2D NACA 4412 airfoil meshing problem

[yfffff1026]

I am trying to simulate a 2D NACA 4412 airfoil in ANSYS Fluent, and I have run into a meshing problem. 

I divided the computational domain into six sections, but one section consistently fails to generate a proper mesh. 

To solve this issue, I have tried several approaches: 

• Using different numbers of airfoil coordinates from the .txt file downloaded from the Airfoil Tools website  

• Changing meshing parameters multiple times, such as the number of divisions, bias factors, and behavior settings (Hard or Soft)  

• Creating the 2D geometry in both DesignModeler and SpaceClaim  

• Modifying the geometry by changing the trailing edge from a point into a finite-thickness section and dividing the domain into 7sections instead of 6  

However, the problem still seems to be caused by a very tiny line segment, which makes the mesh fail. I am using ANSYS Student 2025 R2. 

Has anyone experienced a similar problem or know how to fix it? I would really appreciate any suggestions.

[Rob]

What order are you meshing in? There's also the issue of jump in cell size that may not help the solver if you try and run it.