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

NACA0012 gird generator

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

Reply
 
LinkBack Thread Tools Display Modes
Old   April 26, 2009, 23:55
Default NACA0012 gird generator
  #1
New Member
 
Prashanth
Join Date: Mar 2009
Posts: 3
Rep Power: 8
Prashanth is on a distinguished road
I would like to know where I will be able to find a grid generator code for the NACA 0012 airfoil. Thank you...

Prashanth
Prashanth is offline   Reply With Quote

Old   April 26, 2009, 23:59
Default
  #2
Senior Member
 
N/A
Join Date: Mar 2009
Posts: 188
Rep Power: 8
harishg is on a distinguished road
I guess you need to be specific on what kind of grid you need ?
harishg is offline   Reply With Quote

Old   April 27, 2009, 00:54
Default
  #3
Super Moderator
 
praveen's Avatar
 
Praveen. C
Join Date: Mar 2009
Location: Bangalore
Posts: 251
Blog Entries: 6
Rep Power: 9
praveen is on a distinguished road
For unstructured grids, look at bamg, gmsh, triangle (shewchuck), delaundo.

Dont know any for structured grids.
praveen is offline   Reply With Quote

Old   April 27, 2009, 01:41
Default
  #4
New Member
 
Prashanth
Join Date: Mar 2009
Posts: 3
Rep Power: 8
Prashanth is on a distinguished road
I was looking for structured O grids
Prashanth is offline   Reply With Quote

Old   April 27, 2009, 06:34
Default
  #5
New Member
 
Anon
Join Date: Apr 2009
Posts: 13
Blog Entries: 1
Rep Power: 8
technophobe is on a distinguished road
There's an analytical function for the thickness of a NACA00XX airfoil.
The upper surface of the airfoil is given by:

Code:
upper(I) = thick*5.*(0.2969*sqrt(x(I)) - 0.1260*x(I) - 0.3516*x(I)^2 + 0.2843*x(I)^3 - 0.1015*x(I)^4 )
Where 'thick' is the airfoil thickness - 0.12 in your case. x(I) is the distance along the normalised chord (i.e. x/c) at the I'th node. The NACA0012 is symmetric so simply reflect across the x-axis and you've got your foil.

Note that this gives a shape function that doesn't close at the trailing edge. This is a feature of the NACA analytical functions. In my own work this doesn't cause any problems but you can simply set the thickness to be zero at the trailing edge to close the foil if you need to. The camber is zero for this 'foil.

Hope this helps,
T
technophobe is offline   Reply With Quote

Old   May 1, 2009, 04:20
Default
  #6
Super Moderator
 
praveen's Avatar
 
Praveen. C
Join Date: Mar 2009
Location: Bangalore
Posts: 251
Blog Entries: 6
Rep Power: 9
praveen is on a distinguished road
There is an O grid generator here

http://www.ae.gatech.edu/people/lsankar/AE6022/
praveen is offline   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
Air-Jet Vortex Generator, request for some papers ROOZBEH FLUENT 0 July 12, 2008 10:28
Air-Jet Vortex Generator, request for some papers ROOZBEH Main CFD Forum 0 July 12, 2008 10:27
3D NACA0012 with vortex generator Franny Main CFD Forum 3 April 10, 2007 18:09
grid generator Edwin Munts Main CFD Forum 2 December 4, 2000 15:54
Grid generator for structured grids Tore Myhrvold Main CFD Forum 5 January 21, 1999 09:09


All times are GMT -4. The time now is 16:07.