[ICEM] Sharp leading and trailing edge airfoil

matters_100 · March 16, 2016, 07:19

Hello there,

I'm trying to mesh a symmetric airfoil with a sharp leading and trailing edge (see pic for the geometry), however I didn't manage get the software ICEM to mesh it properly (see other picture).
I've tried to import only the top half of the geometry and mesh it, and them I mirrored the geometry and blocks but the lower part doesn't take into account the airfoil geometry.
I've also tried to mesh the full airfoil at once, but every I end up with this sort of results.

Any ideas ?

Thanks

bboynido · March 16, 2016, 08:04

try this tutorial it helped me a lot
https://www.youtube.com/watch?v=NVyvEH-u0wQ

matters_100 · March 16, 2016, 08:35

Thank but the problem comes from the sharp leading edge of the airfoil. Hence, the topology of the mesh should not be a C-mesh nor a O-mesh.

Any other ideas ?

Thanks.

bboynido · March 16, 2016, 12:44

try this one then
https://www.youtube.com/watch?v=mgjRT4WY_iA

Far · March 17, 2016, 08:37

There are two approaches.

First approach.

1. Make four splits . Two at leading and trailing edge. Two at upper and lower surface of airfoil.

2. Make fifth (vertical) split at mid chord.

3. Merge blockes at leading and training edge

4. associate edges and vertices. Set pre mesh parameters and you are done.

siw · March 17, 2016, 09:06

This is also similar to the ICEM CFD tutorial: Hexa Mesh Generation for a Pipe with Embedded Blade, see the ICEM CFD Tutorial Manual.

Far · March 17, 2016, 09:59

Quote:

Originally Posted by siw

This is also similar to the ICEM CFD tutorial: Hexa Mesh Generation for a Pipe with Embedded Blade, see the ICEM CFD Tutorial Manual.

Yes correct.

matters_100 · March 17, 2016, 10:03

SOLVED.
Thank you everyone, I was missing a step as given in Far's answer:

Quote:

2. Make fifth (vertical) split at mid chord.

.
and that's why it failed before.

Far · March 17, 2016, 10:06

failed or solved?

matters_100 · March 17, 2016, 10:12

I suppose my response wasn't clear :/ but it's solved.
Thks

pmamf · April 5, 2016, 14:20

Hi Far,
what about the second approach?

March 16, 2016, 08:04		#2
bboynido New Member Nader Khattabi Join Date: Mar 2016 Location: Tunisia Posts: 23 Rep Power: 10	try this tutorial it helped me a lot https://www.youtube.com/watch?v=NVyvEH-u0wQ Dronzer likes this.

March 17, 2016, 08:37		#5
Far Super Moderator Sijal Join Date: Mar 2009 Location: Islamabad Posts: 4,553 Blog Entries: 6 Rep Power: 54	There are two approaches. First approach. 1. Make four splits . Two at leading and trailing edge. Two at upper and lower surface of airfoil. 2. Make fifth (vertical) split at mid chord. 3. Merge blockes at leading and training edge 4. associate edges and vertices. Set pre mesh parameters and you are done. Dronzer likes this.

April 5, 2016, 14:20	second approach	#11
pmamf New Member Join Date: Jul 2015 Posts: 3 Rep Power: 10	Hi Far, what about the second approach?

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March 16, 2016, 08:35		#3
matters_100 New Member Robert Jack Join Date: Mar 2016 Posts: 4 Rep Power: 10	Thank but the problem comes from the sharp leading edge of the airfoil. Hence, the topology of the mesh should not be a C-mesh nor a O-mesh. Any other ideas ? Thanks.

March 16, 2016, 12:44		#4
bboynido New Member Nader Khattabi Join Date: Mar 2016 Location: Tunisia Posts: 23 Rep Power: 10	try this one then https://www.youtube.com/watch?v=mgjRT4WY_iA

March 17, 2016, 09:06		#6
siw Senior Member Stuart Join Date: Jul 2009 Location: Portsmouth, England Posts: 733 Rep Power: 25	This is also similar to the ICEM CFD tutorial: Hexa Mesh Generation for a Pipe with Embedded Blade, see the ICEM CFD Tutorial Manual.

March 17, 2016, 10:06		#9
Far Super Moderator Sijal Join Date: Mar 2009 Location: Islamabad Posts: 4,553 Blog Entries: 6 Rep Power: 54	failed or solved?

March 17, 2016, 10:12		#10
matters_100 New Member Robert Jack Join Date: Mar 2016 Posts: 4 Rep Power: 10	I suppose my response wasn't clear :/ but it's solved. Thks