NACA0012 gird generator

Prashanth · April 26, 2009, 23:55

I would like to know where I will be able to find a grid generator code for the NACA 0012 airfoil. Thank you...

Prashanth

harishg · April 26, 2009, 23:59

I guess you need to be specific on what kind of grid you need ?

praveen · April 27, 2009, 00:54

For unstructured grids, look at bamg, gmsh, triangle (shewchuck), delaundo.

Dont know any for structured grids.

Prashanth · April 27, 2009, 01:41

I was looking for structured O grids

technophobe · April 27, 2009, 06:34

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

praveen · May 1, 2009, 04:20

There is an O grid generator here

http://www.ae.gatech.edu/people/lsankar/AE6022/

April 26, 2009, 23:55	NACA0012 gird generator	#1
Prashanth New Member Prashanth Join Date: Mar 2009 Posts: 3 Rep Power: 17	I would like to know where I will be able to find a grid generator code for the NACA 0012 airfoil. Thank you... Prashanth

April 27, 2009, 06:34		#5
technophobe New Member Anon Join Date: Apr 2009 Posts: 13 Blog Entries: 1 Rep Power: 17	There's an analytical function for the thickness of a NACA00XX airfoil. The upper surface of the airfoil is given by: Code: upper(I) = thick5.(0.2969sqrt(x(I)) - 0.1260x(I) - 0.3516x(I)^2 + 0.2843x(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

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April 26, 2009, 23:59		#2
harishg Senior Member N/A Join Date: Mar 2009 Posts: 189 Rep Power: 17	I guess you need to be specific on what kind of grid you need ?

April 27, 2009, 00:54		#3
praveen Super Moderator Praveen. C Join Date: Mar 2009 Location: Bangalore Posts: 342 Blog Entries: 6 Rep Power: 18	For unstructured grids, look at bamg, gmsh, triangle (shewchuck), delaundo. Dont know any for structured grids.

April 27, 2009, 01:41		#4
Prashanth New Member Prashanth Join Date: Mar 2009 Posts: 3 Rep Power: 17	I was looking for structured O grids

May 1, 2009, 04:20		#6
praveen Super Moderator Praveen. C Join Date: Mar 2009 Location: Bangalore Posts: 342 Blog Entries: 6 Rep Power: 18	There is an O grid generator here http://www.ae.gatech.edu/people/lsankar/AE6022/