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Hello rovie..any help with suggested formulas would be appreciated. davidl@brazosnet.com

Thanks, Buzz, for the reply. I'm using a low RN of 700,000 and have ran the airfoil through a polar program I found and then made some comparisons to old NACA tests. The airfoil is very similar to the NACA 6412. I'm in the midst now of wrassling with induced drag concepts, trying to take old...

I'm designing, building, a strange low/slow single place fun cow pasture airplane of dubious proportions with dubious design skills. It is a wire braced triplane similar in configuration to the old Sopwith tripe of WWI. An old NACA report by Munk has the Cl and Cd plots for a specific Gap/Chord...

I'm near complete on the design of a small triplane of WWI type configuration. Researched old naca poop, etc.etc...figure the moments at various speeds, developed tail loads... But I'm unclear in determining a maximum aft CG position for stall or near static conditions with stall/spin recovery...

I'm near complete on the design of a small triplane of WWI type configuration. Researched old naca poop, etc.etc...figure the moments at various speeds, developed tail loads... But I'm unclear in determining a maximum aft CG position for stall or near static conditions with stall/spin recovery...

Butela..you have succeeded in making me anxious. Try a 20' pole (6.1 meters) or just enough to let me know your concerns. No liability in expressing a concern. Dave

I appreciate the reply Ishvaaag.. I was thinking of maybe multiple wraps of carbon fibre tow along the same path (repetitive wraps)for depth, with epoxy resin matrix and bonded directly to the wood surface. In my mind if these wraps are near vertical and spaced 2-3" apart they may not...

I have constructed an experimental aircraft spar of wood and pultruded carbon fibre. The wood core is 1/2" by 1" and two flat rods (0.092"*0.220") are epoxied flat side down, side by side, on both top and bottom wood surfaces. The spar is lightly loaded in vertical shear...