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


Date: 28 APR 2006


PARTICIPANT INFORMATION
-----------------------
               Name:  Tony Sclafani
              Email:  tony.sclafani@boeing.com
              Phone:  714-896-1074
            Address:  The Boeing Company
            Address:  5301 Bolsa Avenue
            Address:  Huntington Beach, CA
            Address:  92647
            Address:  
            Address:  


SOLVER INFORMATION
--------------------
        Method Name:  OVERFLOW MPI v2.0z
    Basic Algorithm:  Roe Upwind
   Turbulence Model:  Spalart-Allmaras 1-equation
      Miscellaneous:  MPI - Message Passing Interface


GRID INFORMATION
--------------------
Grid-Generator Name:  Surface Grids - ZONI3G/SURGRD,  Volume Grids - HYPGEN/LEGRID/PEGASUS5
          Grid Type:  Structured Overset


COARSE GRID SIZE            WB       WBF
----------------------------------------
              Zones:        12        12
        Field Nodes:  
        Field Cells:  
     Boundary Nodes:  
     Boundary Faces:  
   BL 1st-Cell Size:   0.00055   0.00055
 BL Max-Growth Rate:      1.29      1.29
           BL Cells:  
      Miscellaneous:  


MEDIUM GRID SIZE            WB       WBF
----------------------------------------
              Zones:        12        12
        Field Nodes:  
        Field Cells:  
     Boundary Nodes:  
     Boundary Faces:  
   BL 1st-Cell Size:   0.00038   0.00038  
 BL Max-Growth Rate:      1.19      1.19
           BL Cells:  
      Miscellaneous:  


FINE GRID SIZE              WB       WBF
----------------------------------------
              Zones:        12        12
        Field Nodes:
        Field Cells:  
     Boundary Nodes:  
     Boundary Faces:  
   BL 1st-Cell Size:   0.00025   0.00025
 BL Max-Growth Rate:      1.12      1.12
           BL Cells:  
      Miscellaneous:  


SOLUTION INFORMATION (typical-fine grid)
--------------------
  Computer Platform:  Linux PC Cluster
       # Processors:  22
   Operating System:  
           Compiler:  
       Run Time CPU:  
Run Time Wall-Clock:  
Memory Requirements:  
      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
  2387918.      0.75     0.066	  0.5001   0.02797   0.01602   0.01196   -0.1410
  7985236.      0.75     0.160    0.5001   0.02763   0.01568   0.01195   -0.1407
 26892352.      0.75     0.219    0.4998   0.02761   0.01564   0.01197   -0.1400


WING/BODY/FX2B-FAIRING

 GRID_SIZE      MACH     ALPHA    CL_TOT    CD_TOT     CD_PR     CD_SF    CM_TOT
  2395170.      0.75    -0.001    0.5002   0.02730   0.01520    0.01210  -0.1420
  8020348.      0.75    -0.060    0.5001   0.02661   0.01444    0.01217  -0.1469
 26969192.      0.75    -0.077    0.5000   0.02625   0.01401    0.01224  -0.1486


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
     143.1     107.5     14.1      232.8      84.9      -6.7     239.1      72.5       9.3

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    0.718      1.000
        2.   0.13987     0.239    1.000      1.000
        3.   0.19453     0.331    1.000      1.000
        4.   0.22156     0.377    1.000      1.000
        5.   0.24037     0.411    1.000      1.000
        6.   0.30090     0.514    1.000      1.000
        7.   0.37319     0.638    1.000      1.000
        8.   0.49602     0.847    1.000      1.000 



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    0.1366   0.01881   0.00663   0.01218   0.01819   -0.1563
      0.75      -2.0    0.2529   0.02039   0.00823   0.01216   0.01825   -0.1515
      0.75      -1.0    0.3673   0.02305   0.01095   0.01209   0.01853   -0.1467
      0.75      -0.5    0.4243   0.02480   0.01276   0.01204   0.01877   -0.1443
      0.75       0.0    0.4817   0.02689   0.01491   0.01198   0.01911   -0.1417
      0.75       0.5    0.5390   0.02940   0.01752   0.01189   0.01967   -0.1384
      0.75       1.0    0.5964   0.03264   0.02087   0.01176   0.02072   -0.1344
      0.75       1.5    0.6505   0.03695   0.02536   0.01159   0.02277   -0.1301


WING/BODY/FX2B-FAIRING

      MACH     ALPHA    CL_TOT    CD_TOT     CD_PR     CD_SF CD-CL2/PA    CM_TOT
      0.75      -3.0    0.1396   0.01840   0.00610   0.01230   0.01775   -0.1563
      0.75      -2.0    0.2624   0.02000   0.00770   0.01230   0.01769   -0.1531
      0.75      -1.0    0.3848   0.02279   0.01053   0.01226   0.01783   -0.1502
      0.75      -0.5    0.4460   0.02466   0.01244   0.01222   0.01800   -0.1486
      0.75       0.0    0.5076   0.02691   0.01474   0.01217   0.01827   -0.1467
      0.75       0.5    0.5698   0.02968   0.01759   0.01208   0.01880   -0.1439
      0.75       1.0    0.6343   0.03335   0.02138   0.01197   0.01987   -0.1409
      0.75       1.5    0.6974   0.03844   0.02663   0.01182   0.02215   -0.1378


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.

