Date:  05th July 2001


PARTICIPANT INFORMATION
-----------------------
               Name:  Stéphane AMANT
              Email:  stephane.amant@airbus.aeromatra.com
              Phone:  (33).5.61.18.65.19
            Address:  Département Aérodynamique - M0142/3
			    AIRBUS FRANCE
			    316, route de Bayonne
			    31060 TOULOUSE - FRANCE


SOLVER INFORMATION
--------------------
        Method Name:  NSMB
    Basic Algorithm:  Resolution of the RANS equations, using a cell-centered finite volume formulation
   Turbulence Model:  Spalart-Allmaras
      Miscellaneous:  Multigrid, Jameson's central scheme (+damping of the normal artificial dissipation fluxes),
			    scalar LU-SGS method (implicit)



CASE 1 PROVIDED GRID USED
-------------------------
        Multi-block:  X

CASE 1 "BUILT-IN-HOUSE" GRID USED
---------------------------------
        Multi-block:  X



CASE 1 WITH "BUILT-IN-HOUSE" GRID
---------------------------------
Grid-Generator Name:  ICEMCFD HEXA
          Grid Type:  C topology
        Field Nodes:  5 323 741
        Field Cells:  4 976 128



SOLUTION INFORMATION (PROVIDED GRID)
------------------------------------
  Computer Platform:  CRAY SV1
       # Processors:  4
   Operating System:  UNICOS
           Compiler:  f90
       Run Time CPU:  irrelevant (shared memory)
Run Time Wall-Clock:  irrelevant (shared memory)
Memory Requirements:  350 MWords

SOLUTION INFORMATION ("BUILT-IN-HOUSE" GRID)
--------------------------------------------
  Computer Platform:  CRAY SV1
       # Processors:  4
   Operating System:  UNICOS
           Compiler:  f90
       Run Time CPU:  irrelevant (shared memory)
Run Time Wall-Clock:  irrelevant (shared memory)
Memory Requirements:  496 MWords



CASE 1 DATA ON PROVIDED GRID (REQUIRED)
---------------------------------------
      MACH     ALPHA     CL_TOT  CD_TOT    CD_PR     CD_SF     CM_TOT
      0.75     0.750     0.500   0.04656   0.02173   0.02483   -0.0982

CASE 1 DATA ON "BUILT-IN-HOUSE" GRID
------------------------------------
      MACH     ALPHA     CL_TOT  CD_TOT    CD_PR     CD_SF     CM_TOT
      0.75    -0.120	 0.501   0.03061   0.01649   0.01411   -0.1553



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.
* CM_TOT (F10.4) Total Moment Coefficient.