DPW-IV Common Research Model (CRM) Data Form (Case 1, Case 2, and Case 3) (version 3) ------------------------------------------------------------------------- Date: [Due 26 MAY 2009] PARTICIPANT INFORMATION ----------------------- Name: Email: Phone: Address: Address: Address: Address: Address: Address: SOLVER INFORMATION -------------------- Method Name: Basic Algorithm: Turbulence Model: Miscellaneous: GRID INFORMATION -------------------- Grid-Generator Name: Grid Type: MEDIUM GRID SIZE CRM WING/BODY/NO TAIL --------------------------------------------------- Zones: Field Nodes: Field Cells: Boundary Nodes: Boundary Faces: BL 1st-Cell Size: BL Max-Growth Rate: BL Cells: Miscellaneous: COARSE GRID SIZE CRM WING/BODY/TAIL (iH = 0) --------------------------------------------------- Zones: Field Nodes: Field Cells: Boundary Nodes: Boundary Faces: BL 1st-Cell Size: BL Max-Growth Rate: BL Cells: Miscellaneous: MEDIUM GRID SIZE CRM WING/BODY/TAIL (iH = 0) --------------------------------------------------- Zones: Field Nodes: Field Cells: Boundary Nodes: Boundary Faces: BL 1st-Cell Size: BL Max-Growth Rate: BL Cells: Miscellaneous: FINE GRID SIZE CRM WING/BODY/TAIL (iH = 0) --------------------------------------------------- Zones: Field Nodes: Field Cells: Boundary Nodes: Boundary Faces: BL 1st-Cell Size: BL Max-Growth Rate: BL Cells: Miscellaneous: EXTRA FINE GRID SIZE CRM WING/BODY/TAIL (iH = 0) --------------------------------------------------- Zones: Field Nodes: Field Cells: Boundary Nodes: Boundary Faces: BL 1st-Cell Size: BL Max-Growth Rate: BL Cells: Miscellaneous: SOLUTION INFORMATION (typical-fine grid) -------------------- Computer Platform: # Processors: Operating System: Compiler: Run Time CPU: Run Time Wall-Clock: Memory Requirements: Miscellaneous: -------------------------------------------------------------------------- CASE 1.1: SINGLE-POINT GRID CONVERGENCE STUDY (REQUIRED, FULLY-TURBULENT) -------------------------------------------------------------------------- WING/BODY/TAIL (iH = 0) +----------------------------------- OPTIONAL -----------------------------------+ GRID_SIZE MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CM_TOT CL_WING CD_WING CM_WING CL_TAIL CD_TAIL CM_TAIL CL_FUS CD_FUS CM_FUS ????????? 0.85 ?.??? 0.50?? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ????????? 0.85 ?.??? 0.50?? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ????????? 0.85 ?.??? 0.50?? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ????????? 0.85 ?.??? 0.50?? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? WING-FUSELAGE SEPARATION BUBBLE GEOMETRY - WING/BODY/TAIL (iH = 0) GRID_SIZE FS_BUB BL_BUB WL_BUB FS_EYE_W BL_EYE_W WL_EYE_W FS_EYE_B BL_EYE_B WL_EYE_B ????????? ????.??? ???.??? ???.??? ????.??? ???.??? ???.??? ????.??? ???.??? ???.??? ????????? ????.??? ???.??? ???.??? ????.??? ???.??? ???.??? ????.??? ???.??? ???.??? ????????? ????.??? ???.??? ???.??? ????.??? ???.??? ???.??? ????.??? ???.??? ???.??? ????????? ????.??? ???.??? ???.??? ????.??? ???.??? ???.??? ????.??? ???.??? ???.??? WING UPPER-SURFACE TRAILING-EDGE SEPARATION LOCATION - WING/BODY/TAIL (iH = 0) Note: MEDIUM & FINE GRIDS ARE REQUIRED; COARSE & EXTRAFINE GRIDS ARE OPTIONAL STATION Y (in) Y/BO2 X_COARSE X_MEDIUM X_FINE X_EXTRAFINE X_LE CHORD 1. 121.459 0.1050 ????.??? ????.??? ????.??? ????.??? 993.728 466.466 CFD-ONLY 2. 133.026 0.1150 ????.??? ????.??? ????.??? ????.??? 1002.168 459.571 CFD-ONLY 3. 144.594 0.1250 ????.??? ????.??? ????.??? ????.??? 1010.656 452.687 CFD-ONLY 4. 151.074 0.1306 ????.??? ????.??? ????.??? ????.??? 1015.435 448.836 EXPERIMENTAL 5. 232.444 0.2009 ????.??? ????.??? ????.??? ????.??? 1076.873 400.743 EXPERIMENTAL 6. 327.074 0.2828 ????.??? ????.??? ????.??? ????.??? 1148.974 344.991 EXPERIMENTAL 7. 396.765 0.3430 ????.??? ????.??? ????.??? ????.??? 1202.038 304.101 CFD-ONLY 8. 427.998 0.3700 ????.??? ????.??? ????.??? ????.??? 1225.822 285.806 CFD-ONLY 9. 459.370 0.3971 ????.??? ????.??? ????.??? ????.??? 1249.711 278.111 EXPERIMENTAL 10. 581.148 0.5024 ????.??? ????.??? ????.??? ????.??? 1342.440 248.312 EXPERIMENTAL 11. 697.333 0.6028 ????.??? ????.??? ????.??? ????.??? 1430.914 219.904 EXPERIMENTAL 12. 840.704 0.7268 ????.??? ????.??? ????.??? ????.??? 1540.091 184.844 EXPERIMENTAL 13. 978.148 0.8456 ????.??? ????.??? ????.??? ????.??? 1644.738 151.235 EXPERIMENTAL 14. 1098.926 0.9500 ????.??? ????.??? ????.??? ????.??? 1736.708 121.735 EXPERIMENTAL 15. 1122.048 0.9700 ????.??? ????.??? ????.??? ????.??? 1754.313 116.095 CFD-ONLY 16. 1145.183 0.9900 ????.??? ????.??? ????.??? ????.??? 1771.927 110.452 CFD-ONLY HORIZONTAL TAIL UPPER-SURFACE TRAILING-EDGE SEPARATION LOCATION - WING/BODY/TAIL (iH = 0) Note: MEDIUM & FINE GRIDS ARE REQUIRED; COARSE & EXTRAFINE GRIDS ARE OPTIONAL Note: CUTLEN(X) IS FOR REFERENCE AND IS THE DIFFERENCE BETWEEN (X_TE) - (X_LE) Horizontal Tail Constant Y Cuts STATION Y (in) Y/bo2 X_COARSE X_MEDIUM X_FINE X_EXTRAFINE X_LE CHORD 1. 75.600 0.1800 ????.??? ????.??? ????.??? ????.??? 2243.650 224.363 CFD-ONLY 2. 126.000 0.3000 ????.??? ????.??? ????.??? ????.??? 2286.582 204.525 CFD-ONLY 3. 210.000 0.5000 ????.??? ????.??? ????.??? ????.??? 2358.134 171.467 CFD-ONLY 4. 294.000 0.7000 ????.??? ????.??? ????.??? ????.??? 2429.687 138.421 CFD-ONLY 5. 378.000 0.9000 ????.??? ????.??? ????.??? ????.??? 2501.239 105.398 CFD-ONLY 6. 399.000 0.9500 ????.??? ????.??? ????.??? ????.??? 2519.128 97.148 CFD-ONLY 7. 415.800 0.9900 ????.??? ????.??? ????.??? ????.??? 2533.438 90.551 CFD-ONLY Horizontal Tail Side-of-Body Cuts SOB CUT X_COARSE Y_COARSE X_MEDIUM Y_MEDIUM X_FINE Y_FINE X_EXTRAFINE Y_EXTRAFINE X_LE Y_LE CUTLEN(X) CUT EQUATION 8. ????.??? ???.??? ????.??? ???.??? ????.??? ???.??? ????.??? ???.??? 2242.759 74.554 207.851 0.1736X + 0.9848Y + 0.0Z = 462.873 CFD-ONLY 9. ????.??? ???.??? ????.??? ???.??? ????.??? ???.??? ????.??? ???.??? 2250.906 84.118 204.374 0.1736X + 0.9848Y + 0.0Z = 473.706 CFD-ONLY 10. ????.??? ???.??? ????.??? ???.??? ????.??? ???.??? ????.??? ???.??? 2259.052 93.681 200.896 0.1736X + 0.9848Y + 0.0Z = 484.539 CFD-ONLY ------------------------------------------------------------------------------- CASE 1.2: DOWNWASH STUDY DRAG POLARS - MEDIUM GRID (REQUIRED, FULLY-TURBULENT) ------------------------------------------------------------------------------- WING/BODY/NO TAIL +----------------------------------- OPTIONAL -----------------------------------+ MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CD-CL2/PA CM_TOT CL_WING CD_WING CM_WING CL_TAIL CD_TAIL CM_TAIL CL_FUS CD_FUS CM_FUS 0.85 0.000 ?.???? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? 0.0000 0.00000 0.0000 ?.???? ?.????? ?.???? 0.85 1.000 ?.???? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? 0.0000 0.00000 0.0000 ?.???? ?.????? ?.???? 0.85 1.500 ?.???? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? 0.0000 0.00000 0.0000 ?.???? ?.????? ?.???? 0.85 2.000 ?.???? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? 0.0000 0.00000 0.0000 ?.???? ?.????? ?.???? 0.85 2.500 ?.???? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? 0.0000 0.00000 0.0000 ?.???? ?.????? ?.???? 0.85 3.000 ?.???? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? 0.0000 0.00000 0.0000 ?.???? ?.????? ?.???? 0.85 4.000 ?.???? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? 0.0000 0.00000 0.0000 ?.???? ?.????? ?.???? WING/BODY/TAIL (iH = -2 degrees) +----------------------------------- OPTIONAL -----------------------------------+ MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CD-CL2/PA CM_TOT CL_WING CD_WING CM_WING CL_TAIL CD_TAIL CM_TAIL CL_FUS CD_FUS CM_FUS 0.85 0.000 ?.???? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.85 1.000 ?.???? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.85 1.500 ?.???? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.85 2.000 ?.???? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.85 2.500 ?.???? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.85 3.000 ?.???? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.85 4.000 ?.???? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? WING/BODY/TAIL (iH = 0 degrees) +----------------------------------- OPTIONAL -----------------------------------+ MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CD-CL2/PA CM_TOT CL_WING CD_WING CM_WING CL_TAIL CD_TAIL CM_TAIL CL_FUS CD_FUS CM_FUS 0.85 0.000 ?.???? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.85 1.000 ?.???? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.85 1.500 ?.???? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.85 2.000 ?.???? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.85 2.500 ?.???? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.85 3.000 ?.???? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.85 4.000 ?.???? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? WING/BODY/TAIL (iH = +2 degrees) +----------------------------------- OPTIONAL -----------------------------------+ MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CD-CL2/PA CM_TOT CL_WING CD_WING CM_WING CL_TAIL CD_TAIL CM_TAIL CL_FUS CD_FUS CM_FUS 0.85 0.000 ?.???? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.85 1.000 ?.???? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.85 1.500 ?.???? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.85 2.000 ?.???? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.85 2.500 ?.???? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.85 3.000 ?.???? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.85 4.000 ?.???? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? TRIMMED DRAG POLAR => Interpolate iH at fixed CL to calculate CM_TOT = 0. 1) Interpolate CM_TOT and CD_TOT for each of the iH curves to the common CL values (CL = 0.2, 0.3, 0.4, 0.5, 0.6, 0.7) 2) Compute the iH for trim (CM_TOT=0) for each common CL based on the interpolated CM_TOT 3) Interpolate on the trimmed CD_TOT curves to the trimmed iH value +----------------------------------- OPTIONAL -----------------------------------+ MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CD-CL2/PA CM_TOT CL_WING CD_WING CM_WING CL_TAIL CD_TAIL CM_TAIL CL_FUS CD_FUS CM_FUS iH 0.85 ?.??? 0.2000 ?.????? ?.????? ?.????? ?.????? 0.0000 ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.??? 0.85 ?.??? 0.3000 ?.????? ?.????? ?.????? ?.????? 0.0000 ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.??? 0.85 ?.??? 0.4000 ?.????? ?.????? ?.????? ?.????? 0.0000 ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.??? 0.85 ?.??? 0.5000 ?.????? ?.????? ?.????? ?.????? 0.0000 ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.??? 0.85 ?.??? 0.6000 ?.????? ?.????? ?.????? ?.????? 0.0000 ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.??? 0.85 ?.??? 0.7000 ?.????? ?.????? ?.????? ?.????? 0.0000 ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.??? DELTA DRAG POLAR => TAIL OFF MINUS TRIMMED TAIL ON (= WING/BODY/NO TAIL - TRIMMED DRAG POLAR) 1) Interpolate tail off data to fixed CL values. 2) Subract trimmed data (above) from interpolated tail off data. +----------------------------------- OPTIONAL -----------------------------------+ DELTA DELTA DELTA DELTA DELTA DELTA DELTA DELTA DELTA DELTA DELTA DELTA DELTA DELTA MACH CL_TOT CD_TOT CD_PR CD_SF CD-CL2/PA CM_TOT CL_WING CD_WING CM_WING CL_TAIL CD_TAIL CM_TAIL CL_FUS CD_FUS CM_FUS 0.85 0.2000 ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.85 0.3000 ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.85 0.4000 ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.85 0.5000 ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.85 0.6000 ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.85 0.7000 ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? -------------------------------------------------------------------------- CASE 2 : MACH SWEEP STUDY (OPTIONAL, MEDIUM GRID, FULLY-TURBULENT) -------------------------------------------------------------------------- WING/BODY/TAIL (iH = 0) CL = 0.400 +----------------------------------- OPTIONAL -----------------------------------+ MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CD-CL2/PA CM_TOT CL_WING CD_WING CM_WING CL_TAIL CD_TAIL CM_TAIL CL_FUS CD_FUS CM_FUS 0.70 ?.??? 0.40?? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.75 ?.??? 0.40?? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.80 ?.??? 0.40?? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.83 ?.??? 0.40?? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.85 ?.??? 0.40?? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.86 ?.??? 0.40?? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.87 ?.??? 0.40?? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? WING/BODY/TAIL (iH = 0) CL = 0.450 +----------------------------------- OPTIONAL -----------------------------------+ MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CD-CL2/PA CM_TOT CL_WING CD_WING CM_WING CL_TAIL CD_TAIL CM_TAIL CL_FUS CD_FUS CM_FUS 0.70 ?.??? 0.45?? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.75 ?.??? 0.45?? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.80 ?.??? 0.45?? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.83 ?.??? 0.45?? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.85 ?.??? 0.45?? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.86 ?.??? 0.45?? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.87 ?.??? 0.45?? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? WING/BODY/TAIL (iH = 0) CL = 0.500 +----------------------------------- OPTIONAL -----------------------------------+ MACH ALPHA CL_TOT CD_TOT CD_PR CD_SF CD-CL2/PA CM_TOT CL_WING CD_WING CM_WING CL_TAIL CD_TAIL CM_TAIL CL_FUS CD_FUS CM_FUS 0.70 ?.??? 0.50?? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.75 ?.??? 0.50?? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.80 ?.??? 0.50?? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.83 ?.??? 0.50?? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.85 ?.??? 0.50?? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.86 ?.??? 0.50?? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 0.87 ?.??? 0.50?? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? -------------------------------------------------------------------------- CASE 3 : REYNOLDS NUMBER STUDY (OPTIONAL, MEDIUM GRID, FULLY-TURBULENT) -------------------------------------------------------------------------- WING/BODY/TAIL (iH = 0) CL = 0.500 MACH = 0.85 +----------------------------------- OPTIONAL -----------------------------------+ REYNOLDS ALPHA CL_TOT CD_TOT CD_PR CD_SF CD-CL2/PA CM_TOT CL_WING CD_WING CM_WING CL_TAIL CD_TAIL CM_TAIL CL_FUS CD_FUS CM_FUS 5.0??E6 ?.??? 0.50?? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? 20.0??E6 ?.??? 0.50?? ?.????? ?.????? ?.????? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? ?.???? ?.????? ?.???? NOTES: ------ * Information lines are 168 characters long. * Information blocks allow free-form miscellaneous information. * GRID_SIZE (F10.0) Number of grid nodes or cells * MACH (F 7.2) Mach Number. * ALPHA (F 8.3) Angle of Attack in Degrees. * REYNOLDS (E 8.6) Reynolds Number. * CL_TOT (F 9.4) 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) Note: AR=9.0 * CM_TOT (F10.4) Total Moment Coefficient. * CL_WING (F 9.4) Wing Component Lift Coefficient * CD_WING (F10.5) Wing Component Drag Coefficient * CM_WING (F 9.4) Wing Component Moment Coefficient * CL_TAIL (F 9.4) Tail Component Lift Coefficient * CD_TAIL (F10.5) Tail Component Drag Coefficient * CM_TAIL (F 9.4) Tail Component Moment Coefficient * CL_FUS (F 9.4) Fuselage Component Lift Coefficient * CD_FUS (F10.5) Fuselage Component Drag Coefficient * CM_FUS (F 9.4) Fuselage Component Moment Coefficient * iH (F 8.3) Tail setting for trimmed conditions * FS_BUB (F10.3) Fuselage station at the leading edge of the wing root separation bubble (in) (measured on the wing) * BL_BUB (F10.3) Butt line at the outboard edge of the wing root separation bubble (in) (measured on the wing) * WL_BUB (F10.3) Water line at the top edge of the wing root separation bubble (in) (measured on the fuselage) * FS_EYE_W (F10.3) Fuselage station at the center of the wing root separation bubble (in) (measured on the wing) * BL_EYE_W (F10.3) Butt line at the center of the wing root separation bubble (in) (measured on the wing) * WL_EYE_W (F10.3) Water line at the center of the wing root separation bubble (in) (measured on the wing) * FS_EYE_B (F10.3) Fuselage station at the center of the wing root separation bubble (in) (measured on the fuselage) * BL_EYE_B (F10.3) Butt line at the center of the wing root separation bubble (in) (measured on the fuselage) * WL_EYE_B (F10.3) Water line at the center of the wing root separation bubble (in) (measured on the fuselage) * NOTE: Set side-of-body-separation-bubble-data to 0.000 if no bubble is computed. * STATION (F10.0) Wing station number [Consistent with Cp-data stations]. * Y/BO2 (F10.4) Wing semi-span fraction of station data. * Y/bo2 (F10.4) Tail semi-span fraction of station data. * BO2 Wing Semispan (1156.75 in) * bo2 Tail Semispan ( 420.00 in) * X_* (F10.3) X coordinate for upper-surface trailing-edge separation location * Y_* (F10.3) Y coordinate for upper-surface trailing-edge separation location * X_LE (F10.3) X coordinate at leading edge of cut * Y_LE (F10.3) Y coordinate at leading edge of cut * X_TE (F10.3) X coordinate at trailing edge of cut * CHORD (F10.3) Local chord - distance from cut leading edge to trailing edge * CUTLEN(X) (F10.3) Difference between (X_TE) - (X_LE) * NOTE: Set X_* to 0.0 if no TE separation is detected in solution. * NOTE: Set Y_* to 0.0 if no TE separation is detected in solution.