Date: 8/1/03 PARTICIPANT INFORMATION ----------------------- Name: Dimitri Mavriplis Email: dimitri@nianet.org Phone: 757-766-1828 Address: National Institute of Aerospace Address: 144 Research Drive Address: Hampton, VA 23666 Address: USA Address: Address: SOLVER INFORMATION -------------------- Method Name: NSU3D Basic Algorithm: Unstructured, Mixed elements, Matrix dissipation, Agglomeration Multigrid Turbulence Model: Spalart Allmaras Miscellaneous: GRID INFORMATION -------------------- Grid-Generator Name: VGRIDns version3.5 Grid Type: Unstructured Tetrahedral with viscous tets merged into prisms in post-processing step (not part of VGRID) 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 an exact number of BL cells- BL cells (tetrahedra) are merged into prisms, yielding 3 times fewer 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 an exact number of BL cells- BL cells (tetrahedra) are merged into prisms, yielding 3 times fewer 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 an exact number of BL cells- BL cells (tetrahedra) are merged into prisms, yielding 3 times fewer cells. SOLUTION INFORMATION (for intermediate wing-body (~3M pts): others scale approximately linearly with grid size) -------------------- Computer Platform: Pentium IV 1.7GHz Cluster # Processors: 16 Operating System: Red Hat Linux Compiler: Portland Group Fortran 77 Run Time CPU: 5 hours Run Time Wall-Clock: 5 hours Memory Requirements: 400 Mbytes per cpu = 6.4 Gbytes Miscellaneous: Based on 500 multigrid cycles for convergence CASE 1 SINGLE-POINT GRID CONVERGENCE STUDY (REQUIRED) --------------------------------------- ***NOTE**** REDISDUAL DROP IS MEASURED FROM 1st FINE GRID ITERATION TO LAST. SINCE CODE PERFORMS FULL MULTIGRID, FIRST FINE GRID ITERATION IS SOLUTION INTERPOLATED FROM COARSER GRID WHICH ALREADY HAS LOWER RESIDUAL THAN INITIALIZING FLOW FIELD WITH UNIFORM FLOW. RESIDUAL DROP FROM UNIFORM FLOW FIELD WILL BE 1 TO 2 ORDERS OF MAGNITUDE LARGER (i.e. 8.5E-05 WITH FMG BECONES 8.5E-07 WITHOUT FMG) WING/BODY GRID_SIZE MACH ALPHA CL_TOT (min, max) CD_TOT (min, max) CD_PR CD_SF CM_TOT (min, max) RESID_DROP*(SEE NOTE ABOVE) coarse 0.75 -0.044 0.500 (0.500, 0.500) 0.03117 (0.03117, 0.03117) 0.01804 0.01313 -0.1444 (-0.1444,-0.1444) 8.5e-05 (~8e-07 from uniform flow initialization) medium 0.75 -0.059 0.500 (0.500, 0.500) 0.02914 (0.02914, 0.02914) 0.01608 0.01306 -0.1485 (-0.1485,-0.1485) 4.5e-05 (from fmg) fine 0.75 -0.128 0.499 (0.499, 0.499) 0.02819 (0.02819, 0.02819) 0.01524 0.01294 -0.1518 (-0.1518,-0.1518) 8.8e-04 (from fmg) 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*(SEE NOTE ABOVE) coarse 0.75 0.462 0.500 (0.500, 0.500) 0.03637 (0.03637, 0.03637) 0.02078 0.01559 -0.1461 (-0.1461, -0.1461) 1.1e-04 (from fmg) medium 0.75 0.466 0.500 (0.500, 0.500) 0.03370 (0.03370, 0.03370) 0.01819 0.01552 -0.1477 (-0.1477, -0.1477) 1.8e-04 (from fmg) fine 0.75 0.381 0.500 (0.500, 0.500) 0.03278 (0.03278, 0.03278) 0.01737 0.01541 -0.1539 (-0.1539, -0.1539) 6.8e-04 (from fmg) 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 214.66 77.68 4.22 231.45 73.77 8.16 225.05 67.56 5.51 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 214.47 71.99 6.56 227.65 72.54 7.08 224.59 67.64 5.33 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 0.146 (0.146, 0.146) 0.02098 (0.02098, 0.02098) 0.00775 0.01323 0.02027 -0.1587 (-0.1587, -0.1587) 0.75 -2.0 0.266 (0.266, 0.266) 0.02256 (0.02256, 0.02256) 0.00935 0.01322 0.02019 -0.1558 (-0.1558, -0.1558) 0.75 -1.5 0.326 (0.326, 0.326) 0.02380 (0.02380, 0.02380) 0.01061 0.01319 0.02024 -0.1542 (-0.1542, -0.1542) 0.75 -1.0 0.386 (0.386, 0.386) 0.02533 (0.02533, 0.02533) 0.01218 0.01316 0.02034 -0.1525 (-0.1525, -0.1525) 0.75 0.0 0.507 (0.507, 0.507) 0.02942 (0.02942, 0.02942) 0.01637 0.01305 0.02081 -0.1482 (-0.1482, -0.1482) 0.75 1.0 0.632 (0.632, 0.632) 0.03568 (0.03568, 0.03568) 0.02287 0.01281 0.02230 -0.1411 (-0.1411, -0.1411) 0.75 1.5 0.691 (0.691, 0.691) 0.04047 (0.04047, 0.04047) 0.02785 0.01262 0.02447 -0.1362 (-0.1362, -0.1362) 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 ?.??? (?.???, ?.???) ?.????? (?.?????, ?.?????) ?.????? ?.????? ?.????? ?.???? (?.????, ?.????)*No converged solution 0.75 -2.0 0.211 (0.201, 0.224) 0.02793 (0.27760, 0.02847) 0.01221 0.01571 0.02644 -0.1742 (N/A , N/A )*Averaged(notfully converged) 0.75 -1.5 0.268 (0.267, 0.269) 0.02847 (0.02845, 0.02849) 0.01270 0.01577 0.02606 -0.1674 (N/A , N/A ) 0.75 -1.0 0.325 (0.325, 0.325) 0.02922 (0.02921, 0.02923) 0.01349 0.01573 0.02568 -0.1619 (N/A , N/A ) 0.75 0.0 0.443 (0.443, 0.443) 0.03174 (0.03174, 0.03174) 0.01616 0.01558 0.02516 -0.1524 (N/A , N/A ) 0.75 1.0 0.567 (0.567, 0.567) 0.03663 (0.03663, 0.03663) 0.02122 0.01540 0.02586 -0.1407 (N/A , N/A ) 0.75 1.5 0.629 (0.628, 0.629) 0.04041 (0.04037, 0.04041) 0.02518 0.01524 0.02715 -0.1336 (N/A , N/A ) UPPER SURFACE TRANSITION LOCATIONS (% CHORD) XROOT XKINK XE.844 XTIP *******FULLY TURBULENT RUNS**************** LOWER SURFACE TRANSITION LOCATION (% CHORD) XLO *******FULLY TURBULENT RUNS**************** ------------------------------------------------------------------------------------------------------------------------------------- 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 0.154 (0.154, 0.154) 0.01985 (0.01985, 0.01985) 0.00733 0.01252 0.01906 -0.1638 (-0.1638, -0.1638) 0.75 -2.0 0.276 (0.276, 0.276) 0.02161 (0.02161, 0.02161) 0.00910 0.01252 0.01906 -0.1611 (-0.1611, -0.1611) 0.75 -1.5 0.337 (0.337, 0.337) 0.02293 (0.02293, 0.02293) 0.01043 0.01250 0.01912 -0.1597 (-0.1597, -0.1597) 0.75 -1.0 0.398 (0.398, 0.398) 0.02454 (0.02454, 0.02454) 0.01207 0.01248 0.01923 -0.1583 (-0.1583, -0.1583) 0.75 0.0 0.522 (0.522, 0.522) 0.02880 (0.02880, 0.02880) 0.01641 0.01238 0.01967 -0.1546 (-0.1546, -0.1546) 0.75 1.0 0.649 (0.649, 0.649) 0.03537 (0.03537, 0.03537) 0.02319 0.01219 0.02126 -0.1482 (-0.1482, -0.1482) 0.75 1.5 0.711 (0.711, 0.711) 0.04041 (0.04041, 0.04041) 0.02840 0.01200 0.02347 -0.1440 (-0.1440, -0.1440) 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 ?.??? (?.???, ?.???) ?.????? (?.?????, ?.?????) ?.????? ?.????? ?.????? ?.???? (?.????, ?.????) (No converged solution) 0.75 -2.0 0.218 (0.217, 0.228) 0.02746 (0.02736, 0.02756) 0.01276 0.01481 ?.????? ?.???? (?.????, ?.????) 0.75 -1.5 0.281 (0.281, 0.284) 0.02737 (0.02737, 0.02753) 0.01253 0.01484 0.02472 -0.1736 (?.????, ?.????) Averagedsolution(notfully converged) 0.75 -1.0 0.338 (0.336, 0.338) 0.02830 (0.02818, 0.02830) 0.01348 0.01482 0.02447 -0.1685 (-0.1655, -0.1687) 0.75 0.0 0.456 (0.456, 0.456) 0.03110 (0.03108, 0.03110) 0.01638 0.01472 0.02413 -0.1587 (-0.1587, -0.1587) 0.75 1.0 0.584 (0.584, 0.584) 0.03626 (0.03626, 0.03626) 0.02165 0.01461 0.02483 -0.1476 (-0.1476, -0.1476) 0.75 1.5 0.648 (0.647, 0.648) 0.04028 (0.04017, 0.04028) 0.02583 0.01445 0.02621 -0.1408 (-0.1406, -0.1408) UPPER SURFACE TRANSITION LOCATIONS (% CHORD) XROOT XKINK XE.844 XTIP 5% 15% 15% 5% LOWER SURFACE TRANSITION LOCATION (% CHORD) XLO 25% 0% in vicinity of pylon on wing-body-nacelle-pylon geomtry 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 -0.172 0.500 (0.500, 0.500) 0.02795 (0.02795, 0.02795) 0.01555 0.01240 -0.1554 (-0.1554,-0.1554) TRIPPED 0.75 -0.059 0.500 (0.500, 0.500) 0.02914 (0.02914, 0.02914) 0.01608 0.01305 -0.1485 (-0.1485,-0.1485) 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 0.349 0.500 (0.500, 0.500) 0.03259 (0.03259, 0.03259) 0.01789 0.01469 -0.1554 (-0.1554,-0.1554) TRIPPED 0.75 0.466 0.500 (0.500, 0.500) 0.03370 (0.03370, 0.03370) 0.01819 0.01552 -0.1477 (-0.1477,-0.1477) 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 0.638 0.500 (0.500, 0.500) 0.02756 (0.02756, 0.02756) 0.01430 0.01326 -0.1248 (-0.1248, -0.1248) 0.60 0.393 0.500 (0.500, 0.500) 0.02745 (0.02745, 0.02745) 0.01452 0.01294 -0.1334 (-0.1334, -0.1334) 0.70 0.057 0.500 (0.500, 0.500) 0.02764 (0.02764, 0.02764) 0.01504 0.01259 -0.1461 (-0.1461, -0.1461) 0.72 -0.029 0.500 (0.500, 0.500) 0.02774 (0.02774, 0.02774) 0.01522 0.01252 -0.1497 (-0.1497, -0.1497) 0.74 -0.123 0.500 (0.500, 0.500) 0.02786 (0.02786, 0.02786) 0.01542 0.01244 -0.1533 (-0.1533, -0.1533) 0.75 -0.172 0.500 (0.500, 0.500) 0.02795 (0.02795, 0.02795) 0.01555 0.01240 -0.1554 (-0.1554, -0.1554) 0.76 -0.230 0.500 (0.500, 0.500) 0.02805 (0.02805, 0.02805) 0.01570 0.01236 -0.1580 (-0.1580, -0.1580) 0.77 -0.284 0.500 (0.500, 0.500) 0.02833 (0.02833, 0.02833) 0.01604 0.01229 -0.1609 (-0.1609, -0.1609) WING/BODY/NACELLE/PYLON MACH ALPHA CL_TOT (min, max) CD_TOT (min, max) CD_PR CD_SF CM_TOT (min, max) 0.50 1.042 0.500 (0.500, 0.500) 0.03152 (0.03152, 0.03152) 0.01563 0.01589 -0.1215 (-0.1215, -0.1215) 0.60 0.832 0.500 (0.500, 0.500) 0.03132 (0.03132, 0.03132) 0.01584 0.01547 -0.1314 (-0.1314, -0.1314) 0.70 0.549 0.500 (0.500, 0.500) 0.03174 (0.03174, 0.03174) 0.01673 0.01501 -0.1458 (-0.1458, -0.1458) 0.72 0.475 0.500 (0.500, 0.500) 0.03198 (0.03198, 0.03198) 0.01710 0.01488 -0.1496 (-0.1496, -0.1496) 0.74 0.394 0.500 (0.500, 0.500) 0.03235 (0.03235, 0.03235) 0.01759 0.01476 -0.1535 (-0.1535, -0.1535) 0.75 0.349 0.500 (0.500, 0.500) 0.03259 (0.03259, 0.03259) 0.01789 0.01469 -0.1554 (-0.1554, -0.1554) 0.76 0.297 0.500 (0.500, 0.500) 0.03286 (0.03286, 0.03286) 0.01823 0.01463 -0.1569 (-0.1569, -0.1569) 0.77 0.238 0.500 (0.500, 0.500) 0.03318 (0.03318, 0.03318) 0.01864 0.01453 -0.1597 (-0.1597, -0.1597) 0.80 0.086 0.498 (0.498, 0.498) 0.03637 (0.03637, 0.03637) 0.02220 0.01418 -0.1665 (-0.1665, -0.1665) 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)