RESULTS OF FIRST DRAG PREDICTION WORKSHOP

                     USING NSU3D UNSTRUCTURED MULTIGRID CODE

                                          (Anaheim, CA June 9-10, 2001)



SUMMARY OF RESULTS

 A wing body test case was selected by the AIAA Applied Aerodynamics Technical Committee
for calibrating the effectiveness of various Computational Fluid Dynamics (CFD) computer codes
at predicting drag for aerodynamic configurations in the transonic cruise regime.

The data included below represents the results obtained with the NSU3D unstructured grid solver.
The test cases included a range of Mach numbers from 0.6 to 0.8, and a range of incidences for
each Mach number.
 

Results at these conditions were computed on 3 different grids with the NSU3D solver:
 

  •  A baseline grid of 1.6 million points
  •  A medium grid of 3 million points (not shown here)
  •  A fine grid of 13 million points

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     A total of 72 steady-state solutions were run on the baseline (1.6 million point) grid.
      These cases were all run on the  ICASE PC cluster CORAL
      Each case requires about 3 Gbytes of memory and 3 hours of wall clock time using 32 cpus (800MHz Pentium III)
      The total parametric study was completed in about 1 week on CORAL.

     A total of 6 steady-state solutions were run on the fine (13 million point) grid.
       These cases were all run on   LOMAX, the NAS SGI Origin 2000 system .
        Each case requires about 27 Gbytes of memory and 4 hours of wall clock time using 128 cpus (400MHZ R12000)

    The pictures above depict the baseline unstructured grid (1.6 millon points)
    and a solution in terms of computed surface pressure contours.

    A detailed description of these calculations is given below....
     
     

  •  Announcement and Description of Workshop (at www.aiaa.org)
  •   Description of Workshop Cases (pdf file)
  •   AGARD Document and Data Files are Also Available