O-grid mesh for NACA airfoil
 

Hej

I am Sathya and this is my first post..

I am trying to do simulations for NACA airfoil for a surface roughness study. I have been generating hexa mesh in ICEM. I am new to Block Meshing. I did C-grid mesh by following Simon tutorials. But since i have to maintain y+ of 30 near the wall to BL calculations , I need to have 0.0001 for my first layer distance which degrades the orthogonal quality when smoothing. i attached pics of that. So I switched for O grid block mesh around airfoil.I increased the no of nodes near the leading edge to capture the curvature. I need help with meshing around the curvature of Leading edge. And also whether this type of grid around LE is recommended to go with.

I hope I am clear with description of the problem...

Can someone help me with this?

Thank you in advance.


Regards
Sathya