Stresses around rectangular cut-outs in skin-stringer panels under axial loads - II
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Author
Contributions
- Duberg, John E. (John Edward), 1917- - Contributor
- Diskin, Simon H. - Contributor
- Langley Aeronautical Laboratory - Contributor
- United States. National Advisory Committee for Aeronautics - Contributor
Publication
1943 - Langley Memorial Aeronautical Laboratory, Langley Field, VA, Virginia
Language
English
Word Count
11,500 words, Guess
Page Count
46 pages
Identifiers
- ISBN-101680156489
- ISBN-139781680156485
- OCLC Control Number857368754
- Open LibraryOL44477501M
Classifications
- DDC620.11292
- LCCTA404.8
Alternate Titles
- NACA wartime reports
Description
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 derived by means of the substitute-stringer method of shear-lag analysis. In a previous paper published under the same title as the present one, the analysis had been based on a substitute structure containing only two stringers. The present solution is based on a substitute structure containing three stringers and is more complete as well as more accurate than the previous one. It was found that the results could be used to improve the accuracy of the previous solution without appreciably reducing the speed of calculation. Details are given of the three-stringer solution as well as of the modified two-stringer solution.
Subjects
Series Statement
- NACA WR -- L-368
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