NACA-Report-887
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- December 4, 2015 Create Date
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National Advisory Committee for Aeronautics, Report - Critical Stress of Thin-Walled Cylinders in Axial Compression
Empirical design curces are presented for the critical stress of
thin-walled cylinders loaded in axial compression. These
curves are plotted in terms of the Inondimensional parameters of
small—deflection theory and are compared with theoretical curres
dericedjor the buckling of cylinders with simply supported and
clamped edges. An empirical equation is git-en for the bitch-ling
of cylinders having a length—radius ratio greater than about 0.75.
The test data obtained from carious sources follow the general
trend of the theoretical curve for cylinders with clamped edges,
agreeing closely with the theory in the case of short cylinders, but
falling considerably below the theoretical results for long
cylinders. The discrepancy in the case oflong cylinders increases
with increasing ralues of the ratio of radius to wall thickness.
Plotting curres for difierent values of this ratio reduces the
scatter in the test data and a certain degree of correlation with
theory is achieced. Advantage is taken of this correlation to
obtain estimated design curves for cylinders with simply sup-
ported edges, for which little experimental information. is
aoa-ilable.
Solutions to the problem of the determination of the critical
stress of thin—walled cylinders subjected to axial compression
have been presented by a large number of authors. South-
well, Timoshenko, Plugge, and numerous other authors
have obtained theoretical solutions by the use of the small-
defiection theory.
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