Date: April, 2001 PARTICIPANT INFORMATION ----------------------- Name: Robert Narducci Email: robert.p.narducci@boeing.com Phone: (610) 591-4793 Address: The Boeing Company - Rotorcraft Division Address: P.O. Box 16858, MS P32-74 Address: Philadelphia, PA 19142-0858 Address: Address: Address: SOLVER INFORMATION -------------------- Method Name: CFL3Dv6 Basic Algorithm: Structured, Multiblock, Upwind Scheme Turbulence Model: Menter's k-W Miscellaneous: 3 Level Multigrid 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: 8 Node Origin 2000 # Processors: 3 Operating System: IRIX64 6.5 Compiler: SGI f90 Run Time CPU: N/A Run Time Wall-Clock: Memory Requirements: 632.7 Mbytes double precision Miscellaneous: CASE 1 DATA ON PROVIDED GRID (REQUIRED) --------------------------------------- MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT 0.75 -0.241 0.499 0.02787 0.01572 0.01215 -0.1577 CASE 2 DRAG POLAR DATA (REQUIRED) --------------------------------- MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT 0.75 -3.0 0.169 0.01953 0.00731 0.01230 -0.1687 0.75 -2.0 0.290 0.02145 0.00917 0.01228 -0.1653 0.75 -1.0 0.409 0.02457 0.01234 0.01223 -0.1624 0.75 0.0 0.529 0.02920 0.01709 0.01211 -0.1563 0.75 1.0 0.651 0.03698 0.02513 0.01187 -0.1475 0.75 2.0 0.735 0.04896 0.03747 0.01150 -0.1241 0.75 3.0 0.741 0.06372 0.05273 0.01099 -0.0812 CASE 3 DRAG RISE DATA (OPTIONAL) -------------------------------- MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT 0.75 -0.241 0.499 0.02787 0.01572 0.01215 -0.1577 0.80 -0.245 0.500 0.03163 0.01987 0.01176 -0.1606 0.85 1.344 0.500 0.05861 0.04771 0.01089 -0.1146 0.90 2.894 0.499 0.09773 0.08725 0.01048 -0.0668 0.95 2.748 0.500 0.13235 0.12120 0.01116 -0.1185 CASE 4 ADDITIONAL DRAG RISE DATA (OPTIONAL) ------------------------------------------- MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT 0.50 ?.??? 0.400 ?.????? ?.????? ?.????? ?.???? 0.60 ?.??? 0.400 ?.????? ?.????? ?.????? ?.???? 0.70 ?.??? 0.400 ?.????? ?.????? ?.????? ?.???? 0.75 ?.??? 0.400 ?.????? ?.????? ?.????? ?.???? 0.76 ?.??? 0.400 ?.????? ?.????? ?.????? ?.???? 0.77 ?.??? 0.400 ?.????? ?.????? ?.????? ?.???? 0.78 ?.??? 0.400 ?.????? ?.????? ?.????? ?.???? 0.80 ?.??? 0.400 ?.????? ?.????? ?.????? ?.???? MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT 0.50 ?.??? 0.600 ?.????? ?.????? ?.????? ?.???? 0.60 ?.??? 0.600 ?.????? ?.????? ?.????? ?.???? 0.70 ?.??? 0.600 ?.????? ?.????? ?.????? ?.???? 0.75 ?.??? 0.600 ?.????? ?.????? ?.????? ?.???? 0.76 ?.??? 0.600 ?.????? ?.????? ?.????? ?.???? 0.77 ?.??? 0.600 ?.????? ?.????? ?.????? ?.???? 0.78 ?.??? 0.600 ?.????? ?.????? ?.????? ?.???? 0.80 ?.??? 0.600 ?.????? ?.????? ?.????? ?.???? 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.