[brucewayne123]

I have a rectangular wing of NACA 0012 aerofoil (0.25m chord length and 1m span length). The fluid domain I'm using is of half elliptical-shaped.



I am trying to get hex mesh as tetra mesh yields terrible numerical results for this particular case (compared with experimental results, about 7000% error). The following are the settings I used:
Global
1)Advance sizing function: Proximity and curvature

Local
1)Local method: Multi zone, hex
2)Local edge sizing about the aerofoils (both side): Element size of 1mm/500 no. of division, with both ends bias and bias factor of 5
3)Local edge sizing about the leading and trailing edges: Element size of 1mm/500 no. of division
4)Local inflation: The entire fluid body and the surface of the wing, with 30 layers and growth rate of 1.2. (I even tried 1st layer thickness of 0.01mm with growth rate of 1.2)

However, the local inflation always failed to generate (Inflation not possible with this setting. Mesh without inflation will be created.).


I even tried:

A)Adding local face sizing about the surface of the wing with 5mm element size.
B)Changing the parameters of local edge sizing and local inflation.

but I'm still having the same problem of inflation (Sometimes give errors, sometimes give warnings).



The reason I use multi zone method is because whenever I choose hex dominant method, the inflation method will automatically be shut off. I know that multi zone method actually supports 3D inflation, but I always get error or warning messages whenever I use the inflation features.



I am also wondering whether multi zone method is patch conforming algorithm. This is because ANSYS guide didn't mentioned whether hex dominant and multi zone methods are using patch conforming or independent algorithm. But I presume multi zone method is patch independent and hex dominant method is patch conforming.



PS: I knew some people did structured mesh with ICEM CFD. However, I did not learn ICEM CFD in college, which is why I'm using ANSYS Meshing.