Bryan, Just out of curiosity how do you calculate the MAC? I have been using the NACA website however I can get 2 different answers depending on whether the calculation is based on the actual physical wing panel dimensions or the dimensions with the wing planform projected to the fuse centre line. On my Arbalest wings the CoG is 26.5% based on the actual panel dimensions or 29% if I project to the fuse C/L. My understanding is that wing area is usually based on projection to the fuse C/L so just wondered if that convention applies to MAC as well.
Thanks Bill