[themrdjj]

I'm working on a c-grid around an airfoil. At the leading edge, some cells exhibit very high skewness, which reduces the overall quality of the mesh quite a bit. This skewness is created because the o-grid block edge at the leading edge is assigned to the geometry curves.


One solution would be to increase the spacing near the LE, but that would again reduce the smoothness because of the spacing in the o-grid. Is there any way to "smoothen" curvature by realigning nodes of the mesh? Or does anyone have another idea how to deal with this? Maybe a different distribution on the middle edge?

[lgn_aero]

Originally Posted by themrdjj

I'm working on a c-grid around an airfoil. At the leading edge, some cells exhibit very high skewness, which reduces the overall quality of the mesh quite a bit. This skewness is created because the o-grid block edge at the leading edge is assigned to the geometry curves.


One solution would be to increase the spacing near the LE, but that would again reduce the smoothness because of the spacing in the o-grid. Is there any way to "smoothen" curvature by realigning nodes of the mesh? Or does anyone have another idea how to deal with this? Maybe a different distribution on the middle edge?

What's your domain shape?

[AidealZohary]

Hi, this is an old thread. But if anyone is still interested to run a simulation on the NACA 0012, NACA 4415, FX 61-184 E420 and S1223 airfoil, please take a look at:

Numerical Investigation on the Pressure Drag of Some Low-Speed Airfoils for UAV Application.

https://doi.org/10.37934/cfdl.13.2.2948

Unsteady 3-equation k omega intermittency SST was used. Good comparison with XFOIL and experimental data. Transition features also shown through cf and cp plots.

Learn how I designed the mesh here:

https://www.youtube.com/watch?v=qZRqBu9Ss2U