Date: PARTICIPANT INFORMATION ----------------------- Name: Akio OCHI Email: ochi_a@khi.co.jp Phone: +81-583-82-5346 Address: Kawasaki-cho, 1 Address: Kakamigahara, 504-8710 Address: Gifu Pref., Japan Address: Address: Address: SOLVER INFORMATION -------------------- Method Name: UG3 Basic Algorithm: Cell centered unstructured finite volume method Turbulence Model: Spalart-Allmaras Residual: rms of density change Miscellaneous: Spatial (MUSCL+SHUS), Time integ. (MFGS Implicit scheme) GRID INFORMATION -------------------- Grid-Generator Name: PUFGG Grid Type: Hybrid unstructured grid COARSE GRID SIZE WB WBNP ----------------------------------------- Zones: 1 1 Field Nodes: 1568667 2831155 Field Cells: 1868859 3262878 Boundary Nodes: 22195 48241 Boundary Faces: 22440 48525 BL 1st-Cell Size: 2.0e-3 mm 2.0e-3 mm BL Max-Growth Rate: 1.7 1.7 BL Cells: 30 30 Miscellaneous: wing surface grid chord x span : 208 x 67(WB),84(WBNP) MEDIUM GRID SIZE WB WBNP ----------------------------------------- Zones: 1 1 Field Nodes: 3594881 5905535 Field Cells: 4071579 6670800 Boundary Nodes: 57056 104727 Boundary Faces: 57184 104948 BL 1st-Cell Size: 2.0e-3 mm 2.0e-3 mm BL Max-Growth Rate: 1.7 1.7 BL Cells: 30 30 Miscellaneous: wing surface grid chord x span : 208 x 93(WB),163(WBNP) FINE GRID SIZE WB WBNP ----------------------------------------- Zones: 1 1 Field Nodes: 4681025 8626576 Field Cells: 5248829 9732585 Boundary Nodes: 72997 160328 Boundary Faces: 73124 160482 BL 1st-Cell Size: 2.0e-3 mm 2.0e-3 mm BL Max-Growth Rate: 1.4 1.4 BL Cells: 35 35 Miscellaneous: wing surface grid chord x span : 408 x 88(WB),163(WBNP) SOLUTION INFORMATION -------------------- Computer Platform: PC Cluster (Pentium4 2.8GHz) # Processors: 24 Operating System: Linux Compiler: PGI Fortran v4.1 Run Time CPU: 12 days ( time * num of proc. ) Run Time Wall-Clock: 1.5 days Memory Requirements: 400 bytes / cells ( 4GB per 10M cells) Miscellaneous: CASE 1 SINGLE-POINT GRID CONVERGENCE STUDY (REQUIRED) --------------------------------------- WING/BODY GRID_SIZE MACH ALPHA CL_TOT (min, max) CD_TOT (min, max) CD_PR CD_SF CM_TOT (min, max) RESID_DROP 1868859. 0.75 -.151 0.500 (0.500, 0.500) 0.02893 (0.02892, 0.02894) 0.01560 0.01333 -.1509 (-.1511, -.1507) 1.e-5 4071579. 0.75 0.292 0.500 (0.500, 0.500) 0.02962 (0.02962, 0.02962) 0.01642 0.01320 -.1351 (-.1353, -.1350) 1.e-5 5248829. 0.75 0.148 0.500 (0.500, 0.500) 0.02913 (0.02911, 0.02914) 0.01594 0.01318 -.1398 (-.1398, -.1398) 5.e-6 WING/BODY/NACELLE/PYLON GRID_SIZE MACH ALPHA CL_TOT (min, max) CD_TOT (min, max) CD_PR CD_SF CM_TOT (min, max) RESID_DROP 3262878. 0.75 0.579 0.500 (5.000, 0.500) 0.03390 (0.03389, 0.03391) 0.01820 0.01570 -.1391 (-.1392, -.1390) 1.e-5 6670800. 0.75 0.975 0.500 (5.000, 0.500) 0.03515 (0.03515, 0.03515) 0.01957 0.01588 -.1254 (-.1255, -.1252) 1.e-5 9732585. 0.75 0.820 0.500 (5.000, 0.501) 0.03460 (0.03456, 0.03463) 0.01885 0.01575 -.1294 (-.1298, -.1290) 1.e-5 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 174. 101. 21. 234. 81. -7. 237. 71.5 6. 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 175. 99. 18. 234. 82. -7. 237. 71.5 4. CASE 2 DRAG POLAR - MEDIUM GRID (REQUIRED) --------------------------------- WING/BODY 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 0.134 (0.132, 0.136) 0.01967 (0.01954, 0.01973) 0.00673 0.01294 0.01907 -0.1559 (-.1569, -.1545) 0.75 -2.0 0.250 (0.248, 0.252) 0.02124 (0.02120, 0.02128) 0.00831 0.01292 0.01914 -0.1513 (-.1515, -.1511) 0.75 -1.5 0.308 (0.308, 0.308) 0.02244 (0.02242, 0.02246) 0.00955 0.01290 0.01926 -0.1494 (-.1497, -.1492) 0.75 -1.0 0.363 (0.362, 0.364) 0.02393 (0.02391, 0.02395) 0.01104 0.01289 0.01951 -0.1464 (-.1467, -.1463) 0.75 0.0 0.469 (0.463, 0.472) 0.02771 (0.02763, 0.02775) 0.01505 0.01266 0.02035 -0.1387 (-.1399, -.1372) 0.75 1.0 0.587 (0.588, 0.590) 0.03342 (0.03340, 0.03343) 0.02093 0.01249 0.02186 -0.1334 (-.1338, -.1333) 0.75 1.5 0.643 (0.643, 0.650) 0.03773 (0.03772, 0.03779) 0.02540 0.01233 0.02372 -0.1304 (-.1308, -.1295) 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 0.121 (0.120, 0.121) 0.02890 (0.02888, 0.02902) 0.01349 0.01541 0.02841 -0.1662 (-.1668, -.1658) 0.75 -2.0 0.221 (0.221, 0.222) 0.02856 (0.02854, 0.02857) 0.01311 0.01545 0.02692 -0.1562 (-.1563, -.1558) 0.75 -1.5 0.276 (0.275, 0.276) 0.02875 (0.02873, 0.02877) 0.01337 0.01538 0.02621 -0.1528 (-.1535, -.1524) 0.75 -1.0 0.325 (0.325, 0.325) 0.02925 (0.02922, 0.02926) 0.01397 0.01528 0.02570 -0.1481 (-.1488, -.1477) 0.75 0.0 0.423 (0.422, 0.423) 0.03145 (0.03145, 0.03147) 0.01631 0.01513 0.02546 -0.1380 (-.1382, -.1377) 0.75 1.0 0.518 (0.518, 0.518) 0.03503 (0.03501, 0.03510) 0.02027 0.01475 0.02602 -0.1296 (-.1303, -.1292) 0.75 1.5 0.568 (0.567, 0.568) 0.03794 (0.03792, 0.03799) 0.02320 0.01474 0.02714 -0.1279 (-.1280, -.1278) UPPER SURFACE TRANSITION LOCATIONS (% CHORD) XROOT XKINK XE.844 XTIP 9. 12. 15. 15. LOWER SURFACE TRANSITION LOCATION (% CHORD) XLO 18. CASE 3 TRIPPED VS. FULLY TURBULENT DRAG (OPTIONAL) -------------------------------- WING/BODY MACH ALPHA CL_TOT (min, max) CD_TOT (min, max) CD_PR CD_SF CM_TOT (min, max) TYPE 0.75 0.263 0.500 0.02921 0.01660 0.01262 -0.1373 TRIPPED 0.75 0.292 0.500 0.02962 0.01642 0.01320 -.1351 FULLY TURBULENT 0.75 ?.??? 0.??? (?.???, ?.???) ?.????? (?.?????, ?.?????) ?.????? ?.????? ?.???? (?.????, ?.????) TRIPPED 0.75 ?.??? 0.??? (?.???, ?.???) ?.????? (?.?????, ?.?????) ?.????? ?.????? ?.???? (?.????, ?.????) FULLY TURBULENT WING/BODY/NACELLE/PYLON MACH ALPHA CL_TOT (min, max) CD_TOT (min, max) CD_PR CD_SF CM_TOT (min, max) TYPE 0.75 0.809 0.500 0.03434 0.01952 0.01483 -0.1312 TRIPPED 0.75 0.975 0.500 0.03515 0.01957 0.01588 -.1254 FULLY TURBULENT 0.75 ?.??? 0.??? (?.???, ?.???) ?.????? (?.?????, ?.?????) ?.????? ?.????? ?.???? (?.????, ?.????) TRIPPED 0.75 ?.??? 0.??? (?.???, ?.???) ?.????? (?.?????, ?.?????) ?.????? ?.????? ?.???? (?.????, ?.????) FULLY TURBULENT CASE 4 DRAG RISE (OPTIONAL) ------------------------------------------- WING/BODY MACH ALPHA CL_TOT (min, max) CD_TOT (min, max) CD_PR CD_SF CM_TOT (min, max) 0.50 ?.??? 0.??? (?.???, ?.???) ?.????? (?.?????, ?.?????) ?.????? ?.????? ?.???? (?.????, ?.????) 0.60 ?.??? 0.??? (?.???, ?.???) ?.????? (?.?????, ?.?????) ?.????? ?.????? ?.???? (?.????, ?.????) 0.70 ?.??? 0.??? (?.???, ?.???) ?.????? (?.?????, ?.?????) ?.????? ?.????? ?.???? (?.????, ?.????) 0.72 ?.??? 0.??? (?.???, ?.???) ?.????? (?.?????, ?.?????) ?.????? ?.????? ?.???? (?.????, ?.????) 0.74 ?.??? 0.??? (?.???, ?.???) ?.????? (?.?????, ?.?????) ?.????? ?.????? ?.???? (?.????, ?.????) 0.75 ?.??? 0.??? (?.???, ?.???) ?.????? (?.?????, ?.?????) ?.????? ?.????? ?.???? (?.????, ?.????) 0.76 ?.??? 0.??? (?.???, ?.???) ?.????? (?.?????, ?.?????) ?.????? ?.????? ?.???? (?.????, ?.????) 0.77 ?.??? 0.??? (?.???, ?.???) ?.????? (?.?????, ?.?????) ?.????? ?.????? ?.???? (?.????, ?.????) WING/BODY/NACELLE/PYLON MACH ALPHA CL_TOT (min, max) CD_TOT (min, max) CD_PR CD_SF CM_TOT (min, max) 0.50 ?.??? 0.??? (?.???, ?.???) ?.????? (?.?????, ?.?????) ?.????? ?.????? ?.???? (?.????, ?.????) 0.60 ?.??? 0.??? (?.???, ?.???) ?.????? (?.?????, ?.?????) ?.????? ?.????? ?.???? (?.????, ?.????) 0.70 ?.??? 0.??? (?.???, ?.???) ?.????? (?.?????, ?.?????) ?.????? ?.????? ?.???? (?.????, ?.????) 0.72 ?.??? 0.??? (?.???, ?.???) ?.????? (?.?????, ?.?????) ?.????? ?.????? ?.???? (?.????, ?.????) 0.74 ?.??? 0.??? (?.???, ?.???) ?.????? (?.?????, ?.?????) ?.????? ?.????? ?.???? (?.????, ?.????) 0.75 ?.??? 0.??? (?.???, ?.???) ?.????? (?.?????, ?.?????) ?.????? ?.????? ?.???? (?.????, ?.????) 0.76 ?.??? 0.??? (?.???, ?.???) ?.????? (?.?????, ?.?????) ?.????? ?.????? ?.???? (?.????, ?.????) 0.77 ?.??? 0.??? (?.???, ?.???) ?.????? (?.?????, ?.?????) ?.????? ?.????? ?.???? (?.????, ?.????) 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. * RESID_DROP (F10.5) Initial Residual/Final Residual * 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)