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 airfoil. It requires the following inputs: input root chord = 2.381 input tip chord = 0.953 input span = 15 input Root twist angle in degrees = 0 input tip twist angle in degrees = 0 input root lift curve slope in units/ radian = ?? input lift curve slope at the tip, in units/radian = ?? input angle of attack, in degrees = 4 input zero-lift angle at the root = -1.2 input zero lift angle at the tip = -1.2 Since the wing is untwisted, root twist and tip twist would be 0 right? I don't know how to find root lift curve slope at the root and tip. Is this information I'm supposed to find specifically for the NACA 65-210? Where would I find this information? Also zero-lift angle would be -1.2 for root and tip right? Thanks a lot for helping.