DPW-III DLR-F6 CASE-1 Data Form
-------------------------------


Date:  [Due 28 APR 2006]


PARTICIPANT INFORMATION
-----------------------
               Name: Chad Winkler, Andy Dorgan, Mark Fisher, Mori Mani, S. P. Vanka* 
              Email: chad.m.winkler@boeing.com, mori.mani@boeing.com 
              Phone:  314-233-9437
            Address:  The Boeing Company, S306-4030, St. Louis, MO 63166
            Address:  
            Address: * University of Illinois at Urbana-Champaign, Urbana, IL 61801 
            Address:  
            Address:  
            Address:  


SOLVER INFORMATION
--------------------
        Method Name: BCFD 
    Basic Algorithm: Finite volume, cell-centered, multigrid 
   Turbulence Model: Spalart-Allmaras 
      Miscellaneous:  


GRID INFORMATION
--------------------
Grid-Generator Name: MADCAP, AFLR 
          Grid Type: Unstructured, mixed tet/prism 


COARSE GRID SIZE            WB       WBF
----------------------------------------
              Zones:        5         5 
        Field Nodes:  
        Field Cells:     1341396   1098053
     Boundary Nodes:  
     Boundary Faces:     131883    123124
   BL 1st-Cell Size:     0.0011   0.00105
 BL Max-Growth Rate:     1.1        1.1
           BL Cells:     2434294   2811072
      Miscellaneous:  cell size in mm


MEDIUM GRID SIZE            WB       WBF
----------------------------------------
              Zones:        14       14 
        Field Nodes:  
        Field Cells:  1980704      2487029
     Boundary Nodes:  
     Boundary Faces:  200851       184393
   BL 1st-Cell Size:  0.0008       0.0008
 BL Max-Growth Rate:  1.1	1.1
           BL Cells:  6676287  5275485
      Miscellaneous:  


FINE GRID SIZE              WB       WBF
----------------------------------------
              Zones:        33       33  
        Field Nodes: 
        Field Cells:  18088408   19570638
     Boundary Nodes:  
     Boundary Faces:  508735     495891
   BL 1st-Cell Size:  0.00054    0.00054
 BL Max-Growth Rate:  1.2         1.2
           BL Cells:  15749041   16186857
      Miscellaneous:  


SOLUTION INFORMATION (typical-fine grid)
--------------------
  Computer Platform: 64 bit Opteron
       # Processors: 33
   Operating System: Linux 
           Compiler: Intel 9
       Run Time CPU: 792 CPU hours
Run Time Wall-Clock: 24 hours 
Memory Requirements: 49.5 GB 
      Miscellaneous:  



CASE 1.A:  SINGLE-POINT GRID CONVERGENCE STUDY (REQUIRED, FULLY-TURBULENT)
--------------------------------------------------------------------------

WING/BODY

 GRID_SIZE      MACH     ALPHA    CL_TOT    CD_TOT     CD_PR     CD_SF    CM_TOT
 3775690        0.75     0.054     0.4993  0.03279   0.0201    0.01269  -0.13498
 8656991        0.75     0.137     0.4994  0.02959   0.01794   0.01165  -0.12641
 33837449       0.75     0.350     0.4998  0.02947   0.01762   0.01185  -0.12811

WING/BODY/FX2B-FAIRING

 GRID_SIZE      MACH     ALPHA    CL_TOT    CD_TOT     CD_PR     CD_SF    CM_TOT
 3909125        0.75     0.09625   0.49993 0.02954   0.01815   0.01139  -0.12827
 7762514        0.75     0.11715   0.50003 0.02923   0.01747   0.01176  -0.12552
 35757495       0.75     0.1194    0.50000 0.02841   0.01633   0.01208  -0.13335

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
    144.06    112.8   15.5     230.872 84.2754 -6.15689 234.658 72.2554 8.28049 

SEPARATION BUBBLE GEOMETRY - WING/BODY/FX2B-FAIRING - 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
    0.000    0.000   0.000     0.000    0.000    0.000    0.000    0.000    0.000

UPPER-SURFACE TRAILING-EDGE SEPARATION LOCATION

   STATION     Y (m)     Y/BO2   X/C-WB    X/C-WBF
        1.   0.08785     0.150    0.83029  0.99605
        2.   0.13987     0.239    0.99727  0.99728
        3.   0.19453     0.331    0.99161  0.98475
        4.   0.22156     0.377    0.99924  0.99924
        5.   0.24037     0.411    0.97303  0.98423
        6.   0.30090     0.514    0.97585  0.97228
        7.   0.37319     0.638    0.97797  0.97797
        8.   0.49602     0.847    0.99988  0.99982



CASE 1.B:  DRAG POLAR - MEDIUM GRID (REQUIRED, FULLY-TURBULENT)
---------------------------------------------------------------

WING/BODY

      MACH     ALPHA    CL_TOT    CD_TOT     CD_PR     CD_SF CD-CL2/PA    CM_TOT
      0.75      -3.0    0.1339206  0.02133 0.00946   0.01187 0.0207291 -0.14131
      0.75      -2.0    0.25374506 0.02261 0.01075   0.01186 0.0204526 -0.13928
      0.75      -1.0    0.373177   0.02523 0.01341   0.01182 0.0205639 -0.13579
      0.75      -0.5    0.4328414  0.02675 0.01498   0.01177 0.0204725 -0.13305
      0.75       0.0    0.48325    0.02897 0.0173    0.01167 0.0211452 -0.12681
      0.75       0.5    0.539316   0.03146 0.01987   0.01159 0.0217143 -0.12252
      0.75       1.0    0.5988     0.03461 0.02315   0.01146 0.0225959 -0.11699
      0.75       1.5    0.65378    0.03894 0.02765   0.01129 0.0246184 -0.10955

WING/BODY/FX2B-FAIRING

      MACH     ALPHA    CL_TOT    CD_TOT     CD_PR     CD_SF CD-CL2/PA    CM_TOT
      0.75      -3.0    0.12245881 0.020748 0.008798 0.01195 0.02024553 -0.13677
      0.75      -2.0    0.24486913 0.02209  0.01014  0.01195 0.02008093 -0.13542
      0.75      -1.0    0.36620453 0.02464  0.01274  0.0119  0.02014661 -0.13284
      0.75      -0.5    0.4265631  0.02643  0.01457  0.01186 0.02033332 -0.13023
      0.75       0.0    0.4866353  0.02852  0.01672  0.0118  0.02058523 -0.12657
      0.75       0.5    0.5475111  0.0311   0.01939  0.01171 0.02105586 -0.12249
      0.75       1.0    0.6102689  0.03458  0.02298  0.0116  0.02210130 -0.11724
      0.75       1.5    0.668145   0.03927  0.02782  0.01145 0.02431218 -0.11031



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)
                    Note: AR=9.5
* CM_TOT    (F10.4) Total Moment Coefficient.

* 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)

*    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     (F10.3) Wing semi-span fraction of station data.
* X/C-WB    (F10.3) Upper-surface trailing-edge separation location for wing/body geometry.
* X/C-WBF   (F10.3) Upper-surface trailing-edge separation location for wing/body/fairing geometry.

     NOTE:  Set X/C-WB* to 1.000 if no TE separation is detected in solution.

