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

NACA 0012

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

Reply
 
LinkBack Thread Tools Display Modes
Old   July 6, 2006, 12:48
Default NACA 0012
  #1
Ihab Sraj
Guest
 
Posts: n/a
Hello Everybody, do u know from where i can get the mesh files for the NACA 0012 airfoil to use in gambit . . . . .

Thanks in advance
  Reply With Quote

Old   July 6, 2006, 17:20
Default Re: NACA 0012
  #2
Glenn Horrocks
Guest
 
Posts: n/a
Hi,

I do not know anywhere to get the mesh files from, but there are extensive references on the web to generate the NACA profile and you can generate meshes yourself from there. Do a google search on NACA0012 and you'll find heaps.

Glenn Horrocks
  Reply With Quote

Old   July 7, 2006, 02:41
Default Re: NACA 0012
  #3
Ihab Sraj
Guest
 
Posts: n/a
I searched the CFD-online message index and found out that there are reference websites for airfoils design.

The direct link is the following: http://www.pagendarm.de/trapp/progra...les/NACA4.html

Thanks Glenn
  Reply With Quote

Old   July 22, 2006, 01:50
Default Re: NACA 0012
  #4
mahmood.kaskani
Guest
 
Posts: n/a
HELLO.

I DON'T KNOW TO MESHING THE AIRFOIL IN TURBULENT FLOW

THANKS
  Reply With Quote

Old   August 3, 2006, 04:10
Default NACA 0012
  #5
Bhuvnaesh Kannan
Guest
 
Posts: n/a
Sir,

i need pressure distribution curve over NACA 0012 at different anagles of attack(5,10,15,20,25 deg). free stream velocity = 100.8 km/hr, density = 1.224 kg/ cubic meter
  Reply With Quote

Old   August 9, 2006, 18:00
Default Re: NACA 0012
  #6
Jack Navarro Vargas
Guest
 
Posts: n/a
Please , I need to help you about information the NACA0012 , because I will do work the project.
  Reply With Quote

Old   August 29, 2006, 10:35
Default Re: NACA 0012
  #7
Jacob
Guest
 
Posts: n/a
you can find a small program which generates points for airfoil definition, including NACA0012 which is a very standard airfoil.

The way to mesh it is using inflated prism mesh around the airfoil to capture the boundary layer.

good luck.

  Reply With Quote

Reply

Thread Tools
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 On
Pingbacks are On
Refbacks are On


Similar Threads
Thread Thread Starter Forum Replies Last Post
Naca 0012 validation, Cd value is too high. Peter88 OpenFOAM 4 January 21, 2014 16:10
How to import NACA 0012 Profile in Gridgen maplepink Main CFD Forum 17 May 7, 2013 13:01
NACA 0012 Case Will Not Converge dancfd OpenFOAM Running, Solving & CFD 6 November 14, 2011 19:09
Problems with flat plate and NACA 0012 Lift/Force Harly FLUENT 0 June 18, 2007 10:02
NACA 0012 simulation results Luis FLUENT 3 February 15, 2006 11:42


All times are GMT -4. The time now is 09:50.