[anand_30]

I am trying to mesh a NACA0012 airfoil.
Let me be frank and tell you that I am a complete newcomer to Openfoam and to this field of CFD.What I want to do is to compare the lift and drag coefficients for this airfoil vs same airfoil with Gurney flap(its a flap perpendicular to chord,fitted at the trailing edge more about it here http://en.wikipedia.org/wiki/Gurney_flap)
I think salome is the probably good way to mesh this airfoil(but haven't tried blockmesh yet)so what i did is get co-ordinates for airfoil(using javaFoil),the number of co-ordinates is 61,then I created a wire,also created test area and cut that airfoil from test area.
I am getting a very weird kind of mesh(see image)
Also i am not able to convert mesh from IdeasunvToFoam.
what is the most appropriate way to mesh airfoil with quadratic elements so that mesh will be fine around airfoil and at the region past trailing edge?