Meshing in pointwise ( NACA 0012) -- CFD Online Discussion Forums

April 10, 2013, 20:08	Meshing in pointwise ( NACA 0012)	#1
uzairm New Member Uzair Mansuri Join Date: Apr 2013 Posts: 2 Rep Power: 0	Hey, I have a final project for my CFD course,and I want help regarding meshing NACA 0012 Airfoil in pointwise,i know how to use the software, I just need help regarding creating the perfect grid,so I can resolve the perfect Cd value. 1)I can use upto 50,000 points 2)I can use structured mesh. 3)Distance of domain from airfoil I can use is 50 chords.

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 Forum Rules

Similar Threads
Thread	Thread Starter	Forum	Replies	Last Post
Data for NACA 0012	Muntazir	Main CFD Forum	1	March 28, 2023 02:59
How to import NACA 0012 Profile in Gridgen	maplepink	Main CFD Forum	17	May 7, 2013 14:01
NACA 0012 Case Will Not Converge	dancfd	OpenFOAM Running, Solving & CFD	6	November 14, 2011 20:09
Problems with flat plate and NACA 0012 Lift/Force	Harly	FLUENT	0	June 18, 2007 11:02
NACA 0012 simulation results	Luis	FLUENT	3	February 15, 2006 12:42

All times are GMT -4. The time now is 22:04.