Hi SteveH,

Does the equation you are experimenting with work for the NACA 65A009 airfoil? If so, could you share the equation with me. I would be interesting in trying it out. It could be a better way of doing things depending upon how it deals with the leading and trailing edge. I have modeled a bunch of blades using the data file I have, and haven't had any issues. MoI is easily able to curve fit the data from the NACA file. Creating a very smooth airfoil. But I'm always interested in a better way to do things. Perhaps your method will be better.

Thanks,

Anthony