Pressure-distribution investigation of an N.A.C.A. 0009 airfoil with a 50-percent-chord plain flap and three tabs
This is a 1939 NACA technical report, issued by the National Advisory Committee for Aeronautics for aeronautical engineers and researchers, presenting wind-tunnel pressure measurements on a symmetric airfoil with flap and tab deflections. The pages show multi-panel line graphs of flap-section normal force and hinge-moment coefficients against flap deflection, plus a chordwise pressure-distribution plot with inverted axes and an airfoil profile sketch at top. A designer might borrow the clean grid-and-curve plotting style and the sweeping descending line families for abstract technical graphics.
