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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...
| Cote: | Libro Electrónico |
|---|---|
| Auteur principal: | |
| Collectivités auteurs: | , |
| Autres auteurs: | , |
| Format: | Électronique eBook |
| Langue: | Inglés |
| Publié: |
Langley Field, VA :
Langley Memorial Aeronautical Laboratory,
1943.
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| Collection: | NACA WR ;
L-368 |
| Sujets: | |
| Accès en ligne: | Texto completo |