Hi guys I was defining the parameters of my high wing plane (similar to Buttercup but cleaner). Starting with the initial guessing I saw the the leverarm for the horizontal tail is 2,7 the wing chord. Strojnik recommends not less than 3,5. Wittman seems to compensate that, using a fairly thick inverted clark Y tail airfoil. The tail surface is 26 sqft and maybe 23sqft netting for the fuselage tail (dont have the data in front of me). My standard calculated value is 23.6sqft, if I estimate a 0,4 additional lift coefficient with full flaps. Do you think he used Clark Y because of stability reasons or because of stol characteristics? Would you think it could make sense to put a horizontal stabiliser with an inverted GA37315 or with less pitch a NACA747315 How a re the stall characteristics of the NACA747315 I suppose the pitch in the tail thru the lever arm becomes an important criteria.