Date: 5/07/01 (supplied grid w/ SA) PARTICIPANT INFORMATION ----------------------- Name: Kelly R. Laflin Email: klaflin@cessna.textron.com Phone: (316) 831-2247 Address: Cessna Aircraft Co. Address: 5701 E. Pawnee Address: Wichita, Ks 67218 Address: Address: Address: SOLVER INFORMATION -------------------- Method Name: CFL3D Basic Algorithm: Multi-Blocked, Structured, central difference, upwind Turbulence Model: Spalart-Allmaras Miscellaneous: CASE 1 PROVIDED GRID USED Mark one line with an X -------------------- Multi-block: X Overset: Unstructured node: 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: 5 (4+1) Operating System: Red Hat LINUX 6.2 Compiler: Compaq Fortran V1.0-920 Run Time CPU: ~20 Hours Run Time Wall-Clock: ~20 Hours Memory Requirements: .44 GB/node Miscellaneous: CASE 1 DATA ON PROVIDED GRID (REQUIRED) --------------------------------------- MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT 0.75 -0.296 0.5000 0.02977 0.01580 0.01397 -0.1623 CASE 2 DRAG POLAR DATA (REQUIRED) --------------------------------- MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT 0.75 -3.000 0.171 0.02137 0.00724 0.01412 -0.1691 0.75 -2.000 0.294 0.02336 0.00924 0.01411 -0.1684 0.75 -1.000 0.415 0.02662 0.01256 0.01405 -0.1658 0.75 0.000 0.536 0.03138 0.01746 0.01391 -0.1600 0.75 1.000 0.655 0.03918 0.02555 0.01362 -0.1500 0.75 2.000 0.740 0.05091 0.03770 0.01321 -0.1274 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: 5/07/01 (supplied grid w/ SST) PARTICIPANT INFORMATION ----------------------- Name: Kelly R. Laflin Email: klaflin@cessna.textron.com Phone: (316) 831-2247 Address: Cessna Aircraft Co. Address: 5701 E. Pawnee Address: Wichita, Ks 67218 Address: Address: Address: SOLVER INFORMATION -------------------- Method Name: CFL3D Basic Algorithm: Multi-Blocked, Structured, central difference, upwind Turbulence Model: Menter's SST Miscellaneous: CASE 1 PROVIDED GRID USED Mark one line with an X -------------------- Multi-block: X Overset: Unstructured node: 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: 5 (4+1) Operating System: Red Hat LINUX 6.2 Compiler: Compaq Fortran V1.0-920 Run Time CPU: ~20 Hours Run Time Wall-Clock: ~20 Hours Memory Requirements: .44 GB/node Miscellaneous: CASE 1 DATA ON PROVIDED GRID (REQUIRED) --------------------------------------- MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT 0.75 -0.270 0.5000 0.02791 0.01576 0.01215 -0.1596 CASE 2 DRAG POLAR DATA (REQUIRED) --------------------------------- MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT 0.75 -3.000 0.169 0.01960 0.00731 0.01229 -0.1667 0.75 -2.000 0.292 0.02150 0.00922 0.01228 -0.1664 0.75 -1.000 0.412 0.02469 0.01247 0.01223 -0.1638 0.75 0.000 0.533 0.02937 0.01726 0.01211 -0.1573 0.75 1.000 0.655 0.03729 0.02542 0.01187 -0.1496 0.75 2.000 0.735 0.04894 0.03745 0.01149 -0.1240 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: 5/07/01 (refined grid w/ SA) PARTICIPANT INFORMATION ----------------------- Name: Kelly R. Laflin Email: klaflin@cessna.textron.com Phone: (316) 831-2247 Address: Cessna Aircraft Co. Address: 5701 E. Pawnee Address: Wichita, Ks 67218 Address: Address: Address: SOLVER INFORMATION -------------------- Method Name: CFL3D Basic Algorithm: Multi-Blocked, Structured, biased-upwind/central-differencing for inviscid/viscous terms Turbulence Model: Spalart-Allmaras Miscellaneous: CASE 1 PROVIDED GRID USED Mark one line with an X -------------------- Multi-block: X Overset: Unstructured node: Unstructured cell: Could not use: GRID INFORMATION FOR CASES 2-4 Leave blank if you used the Case 1 provided grid -------------------- Grid-Generator Name: icem Grid Type: multi-blocked structured Zones: 49 blocks Field Nodes: 7,429,861 Field Cells: 7,042,048 Boundary Nodes: Boundary Faces: BL 1st-Cell Size: .0001 BL Max-Growth Rate: 1.20 BL Cells: Miscellaneous: SOLUTION INFORMATION -------------------- Computer Platform: Microway Beowulf w/ UP2000 Motherboards # Processors: 9 (8+1) Operating System: Red Hat LINUX 6.2 Compiler: Compaq Fortran V1.0-920 Run Time CPU: ~20 Hours Run Time Wall-Clock: ~20 Hours Memory Requirements: .73 GB/node Miscellaneous: CASE 1 DATA ON PROVIDED GRID (REQUIRED) --------------------------------------- MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT 0.75 -0.296 0.5000 0.02977 0.01580 0.01397 -0.1623 CASE 2 DRAG POLAR DATA (REQUIRED) --------------------------------- MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT 0.75 -3.000 0.167 0.01984 0.00631 0.01352 -0.1710 0.75 -2.000 0.288 0.02180 0.00829 0.01350 -0.1693 0.75 -1.000 0.408 0.02495 0.01151 0.01344 -0.1658 0.75 0.000 0.527 0.02956 0.01625 0.01331 -0.1589 0.75 1.000 0.649 0.03728 0.02423 0.01305 -0.1498 0.75 2.000 0.743 0.04881 0.03615 0.01266 -0.1311 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: 5/07/01 (refined grid w/ SST) PARTICIPANT INFORMATION ----------------------- Name: Kelly R. Laflin Email: klaflin@cessna.textron.com Phone: (316) 831-2247 Address: Cessna Aircraft Co. Address: 5701 E. Pawnee Address: Wichita, Ks 67218 Address: Address: Address: SOLVER INFORMATION -------------------- Method Name: CFL3D Basic Algorithm: Multi-Blocked, Structured, biased-upwind/central-differencing for inviscid/viscous terms Turbulence Model: Menter's k-omega SST Miscellaneous: CASE 1 PROVIDED GRID USED Mark one line with an X -------------------- Multi-block: X Overset: Unstructured node: Unstructured cell: Could not use: GRID INFORMATION FOR CASES 2-4 Leave blank if you used the Case 1 provided grid -------------------- Grid-Generator Name: icem Grid Type: multi-blocked structured Zones: 49 blocks Field Nodes: 7,429,861 Field Cells: 7,042,048 Boundary Nodes: Boundary Faces: BL 1st-Cell Size: .0001 BL Max-Growth Rate: 1.20 BL Cells: Miscellaneous: SOLUTION INFORMATION -------------------- Computer Platform: Microway Beowulf w/ UP2000 Motherboards # Processors: 9 (8+1) Operating System: Red Hat LINUX 6.2 Compiler: Compaq Fortran V1.0-920 Run Time CPU: ~20 Hours Run Time Wall-Clock: ~20 Hours Memory Requirements: .73 GB/node Miscellaneous: CASE 1 DATA ON PROVIDED GRID (REQUIRED) --------------------------------------- MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT 0.75 -0.270 0.5000 0.02791 0.01576 0.01215 -0.1596 CASE 2 DRAG POLAR DATA (REQUIRED) --------------------------------- MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT 0.75 -3.000 0.160 0.01944 0.00666 0.01278 -0.1663 0.75 -2.000 0.280 0.02128 0.00851 0.01276 -0.1643 0.75 -1.000 0.397 0.02425 0.01155 0.01270 -0.1600 0.75 0.000 0.513 0.02864 0.01606 0.01257 -0.1518 0.75 1.000 0.633 0.03608 0.02374 0.01234 -0.1423 0.75 2.000 0.723 0.04720 0.03520 0.01200 -0.1223 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.