NACA profile coordinates

ken87 · March 9, 2011, 12:24

Hi, anyone know where to get a correct NACA 0012 coordinates? i have generate the coordinates by using JavaFoil software but when i run the simulation by using cosmofloworks i cannot get the same result (lift and drag coefficient against AOA) as the software provided....pls help...thanks..

tcarrigan · March 9, 2011, 18:38

The best option would be to write your own code. For symmetric NACA 4-series airfoils it's pretty straightforward. See the Wikipedia article below for the equations.

http://en.wikipedia.org/wiki/NACA_airfoil

Or you could always visit the UIUC airfoil database. There are tons of airfoil coordinates available.

http://www.ae.illinois.edu/m-selig/a..._database.html

March 9, 2011, 12:24	NACA profile coordinates	#1
ken87 New Member koay kheng kean Join Date: Mar 2011 Posts: 3 Rep Power: 14	Hi, anyone know where to get a correct NACA 0012 coordinates? i have generate the coordinates by using JavaFoil software but when i run the simulation by using cosmofloworks i cannot get the same result (lift and drag coefficient against AOA) as the software provided....pls help...thanks..

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March 9, 2011, 18:38		#2
tcarrigan Senior Member Travis Carrigan Join Date: Jul 2010 Location: Arlington, TX Posts: 161 Rep Power: 14	The best option would be to write your own code. For symmetric NACA 4-series airfoils it's pretty straightforward. See the Wikipedia article below for the equations. http://en.wikipedia.org/wiki/NACA_airfoil Or you could always visit the UIUC airfoil database. There are tons of airfoil coordinates available. http://www.ae.illinois.edu/m-selig/a..._database.html