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


Date:  [Due 28 APR 2006]


PARTICIPANT INFORMATION
-----------------------
               Name: Christopher Rumsey, S. Melissa Rivers, Joe Morrison 
              Email: c.l.rumsey@nasa.gov 
              Phone: (757) 864-2165 
            Address: NASA Langley Research Center 
            Address: MS 128 
            Address: Hampton, VA  23681 
            Address:  
            Address:  
            Address:  


SOLVER INFORMATION
--------------------
        Method Name: CFL3D 
    Basic Algorithm: thin-layer N-S, finite volume, upwind-biased, Roe FDS 
   Turbulence Model: Menter SST k-omega 
      Miscellaneous:  


GRID INFORMATION
--------------------
Grid-Generator Name: Grids were supplied by DPW committee
          Grid Type: structured overset 


COARSE GRID SIZE            WB       WBF
----------------------------------------
              Zones:        12        12
        Field Nodes:   2387918   2395170
        Field Cells:   2256896   2263808
     Boundary Nodes:  
     Boundary Faces:  
   BL 1st-Cell Size:   0.00055   0.00055
 BL Max-Growth Rate:  
           BL Cells:  
      Miscellaneous:  


MEDIUM GRID SIZE            WB       WBF
----------------------------------------
              Zones:        12        12
        Field Nodes:   7985236   8020348
        Field Cells:   7689088   7723136
     Boundary Nodes:  
     Boundary Faces:  
   BL 1st-Cell Size:   0.00038   0.00038
 BL Max-Growth Rate:  
           BL Cells:  
      Miscellaneous:  


FINE GRID SIZE              WB       WBF
----------------------------------------
              Zones:        12        12
        Field Nodes:  26892352  26969192
        Field Cells:  26224640  26299904
     Boundary Nodes:  
     Boundary Faces:  
   BL 1st-Cell Size:   0.00025   0.00025
 BL Max-Growth Rate:  
           BL Cells:  
      Miscellaneous:  


SOLUTION INFORMATION (typical-fine grid)
--------------------
  Computer Platform: various (e.g., PC ia64-linux)
       # Processors: various (e.g., 10)
   Operating System: various (e.g., linux)
           Compiler: various (e.g., linux intel)
       Run Time CPU: various
Run Time Wall-Clock: various (e.g., 110 hrs for 2000 MG cycles)
Memory Requirements: various (e.g., 3100 Mbytes double precision) 
      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
  2387918.      0.75     0.280     0.500   0.02858   0.01688   0.01170   -0.1323
  7985236.      0.75     0.162     0.500   0.02711   0.01532   0.01179   -0.1409
 26892352.      0.75     0.113     0.500   0.02702   0.01506   0.01196   -0.1429

WING/BODY/FX2B-FAIRING

 GRID_SIZE      MACH     ALPHA    CL_TOT    CD_TOT     CD_PR     CD_SF    CM_TOT
  2395170.      0.75     0.074     0.500   0.02803   0.01612   0.01191   -0.1430
  8020348.      0.75     0.116     0.500   0.02681   0.01492   0.01189   -0.1392
 26969192.      0.75     0.079     0.500   0.02660   0.01455   0.01206   -0.1416

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
    171.09     93.89     6.45     233.88     80.60     -7.81    250.80     70.66      2.55

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

   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) 
N.B. Only 1 angle of attack (alpha=0) run for thin-layer drag polar
---------------------------------------------------------------

WING/BODY

      MACH     ALPHA    CL_TOT    CD_TOT     CD_PR     CD_SF CD-CL2/PA    CM_TOT
      0.75       0.0     0.482   0.02653   0.01471   0.01181   0.01873   -0.1427

WING/BODY/FX2B-FAIRING

      MACH     ALPHA    CL_TOT    CD_TOT     CD_PR     CD_SF CD-CL2/PA    CM_TOT
      0.75       0.0     0.485   0.02634   0.01444   0.01190   0.01847   -0.1406



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.

