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Critical Compressive Stress for Outstanding FlangesA chart is presented for the values of the coefficient in the formula for the critical compressive stress at which buckling may be expected to occur in outstanding flanges. These flanges are flat rectangular plates supported along the Loaded edges, supported and elastically restrained along one unloaded edge, and free along the other unloaded edge. The mathematical derivations of the formulas required for the construction of the chart are given.
Document ID
20090014138
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Lundquist, Eugene E. (NASA Langley Research Center Hampton, VA, United States)
Stowell, Elbridge Z. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 7, 2013
Publication Date
April 1, 1941
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NACA-SR-188
Report Number: NACA-SR-188
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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