[ICEM] Wrapping mesh around NACA0012

James Hetfield · May 12, 2012, 17:27

Hi

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

James Hetfield · May 12, 2012, 17:29

I mean something like this
http://www.google.com/imgres?hl=en&b...9&tx=134&ty=79

Far · May 13, 2012, 02:46

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, 14:56

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, 15:10

Really

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

James Hetfield · May 13, 2012, 15:21

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, 15:24

small mistake I just found.

James Hetfield · May 13, 2012, 15:29

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, 15:53

Whats the matter?

Far · May 13, 2012, 16:00

Whats the Reynolds no?

James Hetfield · May 13, 2012, 16:01

6 million
i wanna check my results with those in http://turbmodels.larc.nasa.gov/naca0012_val.html

Far · May 13, 2012, 17:00

check this mesh

James Hetfield · May 13, 2012, 17:08

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, 17:11

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, 17:21

Yplus over airfoil surface after 25 iterations
Turbulence model: SST-KW
CFL = 5

Far · May 13, 2012, 17:24

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

Use hybrid initialization and solution steering

James Hetfield · May 13, 2012, 17:31

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, 17:33

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

Far · May 13, 2012, 17:35

give me boundary conditions, I try them here

James Hetfield · May 13, 2012, 17:36

ahh
this convergence is killing me
I cant get a mesh working
I dont know if i should switch to another mesher or solver

May 12, 2012, 17:27	Wrapping mesh around NACA0012	#1
James Hetfield Member Join Date: Oct 2011 Location: OH, USA Posts: 77 Rep Power: 15	Hi Does anyone know how to wrap a NACA0012 airfoil with boundary layer in ICEM?

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May 12, 2012, 17:29		#2
James Hetfield Member Join Date: Oct 2011 Location: OH, USA Posts: 77 Rep Power: 15	I mean something like this http://www.google.com/imgres?hl=en&b...9&tx=134&ty=79

May 13, 2012, 02:46		#3
Far Senior Member Sijal Join Date: Mar 2009 Location: Islamabad Posts: 4,558 Blog Entries: 6 Rep Power: 54	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.

May 13, 2012, 14:56		#4
James Hetfield Member Join Date: Oct 2011 Location: OH, USA Posts: 77 Rep Power: 15	Its about 5 months that Ive been trying to mesh 2D NACA 0012 airfoil but cant get convergence. Im really stuck

May 13, 2012, 15:10		#5
Far Senior Member Sijal Join Date: Mar 2009 Location: Islamabad Posts: 4,558 Blog Entries: 6 Rep Power: 54	Really What you want to do, I can help you. Try ICEM hexa

May 13, 2012, 15:21		#6
James Hetfield Member Join Date: Oct 2011 Location: OH, USA Posts: 77 Rep Power: 15	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

May 13, 2012, 15:24		#7
Far Senior Member Sijal Join Date: Mar 2009 Location: Islamabad Posts: 4,558 Blog Entries: 6 Rep Power: 54	small mistake I just found.

May 13, 2012, 15:29		#8
James Hetfield Member Join Date: Oct 2011 Location: OH, USA Posts: 77 Rep Power: 15	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

May 13, 2012, 15:53		#9
James Hetfield Member Join Date: Oct 2011 Location: OH, USA Posts: 77 Rep Power: 15	Whats the matter?

May 13, 2012, 16:00		#10
Far Senior Member Sijal Join Date: Mar 2009 Location: Islamabad Posts: 4,558 Blog Entries: 6 Rep Power: 54	Whats the Reynolds no?

May 13, 2012, 16:01		#11
James Hetfield Member Join Date: Oct 2011 Location: OH, USA Posts: 77 Rep Power: 15	6 million i wanna check my results with those in http://turbmodels.larc.nasa.gov/naca0012_val.html

May 13, 2012, 17:08		#13
James Hetfield Member Join Date: Oct 2011 Location: OH, USA Posts: 77 Rep Power: 15	should I change it (number of nodes and growth ratios) or just run it in FLUENT with these features? Thanks man

May 13, 2012, 17:11		#14
Far Senior Member Sijal Join Date: Mar 2009 Location: Islamabad Posts: 4,558 Blog Entries: 6 Rep Power: 54	Just output the mesh with appropriate boundary condition and run in Fluent. Tell me the yplus after 20-30 iterations

May 13, 2012, 17:24		#16
Far Senior Member Sijal Join Date: Mar 2009 Location: Islamabad Posts: 4,558 Blog Entries: 6 Rep Power: 54	good enough. proceed with simulation and compare results with experimental. use double precision. Use hybrid initialization and solution steering

May 13, 2012, 17:31		#17
James Hetfield Member Join Date: Oct 2011 Location: OH, USA Posts: 77 Rep Power: 15	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

May 13, 2012, 17:33		#18
Far Senior Member Sijal Join Date: Mar 2009 Location: Islamabad Posts: 4,558 Blog Entries: 6 Rep Power: 54	give CLF 0.1 and use 1st order scheme. Also start new topic in Fluent forum for further discussion.

May 13, 2012, 17:35		#19
Far Senior Member Sijal Join Date: Mar 2009 Location: Islamabad Posts: 4,558 Blog Entries: 6 Rep Power: 54	give me boundary conditions, I try them here

May 13, 2012, 17:36		#20
James Hetfield Member Join Date: Oct 2011 Location: OH, USA Posts: 77 Rep Power: 15	ahh this convergence is killing me I cant get a mesh working I dont know if i should switch to another mesher or solver