Learning Forum

[marcoshenriquegarciagomes]

Here, I show the differences in the aerodynamic coefficients during mesh refinement.

I ran simulations for two different airfoils, one of them being symmetrical. For the non symmetrical one, it was needed close to 600k elements for both the Cofficient of Lift and Drag to converge. For the symmetrical airfoil, at 140k elements, the mesh already had good results, but the chosen mesh to get more accurate results was the one with 230k elements. Other parameters, such as y+ and Orthogonal Quality were used during mesh refinement.
Below there is a table with the values of CL and CD for each mesh made for the second airfoil and a photo of one of the meshes.