Hi,
Â
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]
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
Â