Date: 5/11/01 Revised to correct CD_SF interpolation error PARTICIPANT INFORMATION ----------------------- Name: David W. Levy Email: dlevy@cessna.textron.com Phone: (316) 831-2520 Address: Cessna Aircraft Co. Address: 5701 E. Pawnee Address: Wichita, Ks 67218 Address: Address: Address: SOLVER INFORMATION -------------------- Method Name: NSU3D Basic Algorithm: Unstructured, central difference, matrix dissipation Turbulence Model: Spalart-Allmaras Miscellaneous: Mixed-element, nodal CASE 1 PROVIDED GRID USED Mark one line with an X -------------------- Multi-block: Overset: Unstructured node: X Unstructured cell: Could not use: GRID INFORMATION FOR CASES 2-4 Leave blank if you used the Case 1 provided grid -------------------- Grid-Generator Name: vgrid Grid Type: Unstructured, nodal Zones: N/A Field Nodes: 3,018,643 Field Cells: 10,266,218 Boundary Nodes: 73,477 (No-Slip, Approx) Boundary Faces: 146,954 (No-Slip) BL 1st-Cell Size: .001 BL Max-Growth Rate: ~1.33 (1.20 at surface) BL Cells: 3,728,456 (Prisms) Miscellaneous: Total Boundary nodes/faces = 84173/168342 SOLUTION INFORMATION -------------------- Computer Platform: Microway Beowulf w/ UP2000 Motherboards # Processors: 8 Operating System: Red Hat LINUX 6.2 Compiler: Compaq Fortran V1.0-920 Run Time CPU: ~8 Hours Run Time Wall-Clock: ~8 Hours Memory Requirements: 4.2 GB total, 525 MB/node Miscellaneous: CASE 1 DATA ON PROVIDED GRID (REQUIRED) --------------------------------------- MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT 0.75 -0.248 0.4995 0.02899 0.01662 0.01238 -0.1540 CASE 2 DRAG POLAR DATA (REQUIRED) --------------------------------- MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT 0.75 -3.000 0.181 0.02085 0.00834 0.01251 -0.1702 0.75 -2.000 0.305 0.02279 0.01032 0.01247 -0.1693 0.75 -1.000 0.428 0.02603 0.01364 0.01239 -0.1670 0.75 0.000 0.553 0.03086 0.01861 0.01225 -0.1617 0.75 1.000 0.678 0.03911 0.02718 0.01192 -0.1525 0.75 2.000 0.774 0.05277 0.04128 0.01149 -0.1362 CASE 3 DRAG RISE DATA (OPTIONAL) -------------------------------- MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT 0.50 0.320 0.500 0.02769 0.01468 0.01300 -0.1338 0.60 0.097 0.500 0.02768 0.01488 0.01279 -0.1431 0.70 -0.211 0.500 0.02819 0.01569 0.01250 -0.1553 0.75 -0.424 0.500 0.02881 0.01650 0.01231 -0.1639 0.76 -0.481 0.500 0.02896 0.01669 0.01227 -0.1664 0.77 -0.545 0.500 0.02920 0.01699 0.01222 -0.1697 0.78 -0.590 0.500 0.02986 0.01771 0.01215 -0.1730 0.80 -0.581 0.500 0.03296 0.02089 0.01194 -0.1768 CASE 4 ADDITIONAL DRAG RISE DATA (OPTIONAL) ------------------------------------------- MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT 0.50 -1.717 0.300 0.02199 0.00880 0.01315 -0.1477 0.60 -1.827 0.300 0.02200 0.00907 0.01292 -0.1545 0.70 -1.957 0.300 0.02231 0.00967 0.01265 -0.1633 0.75 -2.040 0.300 0.02271 0.01024 0.01247 -0.1693 0.76 -2.056 0.300 0.02286 0.01043 0.01243 -0.1708 0.77 -2.078 0.300 0.02301 0.01062 0.01239 -0.1725 0.78 -2.098 0.300 0.02324 0.01090 0.01233 -0.1745 0.80 -2.097 0.300 0.02441 0.01222 0.01219 -0.1782 MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT 0.50 -0.704 0.400 0.02441 0.01129 0.01309 -0.1411 0.60 -0.865 0.400 0.02442 0.01155 0.01286 -0.1492 0.70 -1.087 0.400 0.02477 0.01219 0.01260 -0.1600 0.75 -1.228 0.400 0.02529 0.01288 0.01241 -0.1675 0.76 -1.262 0.400 0.02545 0.01308 0.01237 -0.1695 0.77 -1.302 0.400 0.02565 0.01334 0.01233 -0.1717 0.78 -1.331 0.400 0.02605 0.01378 0.01226 -0.1741 0.80 -1.356 0.400 0.02758 0.01548 0.01210 -0.1787 MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT 0.50 1.351 0.600 0.03183 0.01893 0.01291 -0.1256 0.60 1.071 0.600 0.03186 0.01917 0.01268 -0.1358 0.70 0.691 0.600 0.03310 0.02078 0.01232 -0.1473 0.75 0.376 0.600 0.03396 0.02183 0.01213 -0.1582 0.76 0.309 0.600 0.03431 0.02223 0.01208 -0.1613 0.77 0.233 0.600 0.03473 0.02270 0.01203 -0.1652 0.78 0.176 0.600 0.03569 0.02371 0.01196 -0.1693 0.80 0.341 0.600 0.04258 0.03071 0.01167 -0.1677 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. * CM_TOT (F10.4) Total Moment Coefficient. Date: 5/15/01 Case 2 on Standard Grid PARTICIPANT INFORMATION ----------------------- Name: David W. Levy Email: dlevy@cessna.textron.com Phone: (316) 831-2520 Address: Cessna Aircraft Co. Address: 5701 E. Pawnee Address: Wichita, Ks 67218 Address: Address: Address: SOLVER INFORMATION -------------------- Method Name: NSU3D Basic Algorithm: Unstructured, central difference, matrix dissipation Turbulence Model: Spalart-Allmaras Miscellaneous: Mixed-element, nodal CASE 1 PROVIDED GRID USED Mark one line with an X -------------------- Multi-block: Overset: Unstructured node: X Unstructured cell: Could not use: GRID INFORMATION FOR CASES 2-4 Leave blank if you used the Case 1 provided grid -------------------- Grid-Generator Name: Grid Type: Zones: Field Nodes: Field Cells: Boundary Nodes: Boundary Faces: BL 1st-Cell Size: BL Max-Growth Rate: BL Cells: Miscellaneous: SOLUTION INFORMATION -------------------- Computer Platform: Microway Beowulf w/ UP2000 Motherboards # Processors: 4 Operating System: Red Hat LINUX 6.2 Compiler: Compaq Fortran V1.0-920 Run Time CPU: ~8 Hours Run Time Wall-Clock: ~8 Hours Memory Requirements: 2.24 GB total, 560 MB/node Miscellaneous: CASE 1 DATA ON PROVIDED GRID (REQUIRED) --------------------------------------- MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT 0.75 -0.248 0.4995 0.02899 0.01662 0.01238 -0.1540 CASE 2 DRAG POLAR DATA (REQUIRED) --------------------------------- MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT 0.75 -3.000 0.162 0.02108 0.00853 0.01255 -0.1632 0.75 -2.000 0.285 0.02288 0.01035 0.01252 -0.1618 0.75 -1.000 0.407 0.02593 0.01347 0.01246 -0.1588 0.75 0.000 0.531 0.03050 0.01817 0.01233 -0.1532 0.75 1.000 0.655 0.03831 0.02627 0.01204 -0.1438 0.75 2.000 0.740 0.05147 0.03989 0.01158 -0.1231