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[ANSYS Meshing] How to: Grid independence study for structured mesh

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Old   March 29, 2018, 23:46
Question How to: Grid independence study for structured mesh in ICEM CFD
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Hi everyone,

I am trying to predict cd and cl for NACA 0012 which is a test case from Drag Prediction Workshop 6. I have constructed a structured mesh (minimum quality=0.9 and minimum angle=72) as shown in Figures (attached).
Using the above mesh I completed the simulation in Fluent with 7% and 2% errors in cd and cl.
I want to improve the above results and planning to do a grid independence study. Is there any standard way of doing it for structured mesh in ICEM?
If yes, please tell me.
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Old   March 30, 2018, 04:04
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A simple method is: Find a reasonable solution on a coarse grid. Refine globally, e.g. by 2x2 cell splitting (in 2D). Rerun your simulation and compare the results.
Refine further until you reach satisfying convergence.
BUT: Keep in mind which discretisation schemes you are using. Second order accuracy formally leads to 'faster' convergence when reducing discrete step sizes than first order schemes.
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Old   March 30, 2018, 04:14
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Hi NablaDyn,

Thank you for your reply.
Yes, I do have an initial mesh and solution now.
Can you tell me how to refine the grid globally for a structured mesh in ICEM ?
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Old   March 30, 2018, 04:26
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I'm not familiar with ICEM. But I'm perfectly sure it offers such refinement tool(s) . Searching the GUI or ICEM's help pages would be the best next step.
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Old   March 30, 2018, 04:54
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Thanks for the suggestions
I could see global sizing parameter for unstructured meshing. But I could not find such options for structured meshing.
I am quite new to ICEM so I may be wrong.
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Old   March 30, 2018, 04:59
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Can you apply that refinement tool or is it not available for your mesh? If so, is the resulting mesh still of quad type? If not, do you have access to the mesh generation data, i.e. where the point distributions on the lines and the surface meshes have been defined?
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Old   March 30, 2018, 08:09
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Quote:
Originally Posted by NablaDyn View Post
Can you apply that refinement tool or is it not available for your mesh?
I believe that global refinement tools are only for unstructured mesh in ICEM(as far as I know).

Quote:
Originally Posted by NablaDyn View Post
If so, is the resulting mesh still of quad type? If not, do you have access to the mesh generation data, i.e. where the point distributions on the lines and the surface meshes have been defined?
Yes, I do have access to the number of elements, distribution etc of edges of the blocks (as in fig).
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Old   March 30, 2018, 08:42
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Well, that's a good starting point. I assume the 'nodes' entry in the bottom left mask is what you are looking for. Try to adapt the number of nodes uniformly at each mesh-defining edge. As your mesh looks pretty dense I would suggest to first coarsen it, say half number of points, before going too fine.
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Old   March 31, 2018, 23:37
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If you use blocks to generate your mesh, you can start with corse mesh, e.g. 1 million nodes. Then you can increase the nodes to larger numbers, like 2, 4, 8, 16 million.

For 2D problem, you can double the nodes for 1 direction each time.

Compare the results to check convergence. For this case, you can compare global parameters like drag force. Or you can plot out the velocity profiles, or other variables your project is interested in, at certain location to compare. When the change is not much, the mesh can be thought as converged.

Above is my understanding for grid convergence check. Hope it help.
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drag and lift, grid independent study, icem 18.1, naca 0012, structured hex mesh

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