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


Date:  [Due 28 APR 2006]


PARTICIPANT INFORMATION
-----------------------
               Name:  Elizabeth M. Lee-Rausch & Dr. Christopher L. Rumsey
              Email:  e.m.lee-rausch@larc.nasa.gov
              Phone:  757-864-8422
            Address:  MS 128
            Address:  NASA Langley Research Center
            Address:  Hampton, VA 23681-2199
            Address:  
            Address:  
            Address:  


SOLVER INFORMATION
--------------------
        Method Name:  FUN3D
    Basic Algorithm:  Unstructured Grid Upwind RANS
   Turbulence Model:  SA
      Miscellaneous:  Node-Centered


GRID INFORMATION
--------------------
Grid-Generator Name: VGridNS
          Grid Type: Unstructured Node-Centered Tetrahedral 


COARSE GRID SIZE            WB       WBF
----------------------------------------
              Zones: 	     1          1 
        Field Nodes:  5,354,214  5,618,073
        Field Cells: 31,481,575 33,037,458   
     Boundary Nodes:    134,519    142,409
     Boundary Faces:    269,034    284,814 
   BL 1st-Cell Size:     0.0006     0.0006
 BL Max-Growth Rate:  1.16-1.30  1.16-1.30 
           BL Cells:        ~32        ~32
      Miscellaneous: VGridNS IFACT 1.5 Rate1 .16 Rate2 .02


MEDIUM GRID SIZE            WB       WBF
----------------------------------------
              Zones:          1 
        Field Nodes: 14,298,135 14,598,610 
        Field Cells: 84,078,830 85,850,911
     Boundary Nodes:    286,050    295,916
     Boundary Faces:    572,096    591,828
   BL 1st-Cell Size:     0.0004     0.0004
 BL Max-Growth Rate:  1.16-1.30  1.16-1.30 
           BL Cells:        ~32        ~32  
      Miscellaneous: VGridNS IFACT 1.0 Rate1 .16 Rate2 .02


FINE GRID SIZE              WB       WBF
----------------------------------------
              Zones:           1
        Field Nodes:  40,014,934  41,069,036
        Field Cells: 235,263,704 241,486,342 
     Boundary Nodes:     618,130     650,376 
     Boundary Faces:   1,236,256   1,300,748 
   BL 1st-Cell Size:    0.000267    0.000267
 BL Max-Growth Rate:   1.16-1.30   1.16-1.30 
           BL Cells:         ~32         ~32 
      Miscellaneous: VGridNS IFACT 0.67 Rate1 .16 Rate2 .02 


SOLUTION INFORMATION (typical-fine grid)
--------------------
  Computer Platform: Altix
       # Processors: 128
   Operating System: Linux
           Compiler: Intel 8.0
       Run Time CPU: 4,281 hours 
Run Time Wall-Clock: 33.4 hours 
Memory Requirements: 1.0GB/processor 
      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     0.729     0.500   0.02974   0.01858   0.01117   -0.1216
 14298135.      0.75     0.877     0.500   0.03017   0.01925   0.01091   -0.1193
 40014934.      0.75     1.061     0.499   0.03121   0.02058   0.01063   -0.1150

WING/BODY/FX2B-FAIRING

 GRID_SIZE      MACH     ALPHA    CL_TOT    CD_TOT     CD_PR     CD_SF    CM_TOT
  5618073.      0.75     0.176     0.500   0.02672   0.01526   0.01147   -0.1321
 14598610.      0.75     0.220     0.500   0.02618   0.01489   0.01129   -0.1295
 41069036.      0.75     0.303     0.500   0.02601   0.01497   0.01103   -0.1239

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
     82.54   -131.90    33.87     230.21   -110.67     -1.42    216.20    -73.42     14.37

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
      0.00      0.00     0.00       0.00      0.00      0.00      0.00      0.00      0.00

UPPER-SURFACE TRAILING-EDGE SEPARATION LOCATION

   STATION     Y (m)     Y/BO2   X/C-WB    X/C-WBF
        1.   0.08785     0.150    0.475      1.000
        2.   0.13987     0.239    0.941      0.973
        3.   0.19453     0.331    0.958      0.957
        4.   0.22156     0.377    0.957      0.956
        5.   0.24037     0.411    0.952      0.952
        6.   0.30090     0.514    0.968      0.971
        7.   0.37319     0.638    0.972      0.979
        8.   0.49602     0.847    0.975      0.983 



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     0.093   0.01839   0.00705   0.01134   0.01810   -0.1411
      0.75      -2.0     0.203   0.01977   0.00845   0.01131   0.01839   -0.1361
      0.75      -1.0     0.312   0.02217   0.01092   0.01125   0.01891   -0.1310
      0.75      -0.5     0.363   0.02387   0.01269   0.01119   0.01945   -0.1284
      0.75       0.0     0.415   0.02578   0.01466   0.01112   0.02001   -0.1255
      0.75       0.5     0.465   0.02807   0.01705   0.01102   0.02083   -0.1222
      0.75       1.0     0.512   0.03091   0.02003   0.01088   0.02213   -0.1182
      0.75       1.5     0.550   0.03467   0.02399   0.01068   0.02453   -0.1146

WING/BODY/FX2B-FAIRING

      MACH     ALPHA    CL_TOT    CD_TOT     CD_PR     CD_SF CD-CL2/PA    CM_TOT
      0.75      -3.0     0.118   0.01754   0.00607   0.01147   0.01707   -0.1439
      0.75      -2.0     0.238   0.01891   0.00744   0.01147   0.01701   -0.1401
      0.75      -1.0     0.357   0.02142   0.01000   0.01143   0.01715   -0.1362
      0.75      -0.5     0.416   0.02312   0.01173   0.01138   0.01732   -0.1338
      0.75       0.0     0.474   0.02515   0.01383   0.01132   0.01762   -0.1310
      0.75       0.5     0.533   0.02763   0.01640   0.01123   0.01811   -0.1272
      0.75       1.0     0.592   0.03088   0.01977   0.01111   0.01914   -0.1224
      0.75       1.5     0.651   0.03536   0.02443   0.01093   0.02116   -0.1176



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.

