Date: July 25, 2003 PARTICIPANT INFORMATION ----------------------- Name: Elizabeth Lee-Rausch*, Eric Nielsen, Micheal Park, and Russ Rausch Email: e.m.lee-rausch@larc.nasa.gov;e.j.nielsen@larc;m.a.park@larc;r.d.rausch@larc Phone: 757-864-8422 Address: Mail Stop 128 Address: NASA Langley Research Center Address: Hampton, Virginia 23681 Address: Address: Address: SOLVER INFORMATION -------------------- Method Name: HEFSS (formerly FUN3D) Basic Algorithm: RANS Node-Based, Implicit, Finite-Volume, Roe's Flux Difference Splitting Turbulence Model: SA (loosely coupled) Residual: L2 Norm of density Miscellaneous: Full Navier-Stokes GRID INFORMATION -------------------- Grid-Generator Name: VGridNS version 3.5 Grid Type: Unstructured Tetrahedra COARSE GRID SIZE WB WBNP ----------------------------------------- Zones: 1 1 Field Nodes: 1,121,301 1,827,470 Field Cells: 6,558,758 10,715,204 Boundary Nodes: 25,104 45,015 Boundary Faces: 49,901 89,738 BL 1st-Cell Size: 0.00144 0.00144 BL Max-Growth Rate: 1.20-1.32 1.20-1.32 BL Cells: ~26 ~24 Miscellaneous: Due to the grid generation there is not the same number of BL cells- MEDIUM GRID SIZE WB WBNP ----------------------------------------- Zones: 1 1 Field Nodes: 3,010,307 4,751,207 Field Cells: 17,635,283 27,875,222 Boundary Nodes: 55,069 96,611 Boundary Faces: 109,679 192,785 BL 1st-Cell Size: 0.00100 0.00100 BL Max-Growth Rate: 1.20-1.32 1.20-1.32 BL Cells: ~26 ~24 Miscellaneous: Due to the grid generation there is not the same number of BL cells- FINE GRID SIZE WB WBNP ----------------------------------------- Zones: 1 1 Field Nodes: 9,133,352 10,278,588 Field Cells: 53,653,279 60,412,948 Boundary Nodes: 118,903 165,941 Boundary Faces: 237,121 331,303 BL 1st-Cell Size: 0.000695 0.000794 BL Max-Growth Rate: 1.13-1.24 1.13-1.22 BL Cells: ~33 ~28 Miscellaneous: Due to the grid generation there is not the same number of BL cells- SOLUTION INFORMATION -------------------- Computer Platform: Beowulf Linux Cluster # Processors: 9- 2.4 Ghz Pentium 4 nodes with 2GB of 800Mhz Rambus memory Operating System: Linux Compiler: Intel 7.0 Run Time CPU: 375 hours for 2500 iterations Run Time Wall-Clock: 42 hours for 2500 iterations Memory Requirements: 14.25GB Miscellaneous: This is "typical" for 4.75 million node mesh for one angle of attack CASE 1 SINGLE-POINT GRID CONVERGENCE STUDY (REQUIRED) --------------------------------------- WING/BODY GRID_SIZE MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT LOG(RESID_DROP) 1121301. 0.75 0.102 0.500 0.03034 0.01812 0.01221 -.1309 5.5738 (6.4251 max/final) 3010307. 0.75 0.201 0.500 0.02857 0.01646 0.01210 -.1269 7.4641 (9.8987 max/final) 9133352. 0.75 0.263 0.500 0.02812 0.01600 0.01212 -.1254 5.6974 (8.2718 max/final) WING/BODY/NACELLE/PYLON GRID_SIZE MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT LOG(RESID_DROP) 1827470. 0.75 0.679 0.500 0.03524 0.02092 0.01432 -.1280 6.0829 (9.0466 max/final) 4751207. 0.75 0.945 0.500 0.03341 0.01918 0.01423 -.1165 4.9378 (8.0432 max/final) 10278588. 0.75 1.015 0.500 0.03357 0.01933 0.01424 -.1120 4.5102 (7.6808 max /final) 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 198.10 -90.50 11.70 227.40 -74.40 -6.70 235.60 -69.70 -.30 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 191.40 -95.20 17.60 223.60 -75.60 -5.30 236.40 -70.10 000.80 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 0.129 0.02009 0.00779 0.01230 0.01953 -0.1427 0.75 -2.0 0.247 0.02147 0.00918 0.01230 0.01941 -0.1385 0.75 -1.5 0.305 0.02259 0.01031 0.01228 0.01945 -0.1363 0.75 -1.0 0.363 0.02399 0.01174 0.01225 0.01955 -0.1341 0.75 0.0 0.477 0.02766 0.01553 0.01214 0.01999 -0.1285 0.75 1.0 0.591 0.03319 0.02128 0.01191 0.02141 -0.1193 0.75 1.5 0.647 0.03744 0.02571 0.01173 0.02332 -0.1136 WING/BODY/NACELLE/PYLON MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CD-CL2/PA CM_TOT 0.75 -3.0 0.101 0.02991 0.01534 0.01457 0.02957 -0.1473 0.75 -2.0 0.208 0.02928 0.01473 0.01455 0.02782 -0.1378 0.75 -1.5 0.259 0.02944 0.01492 0.01452 0.02718 -0.1327 * 0.75 -1.0 0.303 0.0296 0.0151 0.0145 0.02650 -0.128 0.75 0.0 0.398 0.02986 0.01545 0.01441 0.02452 -0.1288 0.75 1.0 0.506 0.03376 0.01954 0.01422 0.02512 -0.1151 0.75 1.5 0.561 0.03683 0.02276 0.01407 0.02620 -0.1081 *converged but oscillatory +- 0.003 in lift +- 0.0003 in drag +- 0.003 in pitching moment FULLY TURBULENT 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 0.059 0.500 0.02747 0.01586 0.01161 -0.1352 TRIPPED 0.75 0.201 0.500 0.02857 0.01646 0.01210 -0.1269 FULLY TURBULENT WING/BODY/NACELLE/PYLON MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT TYPE 0.75 0.860 0.500 0.03305 0.01939 0.01366 -0.1179 TRIPPED 0.75 0.945 0.500 0.03341 0.01918 0.01423 -0.1165 FULLY TURBULENT UPPER SURFACE TRANSITION LOCATIONS (% CHORD) XROOT XKINK XE.844 XTIP 5. 15. 15. 5. LOWER SURFACE TRANSITION LOCATION (% CHORD) XLO 25. 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. * 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)