Meshing according to the flow problem - External Aerodynamics.
 

Dear Every one!

I am working on a Thesis regarding Ground effect on external aerodynamics of a generic Aircraft model. I have some doubts regarding this. I am an experienced user of ICEM to some extent ! but I have problems in understanding the best concepts! So if any one can help me out I will be grateful. Here are some questions in my mind?

1) What type of mesh is better for External aerodynamics? Blocked structured mesh or Unstructured tetra delaunay or AF mesh with resolve boundary using prism layers? Does the type of the mesh change the results a lot? Or is the effect in results negligible?

2) When you have Density regions such as wake behind the wing how far do you extend it? 2 times the length of Aircraft? What is the standard way?

3) How many cells are in a fine or a coarse mesh for an Aircraft? Because I saw in a NASA Document that 12 million elements of an unstructured mesh is still Coarse!

4) What factors can be considered to minimize the number of cells in a mesh but still capture the important parts in a refined manner?

5) I have problems when it comes to the curvature of the wings using octree meshing? Which factors can be set to enable the mesh to capture the surface curvature? Is it the curvature/proximity refinement? Edge criterion?

Feel free to post any opinions. Regards and thank you in advance
:)

Any answers would be appreciated. Please help

Hello Shereez, I am late to the question. But I hope you would have an answer to those questions you had previously.
I am performing an external aero analysis using Fluent and ICEM for meshing, and I would like to know those answers if you know them.
I will be performing an unstr viscous mesh, but the problem is the geometry is complex and has a lot of faces.
Your info would be of great help.
Thanks!