Stresses around rectangular cut-outs in skin-stringer panels under axial loads - II

Cut-outs in wings or fuselages produce stress concentrations that present a serious problem to the stress analyst. As a partial solution of the general problem, this paper presents formulas for calculating the stress distribution around rectangular cut-outs in axially loaded panels. The formulas are...

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Bibliographic Details
Main Author Kuhn, Paul
Corporate Authors Langley Aeronautical Laboratory, United States. National Advisory Committee for Aeronautics
Other Authors Duberg, John E. 1917-, Diskin, Simon H.
Format Electronic eBook
LanguageEnglish
Published Langley Field, VA : Langley Memorial Aeronautical Laboratory, 1943.
SeriesNACA WR ; L-368
Subjects
Online AccessFull text
ISBN9781680156485
1680156489
Physical Description1 online resource (46 pages, [32] leaves) : illustrations

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