Hello everyone,
I am working on a CFD analysis of a blended wing body aircraft. All parameters as aspect ratio, volume ratio, etc are so good, less non-Orthogonality, which is worst. It is equal to 81.77. I applied a local size element at wing, 0.05. Although,apperantly, the mesh apperantly is good at geometry, exist some imperfections at trailing edge of whole airplane:
Could I decrease the non-Orthogonality without decrease the local siz? Since I have done before, applying a local size equal to 0.01, and the core hours goes to 225 min, and run out the time before finishing the meshing.
My advice here would be to improve the refinements. For example, look how big the maximum element size is compared to the characteristics of the trailing edge:
What you can do here is to create a cartesian box that contains the problematic area, and add a region refinement with a very small “maximum edge length”, so the mesh is created properly. Go smaller than 0.05 on this trailing edge, otherwise it will not really help
Have a look at the different refinement options here:
