nik.kruhmin
Well-Known Member
I'm plotting out my build of my Sonerai I wings. The plans spec 2024-t3 alclad for everything. I'd like to use 6061-t6, for cost, weight savings and corrosion resistance. I'd like to avoid any coatings, which I believe I can get away with using 6061 and being in SoCal. It does have a 11% lower tensile yield stress however...
Now there's been a few iterations of the internal wing design as applied to the II and IILS versions of the Sonerai, which originally just had longer I wings. The spar mods were done initially to increase the strength of the II and IILS. These mods are often applied to the I for an even larger safety factor. On the II the spar mod bumped the g rating to 150% of the amended value. Is my thinking that applying this using 6061-t6 would net a spar that is 130% stronger before failure than the original flawed? Am I making it too simple? How critical are the ribs and skin? Their thicknesses throughout the Sonerai evolution seem to have been more driven by manufacturability than anything else.
Now there's been a few iterations of the internal wing design as applied to the II and IILS versions of the Sonerai, which originally just had longer I wings. The spar mods were done initially to increase the strength of the II and IILS. These mods are often applied to the I for an even larger safety factor. On the II the spar mod bumped the g rating to 150% of the amended value. Is my thinking that applying this using 6061-t6 would net a spar that is 130% stronger before failure than the original flawed? Am I making it too simple? How critical are the ribs and skin? Their thicknesses throughout the Sonerai evolution seem to have been more driven by manufacturability than anything else.
