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

Part 1

Date:  23 May 2006		


PARTICIPANT INFORMATION		
-----------------------		
               Name:  	Olaf Brodersen
              Email:  	o.brodersen@dlr.de
              Phone:  	+49-531-295-2439
            Address:  	DLR, Institute of Aerodynamics and Flow Technology
            Address:  	Lilienthalplatz 7
            Address:  	38108 Braunschweig
            Address:  	Germany


SOLVER INFORMATION		
--------------------		
        Method Name:  	TAU
    Basic Algorithm:  	Finite Volume, central difference, artificial dissipation
   Turbulence Model:  	Spalart-Allmaras, Edwards mod.
      Miscellaneous:  	unstructured, hybrid, node based


GRID INFORMATION		
--------------------		
Grid-Generator Name:  	Centaur from CentaurSoft (grids named Centaur)
          Grid Type:  	hybrid 


COARSE GRID SIZE           		 WB		   WBF
----------------------------------------				
              Zones:			1		   1
        Field Nodes:  			2464385		   2873102
     Boundary Nodes:  		        45065              60423
     Boundary Faces:  			
   BL 1st-Cell Size:  			y+~ 0.9	           y+~ 0.9
 BL Max-Growth Rate:  	
           BL Cells:  			21	           21       (prismatic layers)
      Miscellaneous:  				


MEDIUM GRID SIZE           		 WB		   WBF
----------------------------------------				
              Zones:			1		   1
        Field Nodes:  			5102446		   6111664
     Boundary Nodes:  		        85769              112672
     Boundary Faces:  			
   BL 1st-Cell Size:  			y+~ 0.9	           y+~ 0.9
 BL Max-Growth Rate:  		
           BL Cells:  			31	           31       (prismatic layers)
      Miscellaneous:  				


FINE GRID SIZE           		 WB		   WBF
----------------------------------------				
              Zones:			1		   1
        Field Nodes:  			8535263 	   10305876
     Boundary Nodes:  		        121588             167434
     Boundary Faces:  			
   BL 1st-Cell Size:  	                y+~ 0.9            y+~ 0.9
 BL Max-Growth Rate:  			                  
           BL Cells:  			40	           40       (prismatic layers)
      Miscellaneous:  				



SOLUTION INFORMATION (medium grid)				
--------------------				
  Computer Platform:  			SUN Opteron Cluster	
       # Processors:  			16 (for these cases)
   Operating System:  			Linux
           Compiler:  			GNU 3.2.3
       Run Time CPU:  	                6.6 s/iter (WBF medium grid)
Run Time Wall-Clock:  			
Memory Requirements:  			
      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
2464385		0.75	-0.141	0.49992	0.027369 0.01561  0.01176  -0.1527
5102446		0.75	-0.194	0.49978	0.026770 0.01490  0.01187  -0.1591
8535263         0.75    -0.108  0.49976 0.02658  0.01445  0.01206  -0.15717
							
WING/BODY/FX2B-FAIRING							
							
GRID_SIZE	MACH	ALPHA	CL_TOT	CD_TOT	 CD_PR	 CD_SF	  CM_TOT
2873102		0.75	-0.021	0.50015 0.027327 0.01548 0.01185  -0.1467
6111664		0.75	-0.121	0.50030 0.026664 0.01467 0.01199  -0.1560
10305876	0.75	-0.127	0.50009 0.026255 0.01425 0.01200  -0.1573

SEPARATION BUBBLE GEOMETRY - WING/BODY - Medium 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
215.7   82.5    4.6      238.0          75.0            surf            237.8           surf            -3.5

SEPARATION BUBBLE GEOMETRY - WING/BODY/FX2B-FAIRING - Medium 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								

WING/BODY

STATION	Y (m)	Y/BO2	X/C-WB	X/C-WBF
1	0.08785	0.15	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	0.3009	0.514	1.000	1.000
7	0.37319	0.638	1.000	1.000
8	0.49602	0.847	1.000	1.000


WING/BODY/FX2B-FAIRING

STATION	Y (m)	Y/BO2	X/C-WB	X/C-WBF
1	0.08785	0.15	1.0     1.0
2	0.13987	0.239	1.0     1.0
3	0.19453	0.331	1.0     1.0
4	0.22156	0.377	1.0     1.0
5	0.24037	0.411	1.0     1.0
6	0.3009	0.514	1.0     1.0
7	0.37319	0.638	1.0     1.0
8	0.49602	0.847	1.0     1.0



"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	-3.000	?.?     ?.?     ?.?     ?.?     ?.?             ?.?
0.75	-2.000	0.2730  0.02052 0.00856 0.01196 0.018023        -0.1622
0.75	-1.000	0.3955  0.02343 0.01151 0.01193 0.018189        -0.1600
0.75	-0.500	0.4579  0.02532 0.01342 0.01189 0.018295        -0.1590
0.75	-0.194  0.4998  0.02677 0.01490 0.01187 0.018400        -0.1591
0.75	0.500	0.5751  0.03020 0.01845 0.01175 0.019118        -0.1520
0.75	1.000	0.6318  0.03361 0.02199 0.01163 0.020269        -0.1461
0.75	1.500	0.6867  0.03825 0.02680 0.01145 0.022450        -0.1397
							
WING/BODY/FX2B-FAIRING							
							
MACH	ALPHA	CL_TOT	CD_TOT	CD_PR	CD_SF	CD-CL2/PA	CM_TOT
0.75	-3.000  ?.?     ?.?     ?.?     ?.?     ?.?             ?.?
0.75	-2.000  0.2673  0.02020 0.00810 0.01210 0.017806        -0.1605
0.75	-1.000  0.3911  0.02306 0.01099 0.01207 0.017938        -0.1584
0.75	-0.500  0.4530  0.02496 0.01293 0.01203 0.018085        -0.1574
0.75	-0.121  0.5003  0.02666 0.01467 0.01199 0.018273        -0.1560
0.75	0.500	0.5776  0.03008 0.01819 0.01189 0.018906        -0.1523
0.75	1.000	0.6409  0.03380 0.02202 0.01177 0.020033        -0.1482
0.75	1.500	0.7014  0.03883 0.02722 0.01160 0.022341        -0.1434




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.
