General Instability of Stiffened Cylinders Page: 3 of 27
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NACA TN 4237
cylinders, for which there is no boundary influence. Details of bound-
ary conditions for the different loadings are discussed in the pertinent
The investigation is restricted to elastic buckling. Linear theory
is used in all cases. Section properties of the frames, stiffeners, and
sheet are nominal, as depicted in figure 1. The actual properties to
be used in design are discussed in part VI of the Handbook of Structural
Stability (ref. 5). This handbook contains a critical review of the
field of general instability. It presents comparisons of theory and test
data which delineate the utility both of the theoretical results presented
herein and of other theories which do not employ the orthotropic-shell
A summary of the results of the investigations appears in table 1.
Short discussions of the analyses of each case investigated are also
included. The derivations of the general instability stresses are pre-
sented in appendixes A to D.
This investigation was conducted at New York University under the
sponsorship and with the financial assistance of the National Advisory
Committee for Aeronautics.
Af distributed area of frame including effective sheet, in., A/d
Af area of frame including effective sheet, sq in.
As distributed area of stiffener including effective sheet, in., A/b
As area of stiffener including effective sheet, sq in.
b stiffener spacing, in.
d frame spacing, in.
E Young's modulus, psi
F Airy's stress function
G shear modulus, psi
If distributed bending moment of inertia of frame, if/d, cu in.
Is distributed bending moment of inertia of stiffener, 1I/b, cu in.
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Becker, Herbert. General Instability of Stiffened Cylinders, report, July 1958; (https://digital.library.unt.edu/ark:/67531/metadc57302/m1/3/: accessed May 22, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.