I am trying to experiment in solidworks and find the cl of NACA 4412 at 0° at 200e3 Reynolds number. It says at airfoil tools that it is around .5 at 0 degrees, but when I do it its around .007 at max here are my steps. I just want to know were I made the mistake/s.

I got the airfoil xyz curve from airfoil tools by importing them into excel tweaking the data to be spaced between and adding 0's on the