- #1
xzi86
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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.
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.