# Separation Point over a NACA 0012

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 March 22, 2007, 03:02 Separation Point over a NACA 0012 #1 Franny Guest   Posts: n/a Hi all, I was wondering if anyone could help me with this problem.I m try to show that is possible to delay the separation over a NACA 0012 using vortex genereators into the sub-boundary layer.I ve done 4 2-D simulations at 4 different a0a in CFX.Now,as the separation happen,I need to determine the distance between the leading edge and the separation point to calculate the geometric dimension of the VGs.Anyone has a clue of how this can be done? After plotting streamlines and velocity vectors,I dont know how to do.Maybe plot the velocity on the polyline and export in Excel and see where the velocity goes down....It looks too rough as definition of an exect point. If you have an idea, please let me know it. Thanks for now. Franny

 March 22, 2007, 04:26 Re: Separation Point over a NACA 0012 #2 Jonas Larsson Guest   Posts: n/a When looking at separating airfoils I usually plot surface skin friction in the streamwise direction in order to specify where it is close to zero and the separated region begins.

 March 22, 2007, 04:33 Re: Separation Point over a NACA 0012 #3 Charles Guest   Posts: n/a Plot the shear stress

 March 22, 2007, 15:49 Re: Separation Point over a NACA 0012 #4 Franny Guest   Posts: n/a Thank you very much guys. Franny

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