Bending tests of metal monocoque fuselage construction

Ralph W. Mossman, Russell G. Robinson
naca-tn-357
Nov 1930


This thesis presents a study of the bending stress in smooth skin, aluminum alloy, true monocoque fuselage sections of varying ratio of diameters to thickness. The test specimens - circular, thin-walled cylinder were loaded to give a large bending stress in proportion to the shearing stress, in order to represent the critical section of a fuselage.

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