Full Scale Span Load Distribution on a Tapered Wing with Split Flaps of Various Spans
This is a 1937 NACA technical report, published by the National Advisory Committee for Aeronautics for aeronautical engineers and wind-tunnel researchers, on full-scale span load distribution across a tapered wing fitted with split flaps of several spans. The plates chart flap effectiveness curves against angle of attack and show a half-span tapered airfoil mounted in a wind tunnel test section with flap positions set at 67.9 and 38.3 percent span, so a designer would see plotted engineering data and laboratory photographs rather than decorative imagery.
