im not trying let somebody doit for me im just trying get some more info on actual problem i have all loads ,all bending moments and shear stress at each point figured but after reading alex strojnik books like with other books lot a problems they did not say what formula for example (m=pl/4 just example) you can use to determine cross section for spar my wing design is spar in one piece i asked designer who does all the analysis but for that price i can buy a new airplane,when i build the wings im goint to load it with 4 g' of actual gross weight to find out if its strong enough,i think they were lot of planes build in early 60',70' without any stress analysis and they are proven design,so no one here sad go a head and do it ,im doin it if i dont build it ill never find out if the plane i draw on piece of paper will fly it always will be just dream