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


Date:  27 APRIL 2006


PARTICIPANT INFORMATION
-----------------------
               Name:  Peter Eliasson, Shia-Hui Peng
              Email:  peter.eliasson@foi.se, peng@foi.se
              Phone:  +46 8 55503225 (+46 709 277280)
            Address:  FOI, Swedish Defence Research Agency
            Address:  Systems Technology Division
            Address:  Computational Physics Department
            Address:  SE-172 90 Stockholm
            Address:  Sweden
            Address:  


SOLVER INFORMATION
--------------------
        Method Name:  Edge, Unstructured edge based
    Basic Algorithm:  Unstructured, node centered, dual grid, multigrid
   Turbulence Model:  Hellsten k-omega EARSM
      Miscellaneous:  Explicit steady state, multigrid acceleration


GRID INFORMATION
--------------------
Grid-Generator Name:  ANSYS CFX-Mesh, grid was supplied
          Grid Type:  Hybrid/unstructured mesh


COARSE GRID SIZE            WB       WBF
----------------------------------------
              Zones:         1         1
        Field Nodes:   3059189   3163605
        Field Cells:   8773810   8860779
     Boundary Nodes:     74640     78829
     Boundary Faces:    148982    157374
   BL 1st-Cell Size:     6E-07     6E-07
 BL Max-Growth Rate:         0         0
           BL Cells:   4581225   4854518
      Miscellaneous:  Note: Growth rate unknown


MEDIUM GRID SIZE            WB       WBF
----------------------------------------
              Zones:         1         1
        Field Nodes:   8038922   8272308
        Field Cells:  26194716  26293307
     Boundary Nodes:    168006    179071
     Boundary Faces:    335558    357713
   BL 1st-Cell Size:     4E-07     4E-07
 BL Max-Growth Rate:         0         0
           BL Cells:  10484219  11142429
      Miscellaneous:  Note: Growth rate unknown


FINE GRID SIZE              WB       WBF
----------------------------------------
              Zones:         1         1
        Field Nodes:  18120772  20472520
        Field Cells:  65056800  73059851
     Boundary Nodes:    329200    375190
     Boundary Faces:    657772    749758
   BL 1st-Cell Size:   2.5E-07   2.5E-07
 BL Max-Growth Rate:         0         0
           BL Cells:  20625275  23568965
      Miscellaneous:  Note: Growth rate unknown


SOLUTION INFORMATION (typical-fine grid)
--------------------
  Computer Platform:  Linux cluster
       # Processors:  16
   Operating System:  Linux
           Compiler:  Intel ifort 9.0
       Run Time CPU:  768 h
Run Time Wall-Clock:  48 h
Memory Requirements:  20 Gbyte summed up
      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
  3059189.      0.75   0.040 0.4970 2.8560E-02 1.6152E-02 1.2403E-02 -1.3245E-01
  8038922.      0.75   0.040 0.5006 2.8003E-02 1.5510E-02 1.2493E-02 -1.3659E-01
 18120772.      0.75   0.040 0.5039 2.7625E-02 1.4775E-02 1.2849E-02 -1.4745E-01

WING/BODY/FX2B-FAIRING

 GRID_SIZE      MACH     ALPHA    CL_TOT    CD_TOT     CD_PR     CD_SF    CM_TOT
  3163605.      0.75   0.157 0.4968 2.8430E-02 1.6079E-02 1.2350E-02 -1.2682E-01
  8272308.      0.75   0.157 0.5002 2.7826E-02 1.5393E-02 1.2433E-02 -1.3014E-01
 20472520.      0.75   0.157 0.5021 2.7575E-02 1.5088E-02 1.2488E-02 -1.3151E-01

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
    226.1        68.3    -0.8    230.5       66.7      -9.0    223.8      68.8   -2.7  Bubble1
                         -2.0                                  240.4      68.    -4.6  Bubble2
Note: several bubbles detected on fuselage, see attached picture


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 
Note: no separation detected at these locations


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 1.4158E-01 1.9685E-02 7.0768E-03 1.2607E-02 1.9013E-02 -1.5005E-01
      0.75     -2.0 2.6063E-01 2.1201E-02 8.5983E-03 1.2606E-02 1.8925E-02 -1.4588E-01
      0.75     -1.0 3.7843E-01 2.3897E-02 1.1324E-02 1.2573E-02 1.9099E-02 -1.4191E-01
      0.75     -0.5 4.3689E-01 2.5699E-02 1.3151E-02 1.2540E-02 1.9304E-02 -1.3980E-01
      0.75      0.0 4.9524E-01 2.7837E-02 1.5333E-02 1.2497E-02 1.9619E-02 -1.3687E-01
      0.75      0.5 5.5435E-01 3.0435E-02 1.7989E-02 1.2441E-02 2.0138E-02 -1.3307E-01
      0.75      1.0 6.1457E-01 3.3850E-02 2.1485E-02 1.2360E-02 2.1195E-02 -1.2880E-01
      0.75      1.5 6.7387E-01 3.8507E-02 2.6253E-02 1.2250E-02 2.3292E-02 -1.2436E-01

WING/BODY/FX2B-FAIRING

      MACH     ALPHA    CL_TOT    CD_TOT     CD_PR     CD_SF CD-CL2/PA    CM_TOT
      0.75     -3.0 1.2160E-01 1.9291E-02 6.7451E-03 1.2546E-02 1.8796E-02 -1.4194E-01
      0.75     -2.0 2.4247E-01 2.0661E-02 8.1074E-03 1.2554E-02 1.8691E-02 -1.3872E-01
      0.75     -1.0 3.6210E-01 2.3223E-02 1.0703E-02 1.2520E-02 1.8830E-02 -1.3546E-01
      0.75     -0.5 4.2152E-01 2.4976E-02 1.2485E-02 1.2491E-02 1.9023E-02 -1.3356E-01
      0.75      0.0 4.8105E-01 2.7089E-02 1.4640E-02 1.2450E-02 1.9335E-02 -1.3114E-01
      0.75      0.5 5.4118E-01 2.9681E-02 1.7288E-02 1.2394E-02 1.9868E-02 -1.2774E-01
      0.75      1.0 6.0253E-01 3.3101E-02 2.0786E-02 1.2315E-02 2.0937E-02 -1.2389E-01
      0.75      1.5 6.6360E-01 3.7810E-02 2.5605E-02 1.2204E-02 2.3055E-02 -1.2000E-01



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.

