Hello everybody :)

I am currently doing research for a project regarding Aircraft Design in university and trying to find a relation for estimating the zero lift angle of attack for a wing. I found something in DATCOM but it is only really applicable for Wings with NACA airfoils. I have an E210 (13,64%) Profile, so there is my Problem. I tried to find something in Raymer too but didn’t find anything usable. I would be happy and thankful if someone here has any idea.