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Equations - Nacra curve


Phil-W

Hi,

 

I am trying to use the custom option in DSM to create an Airfoil section based on the NACRA profile, currently with no luck ( lack of experience and knowlege hopefully).  The actual equation from Wikipedia is:

yt = 5t[0.2969Sqrtx - 0.1260x - 0.3516x2 + 0.2843x3 - 0.1015x4]

Nacra Airfoil @ Wiki

My attemp in the equation tool is:

5[t][(0.2969*Sqrt[t])-(0.1260*[t])-(0.3516*Pow([t],2))+(0.2843*Pow([t],3))-(0.1015*Pow([t],4))]

All I get is a straight line :(

Idealy I would want the airfoil section to be 300mm wide from which i can make a surface.

Many thanks

 

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