Date: 5 August 2003 PARTICIPANT INFORMATION ----------------------- Name: Chris Rumsey, S. Melissa Rivers, Joe Morrison Email: christopher.l.rumsey@nasa.gov Phone: (757) 864-2165 Address: NASA Langley Research Center Address: MS 128 Address: Hampton, VA 23681 Address: Address: Address: SOLVER INFORMATION -------------------- Method Name: CFL3D Basic Algorithm: finite volume, upwind-biased, Roe FDS Turbulence Model: explicit algebraic stress model in k-omega form (EASM-ko) Residual: log10(L-2 norm of density eqn RHS), using all zones Miscellaneous: note that we are reporting number of orders of magnitude of res drop GRID INFORMATION -------------------- Grid-Generator Name: Grids were supplied by the DPW committee Grid Type: 1-to-1 COARSE GRID SIZE WB WBNP ----------------------------------------- Zones: 21 47 Field Nodes: 3579589 5152355 Field Cells: 3374848 4787392 Boundary Nodes: Boundary Faces: BL 1st-Cell Size: BL Max-Growth Rate: BL Cells: Miscellaneous: MEDIUM GRID SIZE WB WBNP ----------------------------------------- Zones: 27 58 Field Nodes 6038635 8879562 Field Cells: 5715968 8290304 Boundary Nodes: Boundary Faces: BL 1st-Cell Size: BL Max-Growth Rate: BL Cells: Miscellaneous: FINE GRID SIZE WB WBNP ----------------------------------------- Zones: 32 58 Field Nodes: 10421976 14275906 Field Cells: 9966592 13481984 Boundary Nodes: Boundary Faces: BL 1st-Cell Size: BL Max-Growth Rate: BL Cells: Miscellaneous: SOLUTION INFORMATION -------------------- Computer Platform: various (PC, Alpha, SGI, Cray) # Processors: various Operating System: various Compiler: various Run Time CPU: various Run Time Wall-Clock: various Memory Requirements: various Miscellaneous: for cases in which results were steady, no (min, max) info is given below 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 3374848. 0.75 ?.??? 0.50? ?.????? ?.????? ?.????? ?.???? 5715968. 0.75 0.100 0.500 0.0286 0.0155 0.0131 -0.137 3.6 9966592. 0.75 ?.??? 0.50? ?.????? ?.????? ?.????? ?.???? 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 4787392. 0.75 ?.??? 0.50? ?.????? ?.????? ?.????? ?.???? 8290304. 0.75 0.514 0.500 0.0333 0.0179 0.0154 -0.143 3.5 13481984. 0.75 ?.??? 0.50? ?.????? ?.????? ?.????? ?.???? 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 ???.?? ???.?? ???.?? ???.?? ???.?? ???.?? ???.?? ???.?? ???.?? 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 ???.?? ???.?? ???.?? ???.?? ???.?? ???.?? ???.?? ???.?? ???.?? 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 0.141 0.0194 0.0067 0.0127 0.0187 -0.154 0.75 -2.0 ?.??? ?.????? ?.????? ?.????? ?.????? ?.???? 0.75 -1.5 0.320 0.0223 0.0095 0.0127 0.0188 -0.148 0.75 -1.0 ?.??? ?.????? ?.????? ?.????? ?.????? ?.???? 0.75 0.0 0.497 0.0278 0.0152 0.0126 0.0195 -0.141 0.75 1.0 ?.??? ?.????? ?.????? ?.????? ?.????? ?.???? 0.75 1.5 0.678 0.0386 0.0262 0.0124 0.0231 -0.131 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 ?.??? ?.????? ?.????? ?.????? ?.????? ?.???? 0.75 -2.0 ?.??? ?.????? ?.????? ?.????? ?.????? ?.???? 0.75 -1.5 ?.??? ?.????? ?.????? ?.????? ?.????? ?.???? 0.75 -1.0 ?.??? ?.????? ?.????? ?.????? ?.????? ?.???? 0.75 0.0 ?.??? ?.????? ?.????? ?.????? ?.????? ?.???? 0.75 1.0 ?.??? ?.????? ?.????? ?.????? ?.????? ?.???? 0.75 1.5 ?.??? ?.????? ?.????? ?.????? ?.????? ?.???? 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 (min, max) CD_TOT (min, max) CD_PR CD_SF CM_TOT (min, max) TYPE 0.75 ?.??? 0.50? ?.????? ?.????? ?.????? ?.???? TRIPPED 0.75 ?.??? 0.50? ?.????? ?.????? ?.????? ?.???? 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 ?.??? 0.50? ?.????? ?.????? ?.????? ?.???? 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) (AR=9.436) * CM_TOT (F10.4) Total Moment Coefficient. * RESID_DROP (F10.5) LOG10(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) EXTRA INFORMATION: SEPARATION BUBBLE GEOMETRY - WING/BODY - MEDIUM 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 173. 86. 3. 236. 77. -9. 241. 68. -3. SEPARATION BUBBLE GEOMETRY - WING/BODY/NACELLE/PYLON - MEDIUM 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 169. 92. 6. 235. 76. -9. 240. 69. -3.