CFD Online Logo CFD Online URL
www.cfd-online.com
[Sponsors]
Home > Forums > Software User Forums > OpenFOAM > OpenFOAM Meshing & Mesh Conversion

[Commercial meshers] Naca 0012 airfoil

Register Blogs Members List Search Today's Posts Mark Forums Read

Reply
 
LinkBack Thread Tools Search this Thread Display Modes
Old   January 27, 2009, 04:52
Default Naca 0012 airfoil
  #1
Senior Member
 
NAVEEN.K.M
Join Date: Mar 2009
Location: Bangalore, Karnataka, india
Posts: 114
Rep Power: 17
naveen is on a distinguished road
HI EVERYBODY

i hav created a naca 0012 airfoil in gambit and i solved in fluent...now i need to convert it into openfoam 1.4.1....i need how to import FROM fluentMeshTofoam of fluent 6.3 version ...
naveen is offline   Reply With Quote

Old   January 27, 2009, 12:36
Default I am not sure to get what you
  #2
Senior Member
 
maddalena's Avatar
 
maddalena
Join Date: Mar 2009
Posts: 436
Rep Power: 23
maddalena will become famous soon enough
I am not sure to get what you mean, but fluentMeshToFoam meshfile.msh -case casename -scale scalecoeff works for me, with meshfile.msh generated for fluent 6.3. In any case, you can write fluentMeshToFoam -help at your command line.
Hope this help.
Bye
mad
maddalena is offline   Reply With Quote

Old   February 2, 2009, 06:59
Default Gijsbert Wierink sir my pro
  #3
Senior Member
 
NAVEEN.K.M
Join Date: Mar 2009
Location: Bangalore, Karnataka, india
Posts: 114
Rep Power: 17
naveen is on a distinguished road
Gijsbert Wierink sir

my problem is that i hav done the naca 0012 airfoil case in gambit and i solved in fluent 6.3 ...now i want to compare these results in openfoam 1.4.1..now i need to import to fluentMeshTofoam in openfoam 1.4.1...can u tell me the procedure how to import the (.msh) file to openfoam 1.4.1..for example i used this format for conversion(my case name is-naca0012.msh) fluentMeshToFoam . naca0012 ./naca0012/naca0012.msh -scale 0.001 but the case is not running in foamX....PLEASE HELP ME REGARDING THIS..
naveen is offline   Reply With Quote

Old   July 7, 2010, 05:27
Default
  #4
New Member
 
Sofia
Join Date: May 2010
Location: Toulouse, France
Posts: 14
Rep Power: 15
Sofia is on a distinguished road
Hi,

I calculating the flow around a naca 0015 airfoil in the water but I don't know why my simulation is not correct when I choose k=0.1 and epsilon=30 (k epsilon model)
Have you got an idea?

Thank you

Sofia
Sofia is offline   Reply With Quote

Old   July 8, 2010, 05:46
Default
  #5
New Member
 
Sebastian
Join Date: Feb 2010
Posts: 9
Rep Power: 16
sebware is on a distinguished road
Hey naveen

1. You copy the fluent meshfile *.msh to the directory of your case.
2. You switch to this directory in your terminal.
3. You run fluentMeshToFoam naca0012.msh
4. run checkMesh to find proplems in the Mesh.

I dont know if in OF 1.4 you have the fluent3DMeshToFoam.
But if you have it, use this one instead of fluentMeshToFoam, I like it.

i hope it helps !

best regards
Sebastian
sebware is offline   Reply With Quote

Old   August 18, 2010, 01:07
Default
  #6
New Member
 
darioth's Avatar
 
Darío Montes
Join Date: Aug 2009
Location: Córdoba, Argentina
Posts: 12
Rep Power: 16
darioth is on a distinguished road
Send a message via MSN to darioth Send a message via Skype™ to darioth
Hello,

Does anybody tried first with potentialFoam and comment me the correct results in NACA0015 airfoil??

Regards
darioth is offline   Reply With Quote

Old   August 18, 2010, 01:10
Default
  #7
New Member
 
darioth's Avatar
 
Darío Montes
Join Date: Aug 2009
Location: Córdoba, Argentina
Posts: 12
Rep Power: 16
darioth is on a distinguished road
Send a message via MSN to darioth Send a message via Skype™ to darioth
Hello,

One question: Did you tried with potentialFoam in de NACA0015 first?


Regards
darioth is offline   Reply With Quote

Old   April 14, 2011, 12:03
Default running a sharp NACA with OpenFOAM
  #8
jms
Member
 
José
Join Date: Jan 2011
Posts: 73
Rep Power: 15
jms is on a distinguished road
Dear all,

I have run computations for a NACA with a sharp trailing edge (the original one...) using Low-Re meshes and I get high aspect ratio issues (the max AR is about 30000). I run it anyways and I get divergence. Since this airfoil needs a C-mesh, it is inevitable to get this high aspect ratios in the cells of the wake...

Any idea about how to deal with this? (using meshes with low y+ still...)?

Best Regards,

José
jms is offline   Reply With Quote

Reply

Thread Tools Search this Thread
Search this Thread:

Advanced Search
Display Modes

Posting Rules
You may not post new threads
You may not post replies
You may not post attachments
You may not edit your posts

BB code is On
Smilies are On
[IMG] code is On
HTML code is Off
Trackbacks are Off
Pingbacks are On
Refbacks are On


Similar Threads
Thread Thread Starter Forum Replies Last Post
NACA 0012 Airfoil, simpleFoam, Spalart Allmaras badwalgurpreet OpenFOAM Running, Solving & CFD 11 December 29, 2021 19:04
Ffd_control_point_2d feiyi SU2 4 September 30, 2019 13:42
yPlus NACA 0012 Airfoil badwalgurpreet OpenFOAM Running, Solving & CFD 7 March 8, 2019 02:35
High drag for airfoil compared to XFOIL and wind tunnel data Ry10 SU2 15 October 30, 2016 18:27
2D FFD Optimization RLangtry SU2 2 August 5, 2014 10:48


All times are GMT -4. The time now is 04:24.