- #1

xzi86

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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.