 0.285 0.03080 0.01518 0.01562 0.02808 -0.1340 0.75 0.0 0.394 0.03268 0.01707 0.01561 0.02748 -0.1274 0.75 1.0 0.520 0.03767 0.02154 0.01612 0.02861 -0.1206 0.75 1.5 0.580 0.04110 0.02507 0.01602 0.02983 -0.1134 UPPER SURFACE TRANSITION LOCATIONS (% CHORD) XROOT XKINK XE.844 XTIP Fully turbulent LOWER SURFACE TRANSITION LOCATION (% CHORD) XLO Fully turbulent 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)