Pressure distributions over a retracted leading-edge slat on a 40 degree sweptback wing at Mach numbers up to 0.9
This NACA technical memorandum from 1951, issued by the National Advisory Committee for Aeronautics in the United States, reports wind-tunnel pressure measurements for engineers and aerodynamicists studying a 40 degree sweptback wing. The pictures are plain black-and-white engineering graphs and a wing plan sketch: pressure coefficient curves plotted against chord position, lift coefficient against angle of attack across Mach numbers, and dimensioned drawings of the wing outline with its airfoil section. A designer could take from them the clean line-graph style and the sweptback planform silhouette.
