How to model and aerofoil of given NACA series in Catia?

Can we use any mathematical equation to generate the profile in Catia ?

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You dont want any mathematical equation to generate the airfoil profile. You just need the coordinates of the airfoil profile.

http://www.mh-aerotools.de/airfoils/javafoil.htm

from this website you can get the coordinates of the airfoil which you want.
All you have to do is to select the NACA family and select the preferred thickness, camber and camber location. Thats it.

 
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