Laminar flow airfoil analysis using Ansys Fluent doesn't converge at AoA above 3 degree. Why?

I'm trying to determine the lift and drag coefficient of airfoil DAE-11 for laminar flow using Ansys Fluent laminar model. RE = 260941.0492 Number of cells = 495700 Maximum mesh skewness =...

12 May 2021 4,162 4 View