THE mathematically exact determination of the stress distribution in a two‐spar skin‐covered wing is, in the present state of knowledge, an impossibility, and is in fact quite unnecessary, since only a reasonable approximation is required. The theory outlined in this article will, it is hoped, give a reasonable approximation for a reasonable amount of work, while taking into account as many variables as possible.
CitationDownload as .RIS
MCB UP Ltd
Copyright © 1941, MCB UP Limited