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James Hetfield May 12, 2012 16:27

Wrapping mesh around NACA0012

Does anyone know how to wrap a NACA0012 airfoil with boundary layer in ICEM?

James Hetfield May 12, 2012 16:29

I mean something like this

Far May 13, 2012 01:46

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.

James Hetfield May 13, 2012 13:56

Its about 5 months that Ive been trying to mesh 2D NACA 0012 airfoil but cant get convergence.
Im really stuck

Far May 13, 2012 14:10

Really :confused:

What you want to do, I can help you. Try ICEM hexa

James Hetfield May 13, 2012 14:21

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

Far May 13, 2012 14:24

small mistake I just found.

James Hetfield May 13, 2012 14:29

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

James Hetfield May 13, 2012 14:53

Whats the matter?

Far May 13, 2012 15:00

Whats the Reynolds no?

James Hetfield May 13, 2012 15:01

6 million
i wanna check my results with those in

Far May 13, 2012 16:00

1 Attachment(s)
check this mesh

James Hetfield May 13, 2012 16:08

should I change it (number of nodes and growth ratios) or just run it in FLUENT with these features?

Thanks man

Far May 13, 2012 16:11

Just output the mesh with appropriate boundary condition and run in Fluent. Tell me the yplus after 20-30 iterations

James Hetfield May 13, 2012 16:21

1 Attachment(s)
Yplus over airfoil surface after 25 iterations
Turbulence model: SST-KW
CFL = 5

Far May 13, 2012 16:24

good enough. proceed with simulation and compare results with experimental. use double precision.

Use hybrid initialization and solution steering

James Hetfield May 13, 2012 16:31

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

Far May 13, 2012 16:33

give CLF 0.1 and use 1st order scheme. Also start new topic in Fluent forum for further discussion.

Far May 13, 2012 16:35

give me boundary conditions, I try them here

James Hetfield May 13, 2012 16:36

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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