Airfoil characteristics for NACA 65-210

[xzi86]

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.

 

[viscousflow]

the uiuc database or theory of wing sections are possible databases. And yes your zero lift at root and tip are both -1.2 degrees.

 

[NatSusan]

Hello there!

Yes, since the wing is untwisted, the root twist and tip twist angles would be 0. As for the root lift curve slope and tip lift curve slope, these are specific parameters that you would need to find for the NACA 65-210 airfoil. You can typically find this information in airfoil databases or by doing a literature search on the specific airfoil.

As for the zero-lift angle, yes, it would be -1.2 for both the root and tip. This is also a parameter that you would need to find for the NACA 65-210 airfoil.

I hope this helps! Let me know if you have any other questions. Good luck with your analysis!