Ben Dankongkakul

2d airfoil meshing and results

Discussion created by Ben Dankongkakul on Apr 5, 2009
Latest reply on May 7, 2009 by Anthony Botting
I've been trying to get accurate lift and drag coefficients of a naca 2412 for days now and have finally started making some progress. I've took someones advice here on increasing the boundary to 200*c and the lift coefficient is now pretty close. However, the drag coefficient is still about double the experimental value. I've tried changing the turbulence boundary and testing at different aoa and reynolds number. Any ideas what I could be doing wrong? I heard that drag is difficult to get accurate results with, is that true for even low aoa and moderate flight conditions?

Also, what is the best way to create a mesh for this simulation? It seems like I can only refine the mesh is horizontal and vertical bands or very closely around the airfoil. When i refine the mesh around the airfoil using to local mesh tool, it creates many extra cells along the z-dir instead of leaving it at 1 cell for 2d simulation. Thank you and sorry for themany questions

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