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


Date:  [Due 28 APR 2006]


PARTICIPANT INFORMATION
-----------------------
               Name:     Dimitri Mavriplis
              Email:     mavripl@uwyo.edu
              Phone:     307-766-2868
            Address:     Department of Mechanical Engineering
            Address:     University of Wyoming
            Address:     1000 E. University Ave.
            Address:     Laramie WY 82072
            Address:     USA
            Address:  


SOLVER INFORMATION
--------------------
        Method Name:    NSU3D
    Basic Algorithm:    Unstructured, mixed elements, multigrid
   Turbulence Model:    Spalart-Allmaras
      Miscellaneous:  


GRID INFORMATION
--------------------
Grid-Generator Name:    VGRID
          Grid Type:    LaRC Node-Based Unstructured Grid Set (merged into mixed elements)


COARSE GRID SIZE            WB       WBF
----------------------------------------
              Zones:           1         1
        Field Nodes:     5371747   5637495
        Field Cells:    20109200  20847300
     Boundary Nodes:      134519    142409
     Boundary Faces:      254406    270217
   BL 1st-Cell Size:  
 BL Max-Growth Rate:  
           BL Cells:     5712550   6124265 (prisms)
      Miscellaneous: LaRC Node-Based Grids, merged into mixed elements (prisms, tets, pyramids)


MEDIUM GRID SIZE            WB       WBF
----------------------------------------
              Zones:            1          1
        Field Nodes:     14324914   14627168
        Field Cells:     58967802   59647050
     Boundary Nodes:       286050     295916
     Boundary Faces:       550343     570137
   BL 1st-Cell Size:  
 BL Max-Growth Rate:  
           BL Cells:     12595740   13144822 (prisms)
      Miscellaneous: LaRC Node-Based Grids, merged into mixed elements (prisms, tets, pyramids)


FINE GRID SIZE              WB       WBF
----------------------------------------
              Zones:           1            1
        Field Nodes:    40059252     41118446
        Field Cells:                182427113
     Boundary Nodes:      618130       650376
     Boundary Faces:     1203861      1268564
   BL 1st-Cell Size:
 BL Max-Growth Rate:
           BL Cells:    27894717     29603771 (prisms)
      Miscellaneous: LaRC Node-Based Grids, merged into mixed elements (prisms, tets, pyramids)



SOLUTION INFORMATION (typical-fine grid)
--------------------
  Computer Platform:    NASA Columbia
       # Processors:    248
   Operating System:    Linux
           Compiler:    ifort
       Run Time CPU:  
Run Time Wall-Clock:    1.5 hours to 2 hours
Memory Requirements:    112 Gbytes
      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
   5354214      0.75    -0.046     0.500   0.02692   0.01492   0.01200   -0.1484
  14298135      0.75     0.000     0.500   0.02678   0.01493   0.01185   -0.1449
  40059252      0.75     0.050     0.500   0.02652   0.01483   0.01168   -0.1442
                                                                                                                   
WING/BODY/FX2B-FAIRING
                                                                                                                   
 GRID_SIZE      MACH     ALPHA    CL_TOT    CD_TOT     CD_PR     CD_SF    CM_TOT
   5618073      0.75     0.104     0.500   0.02688   0.01476   0.01213   -0.1408
  14598610      0.75     0.163     0.500   0.02656   0.01456   0.01201   -0.1378
  41069036      0.75     0.213     0.500   0.02631   0.01450   0.01181   -0.1356


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
    210.41     80.96     3.40     235.82     70.70     10.20    237.21     67.35      5.97

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
    000.00    000.00   000.00     000.00    000.00    000.00    000.00    000.00    000.00

UPPER-SURFACE TRAILING-EDGE SEPARATION LOCATION (Defined as -ve Cf vector component normal to local TE line)

   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    0.974      0.982
        3.   0.19453     0.331    0.971      0.972
        4.   0.22156     0.377    0.972      0.973
        5.   0.24037     0.411    0.970      0.969
        6.   0.30090     0.514    0.958      0.957
        7.   0.37319     0.638    0.961      0.961
        8.   0.49602     0.847    0.969      0.969 



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

WING/BODY  (MED GRID: 14M pts)

      MACH     ALPHA    CL_TOT    CD_TOT     CD_PR     CD_SF CD-CL2/PA    CM_TOT
      0.75      -3.0     0.154   0.01851   0.00647   0.01203   0.01772   -0.1592
      0.75      -2.0     0.265   0.02010   0.00807   0.01202   0.01775   -0.1558
      0.75      -1.0     0.384   0.02281   0.01084   0.01197   0.01787   -0.1518
      0.75      -0.5     0.440   0.02445   0.01253   0.01191   0.01796   -0.1488
      0.75       0.0     0.505   0.02674   0.01487   0.01186   0.01820   -0.1474
      0.75       0.5     0.564   0.02932   0.01754   0.01178   0.01866   -0.1428
      0.75       1.0     0.624   0.03281   0.02114   0.01167   0.01976   -0.1376
      0.75       1.5     0.684   0.03746   0.02595   0.01151   0.02178   -0.1329

WING/BODY/FX2B-FAIRING  (MED GRID: 14M pts)

      MACH     ALPHA    CL_TOT    CD_TOT     CD_PR     CD_SF CD-CL2/PA    CM_TOT
      0.75      -3.0     0.120   0.01804   0.00588   0.01216   0.01756   -0.1507
      0.75      -2.0     0.241   0.01943   0.00728   0.01216   0.01748   -0.1476
      0.75      -1.0     0.360   0.02198   0.00985   0.01212   0.01764   -0.1439
      0.75      -0.5     0.420   0.02371   0.01162   0.01208   0.01780   -0.1416
      0.75       0.0     0.480   0.02579   0.01376   0.01203   0.01807   -0.1388
      0.75       0.5     0.541   0.02837   0.01641   0.01195   0.01856   -0.1352
      0.75       1.0     0.604   0.03175   0.01991   0.01184   0.01953   -0.1311
      0.75       1.5     0.665   0.03640   0.02472   0.01168   0.02158   -0.1266




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.

