CFD Online Logo CFD Online URL
www.cfd-online.com
[Sponsors]
Home > Forums > General Forums > Main CFD Forum

how to create airfoil section for NACA0012?

Register Blogs Community New Posts Updated Threads Search

 
 
LinkBack Thread Tools Search this Thread Display Modes
Prev Previous Post   Next Post Next
Old   March 8, 2003, 14:15
Default how to create airfoil section for NACA0012?
  #1
stone_gargoly
Guest
 
Posts: n/a
HI, Now I am working for NACA0012.CAN ANYONE HELP TO CREATE THE NACA0012 PROFILE OR TELL ME THE METHODE. THANK YOU
  Reply With Quote

 


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
getting airfoil surface to be recongized for tri mesh josip76 ANSYS Meshing & Geometry 4 June 9, 2011 22:48
[GAMBIT] Periodic BC truffaldino ANSYS Meshing & Geometry 4 June 5, 2011 06:39
[Other] cgnsToFoam problems with "QUAD_4" cells lentschi OpenFOAM Meshing & Mesh Conversion 1 March 9, 2011 04:49
Calculating polars from 2D airfoil coordinates... wlvrn Main CFD Forum 0 August 18, 2010 18:43
LiftDrag utility from v12 to v141 cfdphil OpenFOAM Running, Solving & CFD 2 December 5, 2007 05:49


All times are GMT -4. The time now is 00:49.