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


Date:  3 AUG 2006		


PARTICIPANT INFORMATION		
-----------------------		
               Name:  		Edward N. Tinoco
              Email:  		edward.n.tinoco@boeing.com
              Phone:  		425-234-1147
            Address:  		Boeing Commercial Airplanes
            Address:  		Mail Code 67-LK
            Address:  		P.O. Box 3707
            Address:  		"Seattle, WA 98124"
            Address:  		USA
            Address:  		


SOLVER INFORMATION		
--------------------		
        Method Name:  		CFL3D/Zeus
    Basic Algorithm:  		Finite Volume
   Turbulence Model:  		Spalart-Allmaras
      Miscellaneous:  		


GRID INFORMATION		
--------------------		
Grid-Generator Name:  		BCA-Advancing Front
          Grid Type:  		"Structured Block, Point-to-Point Matched"


COARSE GRID SIZE   			WB	WBF
----------------------------------------				
              Zones:  			26	26
        Field Nodes:  			"2,635,778"	"2,635,778"
        Field Cells:  			"2,298,880"	"2,298,880"
     Boundary Nodes:  			"24,286"	"24,286"
     Boundary Faces:  			"21,760"	"21,760"
   BL 1st-Cell Size:  			y+~ 0.82	y+~ 0.82
 BL Max-Growth Rate:  			<1.2 	<1.2 
           BL Cells:  			24	24
      Miscellaneous:  				


MEDIUM GRID SIZE     			WB	WB
----------------------------------------				
              Zones:  			38	38
        Field Nodes:  			"9,182,078"	"9,182,078"
        Field Cells:  			"8,080,896"	"8,080,896"
     Boundary Nodes:  			"57,120"	"57,120"
     Boundary Faces:  			"51,456"	"51,456"
   BL 1st-Cell Size:  			y+~0.60	y+~0.60
 BL Max-Growth Rate:  			<1.2 	<1.2 
           BL Cells:  			32	32
      Miscellaneous:  				


FINE GRID SIZE       			WB	WBF
----------------------------------------				
              Zones:  			48	48
        Field Nodes:			"17,977,893"	"17,977,893"
        Field Cells:  			"15,856,320"	"15,856,320"
     Boundary Nodes:  			"90,993"	"90,993"
     Boundary Faces:  			"81,984"	"81,984"
   BL 1st-Cell Size:  			y+~0.50	y+~0.50
 BL Max-Growth Rate:  			<1.2 	<1.2 
           BL Cells:  			40	40
      Miscellaneous:  				
				
VERY FINE GRID SIZE  			WB	WB
----------------------------------------				
              Zones:  			58	58
        Field Nodes:			"30,751,522"	"30,751,522"
        Field Cells:  			"27,185,664"	"27,185,664"
     Boundary Nodes:  			"126,307"	"126,307"
     Boundary Faces:  			"114,208"	"114,208"
   BL 1st-Cell Size:  			y+~0.40	y+~0.40
 BL Max-Growth Rate:  			<1.2 	<1.2 
           BL Cells:  			48	48
      Miscellaneous:  				


SOLUTION INFORMATION (typical-fine grid)				
--------------------				
  Computer Platform:  			Opteron Cluster	
       # Processors:  			48	48
   Operating System:  			SLES 9.0 Linux 	2.6.5
           Compiler:  			PGI 6.1	
       Run Time CPU:  			85 hr	91 hr
Run Time Wall-Clock:  			5.5 hr	4 hr
Memory Requirements:  			17680Mb	17680Mb
      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
2635778		0.75	-0.191	0.500	0.02732	0.01494	0.01238	-0.1568
9182078		0.75	-0.138	0.500	0.02667	0.01435	0.01231	-0.1550
17977893	0.75	-0.142	0.500	0.02649	0.01419	0.01230	-0.1554
30751522	0.75	-0.152	0.500	0.02642	0.01411	0.01231	-0.1564
							
WING/BODY/FX2B-FAIRING							
							
GRID_SIZE	MACH	ALPHA	CL_TOT	CD_TOT	CD_PR	CD_SF	CM_TOT
2635778		0.75	-0.072	0.500	0.02726	0.01484	0.01242	-0.1502	
9182078		0.75	-0.028	0.500	0.02660	0.01418	0.01242	-0.1490	
17977893	0.75	-0.036	0.500	0.02645	0.01403	0.01242	-0.1496	
30751522	0.75	-0.044	0.500	0.02640	0.01398	0.01243	-0.1506	

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
211.0	81.0	0.0	235.0		72.0		surface		236.5		surface		-4.0

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	0.15	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



"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	0.159	0.01859	0.00612	0.01247	0.01774	-0.1682
0.75	-2.000	0.279	0.02033	0.00787	0.01246	0.01772	-0.1638
0.75	-1.000	0.398	0.02322	0.01081	0.01241	0.01790	-0.1597
0.75	-0.500	0.457	0.02509	0.01273	0.01236	0.01809	-0.1570
0.75	0.000	0.516	0.02731	0.01502	0.01229	0.01839	-0.1528
0.75	0.500	0.577	0.03008	0.01787	0.01221	0.01892	-0.1503
0.75	1.000	0.640	0.03370	0.02162	0.01209	0.02000	-0.1467
0.75	1.500	0.701	0.03872	0.02679	0.01193	0.02226	-0.1429
							
WING/BODY/FX2B-FAIRING							
							
MACH	ALPHA	CL_TOT	CD_TOT	CD_PR	CD_SF	CD-CL2/PA	CM_TOT
0.75	-3.000	0.137	0.01822	0.00566	0.01256	0.01759	-0.1603
0.75	-2.000	0.260	0.01985	0.00728	0.01256	0.01759	-0.1566
0.75	-1.000	0.381	0.02264	0.01012	0.01252	0.01776	-0.1530
0.75	-0.500	0.442	0.02451	0.01203	0.01248	0.01795	-0.1511
0.75	0.000	0.504	0.02675	0.01433	0.01242	0.01826	-0.1489
0.75	0.500	0.565	0.02949	0.01715	0.01233	0.01879	-0.1456
0.75	1.000	0.629	0.03312	0.02090	0.01222	0.01987	-0.1422
0.75	1.500	0.691	0.03816	0.02609	0.01206	0.02214	-0.1388




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.
