[Gmsh] Airfoil meshing Naca 0012

Emanuele T. nuovodna at gmail.com
Fri Feb 19 21:15:25 CET 2010


Hi, i wrote a mesh using naca 0012 points taken here
http://www.soton.ac.uk/~jps7/Aircraft%20Design%20Resources/Sydney%20aerodynamics%20for%20students/panel2d/naca0012.dat

I want to intensify the density of points near the leading edge and the
trailing edge. How can i obtain this??
Thanks
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