dc.contributor.author |
W. S. Hemp |
en_US |
dc.contributor.author |
K. H. Griffin |
en_US |
dc.date.accessioned |
2014-10-21T15:52:06Z |
|
dc.date.available |
2014-10-21T15:52:06Z |
|
dc.date.issued |
1949 |
en_US |
dc.identifier.other |
ARC/R&M-2635 |
en_US |
dc.identifier.uri |
https://reports.aerade.cranfield.ac.uk/handle/1826.2/3174 |
|
dc.description.abstract |
A simplified panel model is described, together with a number of assumptions about the mode of its buckling. The approach to the calculation of the buckling stress is by splitting the panel into a number of flat plates and treating these by the ordinary plate theory. Use of the boundary conditions between these plates leads to a relation between the buckling stress and the variables of the panel geometry. The results thus obtained are compared with two sets of recent experimental work; and an appendix is included to show the effect of initial panel irregularities on the experimental determination of buckling stresses. |
en_US |
dc.relation.ispartofseries |
Aeronautical Research Council Reports & Memoranda |
en_US |
dc.title |
The buckling in compression of panels with square top-hat section stringers |
en_US |