I have to analyze this airfoil at 4 degrees: "Consider a wing of span 15 feet. The root chord is 2.381 feet. The tip chord is 0.953 feet. The airfoils used are NACA 65-210 sections, which have a zeo-lift angle of –1.2 degrees. The wing is untwisted."
Now I've got a MATLAB code to analyze this...