Pressure Distribution Tests on PW-9 Wing Models from -18 Degree Through 90 Degree Angle of Attack
A 1929 NASA technical report presenting wind-tunnel pressure distribution tests on monoplane and biplane wing models of the PW-9 fighter, covering angles of attack from -18 to 90 degrees. The pictures are dense engineering line charts and grids plotting section loads and normal force coefficients against percent semispan for each wing and angle, with solid lines for monoplane and dashed lines for biplane, useful to a designer as a reference for how loading shifts along a wing as incidence rises.
