Experimental Study of Deformation and of Effective Width in Axially Loaded Sheet-stringer Panels
This is a 1939 NACA technical report, issued by the National Advisory Committee for Aeronautics for aircraft engineers, on strain tests of axially loaded sheet-stringer panels such as aircraft fuselage or wing skins. The record is thin, so the pictures carry the description: they show laboratory test specimens mounted in a loading rig with rows of strain gauges, numbered figure captions, and grey photographic plates. A designer could take from them the look of riveted or fastened sheet-and-stringer structure and the plain documentary style of engineering photographs.
