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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| Main Author | |
|---|---|
| Corporate Authors | , |
| Other Authors | , |
| Format | Electronic eBook |
| Language | English |
| Published |
Langley Field, VA :
Langley Memorial Aeronautical Laboratory,
1943.
|
| Series | NACA WR ;
L-368 |
| Subjects | |
| Online Access | Full text |
| ISBN | 9781680156485 1680156489 |
| Physical Description | 1 online resource (46 pages, [32] leaves) : illustrations |