PUMA run on NACA 0012 Wing geometry

Inviscid grid runs using double precision with alpha=5 deg

• Ran on cocoa.aero.psu.edu with 2 nodes (requires 446 MB memory)
• Results after 3 orders reduction in norm
• M=0.30 run
  • Residual history
  • Convergence history
  • PUMA input file
  • PUMA restart file (binary)
  • Tecplot ASCII data (surface only)
  • Tecplot ASCII data (entire flowfield)
  • Plots:
    • Pressure Contours at section Z=-3 (PS file)
    • Pressure Contours at section X=( 0.0, -0.5, -1.0, -1.5, -2.0 )
    • Animated gif from X=0.0 to X=-2.0 to see the tip vortices
    • Animated gif from X=-1 to X=-10 to see the tip vortices
    • Enstrophy at one chord length downstream
    • X-component of vorticity at one chord length downstream
    • Y-component of vorticity at one chord length downstream
    • Z-component of vorticity at one chord length downstream
    • X-component of vorticity around wing-tip section