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


Date:  [Due 11 AUG 2006]


PARTICIPANT INFORMATION
-----------------------
               Name: Murayama Mitsuhiro
              Email: murayama.mitsuhiro@jaxa.jp
              Phone: +81-422-40-1382
            Address: Japan Aerospace Exploration Agency 
            Address: 7-44-1 Jindaiji-Higashi,
            Address: Chofu, Tokyo 182-8522 
            Address: JAPAN
            Address:  
            Address:
Co-authors
               Name: Zhong Lei, Kazuomi Yamamoto, Kentaro Tanaka
                     Tohru Hirai, Ryozo Ito, Hiroaki Ishikawa 

SOLVER INFORMATION
--------------------
        Method Name: TAS_Flow code 
    Basic Algorithm: Upwind, cell-vertex finite volume, Hybrid(Mixed Elm.) unstructured 
   Turbulence Model: Spalart-Allmaras model with a modification (SA_mod) 
      Miscellaneous: HLLEW(Harten-Lax-van Leer-Einfeldt-Wada) method for flux computation
                     MPI, LU-SGS(Lower/Upper Symmetric Gauss-Seidel) implicit method
                     SA_mod:1. without using the trip term for transition 
                            2. without using the ft2 function
                            3. with a modification of production term
                                (use of the minimum of the vorticity and strain rate
                                 to decrease dissipation at the vortex center)


GRID INFORMATION
--------------------
Grid-Generator Name: TAS_Mesh code  
          Grid Type: Hybrid unstructured mesh (tetrahedrons, prisms, and pyramids)  


COARSE GRID SIZE            WB       WBF
----------------------------------------
              Zones:         1         1
        Field Nodes:   5399929   5422128
        Field Cells:  Tetra(4977084 5022575)  Prisms(8902227 8932644)
     Boundary Nodes:    134294    135819
     Boundary Faces:    268273    271323
   BL 1st-Cell Size:  4.249e-6  4.249e-6
 BL Max-Growth Rate:       1.2       1.2
           BL Cells:        50        50
      Miscellaneous:  


MEDIUM GRID SIZE            WB       WBF
----------------------------------------
              Zones:         1         1
        Field Nodes:   9431154   9481477
        Field Cells:  Tetra(10663491 10778697)  Prisms(14913753 14976920)
     Boundary Nodes:    218531    223229
     Boundary Faces:    436591    445987
   BL 1st-Cell Size:  2.832e-6  2.832e-6
 BL Max-Growth Rate:       1.2       1.2
           BL Cells:        50        50
      Miscellaneous:  


FINE GRID SIZE              WB       WBF
----------------------------------------
              Zones:         1         1
        Field Nodes:  17535215  17219535
        Field Cells:  Tetra(25307705 23868585)  Prisms(25944605 25808920)
     Boundary Nodes:    368497    378201
     Boundary Faces:    736289    755697
   BL 1st-Cell Size:  1.912e-6  1.912e-6
 BL Max-Growth Rate:       1.2       1.2
           BL Cells:        70        70
      Miscellaneous:  


SOLUTION INFORMATION (typical-fine grid)
--------------------
  Computer Platform:  Fujitsu PrimePower HPC2500, SPARC 64V(1.3GHz, 1792cpu)
       # Processors:  64
   Operating System:  SunOS 5.8
           Compiler:  Fujitsu MPI Fortran
       Run Time CPU:  75 hours per 1 CPU
Run Time Wall-Clock:  150 hours per 1 CPU
Memory Requirements:  82 Gbytes per 64 CPUs
      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
  5399929.      0.75     0.274     0.500   0.02926   0.01725   0.01200   -0.1324
  9431154.      0.75     0.213     0.499   0.02840   0.01640   0.01200   -0.1372
 17535215.      0.75     0.104     0.500   0.02842   0.01636   0.01205   -0.1430

WING/BODY/FX2B-FAIRING

 GRID_SIZE      MACH     ALPHA    CL_TOT    CD_TOT     CD_PR     CD_SF    CM_TOT
  5422128.      0.75     0.168     0.499   0.02868   0.01656   0.01212   -0.1354
  9481477.      0.75     0.081     0.500   0.02773   0.01558   0.01216   -0.1408
 17219535.      0.75     0.017     0.500   0.02725   0.01505   0.01220   -0.1453

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
    165.63     84.72     7.79     233.25     83.09     -7.17    233.86     71.19      4.25

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    0.810      1.000
        2.   0.13987     0.239    1.000      1.000
        3.   0.19453     0.331    1.000      0.986
        4.   0.22156     0.377    1.000      0.987
        5.   0.24037     0.411    0.987      0.979
        6.   0.30090     0.514    0.997      0.978
        7.   0.37319     0.638    0.999      0.975
        8.   0.49602     0.847    1.000      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     0.122   0.01965   0.00750   0.01215   0.01914   -0.1486
      0.75      -2.0     0.240   0.02104   0.00889   0.01215   0.01911   -0.1459
      0.75      -1.0     0.357   0.02360   0.01148   0.01212   0.01933   -0.1428
      0.75      -0.5     0.416   0.02533   0.01325   0.01208   0.01955   -0.1409
      0.75       0.0     0.474   0.02740   0.01537   0.01203   0.01988   -0.1384
      0.75       0.5     0.533   0.02991   0.01796   0.01195   0.02134   -0.1352
      0.75       1.0     0.594   0.03315   0.02130   0.01184   0.02325   -0.1314
      0.75       1.5     0.653   0.03755   0.02587   0.01168   0.02325   -0.1272


WING/BODY/FX2B-FAIRING

      MACH     ALPHA    CL_TOT    CD_TOT     CD_PR     CD_SF CD-CL2/PA    CM_TOT
      0.75      -3.0     0.121   0.01936   0.00710   0.01226   0.01887   -0.1468
      0.75      -2.0     0.244   0.02073   0.00845   0.01227   0.01873   -0.1455
      0.75      -1.0     0.367   0.02336   0.01111   0.01225   0.01886   -0.1439
      0.75      -0.5     0.428   0.02516   0.01294   0.01222   0.01902   -0.1427
      0.75       0.0     0.490   0.02734   0.01517   0.01217   0.01930   -0.1411
      0.75       0.5     0.552   0.03002   0.01793   0.01209   0.01979   -0.1386
      0.75       1.0     0.617   0.03354   0.02156   0.01198   0.02078   -0.1357
      0.75       1.5     0.679   0.03838   0.02657   0.01181   0.02294   -0.1318



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.


