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


Date:  24 MAY 2006


PARTICIPANT INFORMATION
-----------------------
               Name: Matt Milne 
              Email: memilne@qinetiq.com 
              Phone: +44 1252 39 5339 
            Address: X80 Bldg, Rm 118 
            Address: QinetiQ
            Address: Ively Road 
            Address: Farnborough 
            Address: Hampshire, GU14 0LX 
            Address: United Kingdom 


SOLVER INFORMATION
--------------------
        Method Name: STAR-CCM+ v1.08.018
    Basic Algorithm: Coupled-Implicit Algebraic Multigrid Solver
   Turbulence Model: Wilcox k-omega
      Miscellaneous:  


GRID INFORMATION
--------------------
Grid-Generator Name: SAUNA
          Grid Type: block-structured


COARSE GRID SIZE            WB       WBF
----------------------------------------
              Zones:  688 blocks 688 blocks 
        Field Nodes:   2551989   2551989
        Field Cells:   2487296   2487296
     Boundary Nodes:     31461     31461 (i.e. no. points on model surface (wing-body/wing-body-fairing) but excluding farfield boundaries)
     Boundary Faces:     31264     31264 (i.e. no. faces on model surface (wing-body/wing-body-fairing) but excluding farfield boundaries)
   BL 1st-Cell Size:   1.0E-06   1.0E-06
 BL Max-Growth Rate: TANH distribution modified with first 4 cells linearly spaced
           BL Cells: 41 cells normal to wall in both meshes
      Miscellaneous:  


MEDIUM GRID SIZE            WB       WBF
----------------------------------------
              Zones:  688 blocks 688 blocks 
        Field Nodes:   4731073   4731073
        Field Cells:   4633600   4633600
     Boundary Nodes:     50161     50161 (i.e. no. points on model surface (wing-body/wing-body-fairing) but excluding farfield boundaries)
     Boundary Faces:     49920     49920 (i.e. no. faces on model surface (wing-body/wing-body-fairing) but excluding farfield boundaries)
   BL 1st-Cell Size:   1.0E-06   1.0E-06
 BL Max-Growth Rate: TANH distribution modified with first 4 cells linearly spaced
           BL Cells: 53 cells normal to wall in both meshes
      Miscellaneous:  


FINE GRID SIZE              WB       WBF
----------------------------------------
              Zones:  688 blocks 688 blocks 
        Field Nodes:   9761201   9761201
        Field Cells:   9603072   9603072
     Boundary Nodes:     80561     80561 (i.e. no. points on model surface (wing-body/wing-body-fairing) but excluding farfield boundaries)
     Boundary Faces:     80256     80256 (i.e. no. faces on model surface (wing-body/wing-body-fairing) but excluding farfield boundaries)
   BL 1st-Cell Size:   1.0E-06   1.0E-06
 BL Max-Growth Rate: TANH distribution modified with first 4 cells linearly spaced
           BL Cells: 65 cells normal to wall in both meshes
      Miscellaneous:  


SOLUTION INFORMATION (typical-medium grid)
--------------------
  Computer Platform: Linux Cluster	 
       # Processors: 32 
   Operating System: Red Hat 
           Compiler: ????? 
       Run Time CPU: ????? 
Run Time Wall-Clock: 12 hours (estimated) 
Memory Requirements: 32GB (estimated)
      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
 coarse         0.75    -0.067     0.500   0.03004   0.01761   0.01243   -0.1476
 medium         0.75    -0.099     0.500   0.02886   0.01635   0.01251   -0.1495
 fine           0.75    -0.099     0.500   0.02827   0.01572   0.01255   -0.1510

WING/BODY/FX2B-FAIRING

 GRID_SIZE      MACH     ALPHA    CL_TOT    CD_TOT     CD_PR     CD_SF    CM_TOT
 coarse         0.75    -0.082     0.500   0.02957   0.01701   0.01256   -0.1468
 medium         0.75    -0.115     0.500   0.02838   0.01573   0.01265   -0.1484
 fine           0.75    -0.115     0.500   0.02787   0.01517   0.01269   -0.1502

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
     165.0      90.0     10.0      236.0      81.0      -8.0     237.0      70.0       0.0

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    1.000      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     0.154   0.02047   0.00782   0.01265   0.01967   -0.1599
      0.75      -2.0     0.274   0.02219   0.00956   0.01264   0.01966   -0.1565
      0.75      -1.0     0.393   0.02512   0.01253   0.01259   0.01991   -0.1531
      0.75      -0.5     0.452   0.02706   0.01450   0.01255   0.02015   -0.1513
      0.75       0.0     0.512   0.02935   0.01685   0.01250   0.02051   -0.1490
      0.75       0.5     0.572   0.03215   0.01971   0.01244   0.02112   -0.1459
      0.75       1.0     0.633   0.03578   0.02343   0.01235   0.02225   -0.1424
      0.75       1.5     0.696   0.04078   0.02854   0.01224   0.02446   -0.1395

WING/BODY/FX2B-FAIRING

      MACH     ALPHA    CL_TOT    CD_TOT     CD_PR     CD_SF CD-CL2/PA    CM_TOT
      0.75      -3.0     0.145   0.02006   0.00730   0.01276   0.01935   -0.1561
      0.75      -2.0     0.268   0.02172   0.00896   0.01275   0.01929   -0.1535
      0.75      -1.0     0.391   0.02464   0.01192   0.01272   0.01948   -0.1511
      0.75      -0.5     0.453   0.02661   0.01392   0.01268   0.01970   -0.1497
      0.75       0.0     0.514   0.02897   0.01633   0.01264   0.02005   -0.1479
      0.75       0.5     0.576   0.03187   0.01929   0.01258   0.02066   -0.1451
      0.75       1.0     0.640   0.03568   0.02318   0.01249   0.02184   -0.1421
      0.75       1.5     0.705   0.04095   0.02856   0.01239   0.02420   -0.1397



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.

