[Crank-Shaft]

Fellow CFD-enthusiasts,

I have been looking for a way to create grids identical to those in the link below for a NACA4412 -
https://turbmodels.larc.nasa.gov/naca4412sep_grids.html

I am interested in these files -

• (3-D) 2 x 1793 x 513 (2 x 1025 points on airfoil surface) (13.2 MB)
• (3-D) 2 x 897 x 257 (2 x 513 points on airfoil surface) (3.4 MB)

I have a research CFD code and want to modify the boundary conditions given (as they are not implemented) and also increase the number of blocks by equally splitting at selected grid points to export a multiblock CGNS grid with lots of equally balanced/weighted blocks for efficient parallelisation.

Is this possible on ICEM? I have tried using a simple O-grid topology but the bias sizing around the leading and trailing edges don't match the ones on the NASA site. Additionally I am not sure how to smooth out the multiblock structured grids so that near-wall cells are all perpendicular to the aerofoil surface like in this image for example Mesh 1 or Mesh 2
I believe these were created in GridPro and Pointwise respectively.

Any help or suggestions are greatly appreciated.

Best wishes,