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[ICEM] Wrapping mesh around NACA0012

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Old   May 12, 2012, 16:27
Post Wrapping mesh around NACA0012
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Hi

Does anyone know how to wrap a NACA0012 airfoil with boundary layer in ICEM?
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Old   May 12, 2012, 16:29
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I mean something like this
http://www.google.com/imgres?hl=en&b...9&tx=134&ty=79
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Old   May 13, 2012, 01:46
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either go for
1. the prism + tetra or

2. create two domain.
One for the structured mesh for boundary layer and other one for the outer domain with tetra and then merge them to form the continuous mesh. There is one tutorial on hybrid meshing in ICEM 11 tutorial guide.
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Old   May 13, 2012, 13:56
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Its about 5 months that Ive been trying to mesh 2D NACA 0012 airfoil but cant get convergence.
Im really stuck
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Old   May 13, 2012, 14:10
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Really

What you want to do, I can help you. Try ICEM hexa
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Old   May 13, 2012, 14:21
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I generate the grid exactly based on what Simon has said in the tutorial but it does not work for me

I sent u two emails. Id appreciate it if u take a look at my meshes
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Old   May 13, 2012, 14:24
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small mistake I just found.
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Old   May 13, 2012, 14:29
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I need the grid to be fine enough (first layer of the order of 10^-6 or 10^-7 normal to the airfoil surface) to get the correct drag coefficient
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Old   May 13, 2012, 14:53
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Whats the matter?
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Old   May 13, 2012, 15:00
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Whats the Reynolds no?
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Old   May 13, 2012, 15:01
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6 million
i wanna check my results with those in http://turbmodels.larc.nasa.gov/naca0012_val.html
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Old   May 13, 2012, 16:00
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check this mesh
Attached Files
File Type: zip naca0012.zip (43.2 KB, 22 views)
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Old   May 13, 2012, 16:08
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should I change it (number of nodes and growth ratios) or just run it in FLUENT with these features?

Thanks man
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Old   May 13, 2012, 16:11
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Just output the mesh with appropriate boundary condition and run in Fluent. Tell me the yplus after 20-30 iterations
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Old   May 13, 2012, 16:21
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Yplus over airfoil surface after 25 iterations
Turbulence model: SST-KW
CFL = 5
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File Type: jpg Yplus.jpg (53.0 KB, 22 views)
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Old   May 13, 2012, 16:24
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good enough. proceed with simulation and compare results with experimental. use double precision.

Use hybrid initialization and solution steering
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Old   May 13, 2012, 16:31
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it doesnt converge and just oscillates
also, based on NASA website that I mentioned earlier, I think more nodes are needed on the airfoil surface
and more resolution is required near the trailing edge
ratio in the boundary layer must be less than 1.06 but here its 1.23
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Old   May 13, 2012, 16:33
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give CLF 0.1 and use 1st order scheme. Also start new topic in Fluent forum for further discussion.
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Old   May 13, 2012, 16:35
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give me boundary conditions, I try them here
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Old   May 13, 2012, 16:36
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ahh
this convergence is killing me
I cant get a mesh working
I dont know if i should switch to another mesher or solver
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