General Instability of Stiffened Cylinders Page: 4 of 27
This report is part of the collection entitled: National Advisory Committee for Aeronautics Collection and was provided to Digital Library by the UNT Libraries Government Documents Department.
The following text was automatically extracted from the image on this page using optical character recognition software:
NACA TN 4237 3
If bending moment of inertia of frame including effective sheet, in.
Is bending moment of inertia of stiffener including effective sheet,
J = 3f + Js
Jf distributed torsional moment of inertia of frame, f/d, cu in.
Js distributed torsional moment of inertia of stiffener, is/b.
Jf torsional moment of inertia of stiffener, in.4
J, torsional moment of inertia of frame, in.4
ky buckling coefficient for unstiffened circular cylinder under
kp buckling coefficient for unstiffened circular cylinder under
L length of cylinder, in.
Mx = EIs -2
M XY=1 G J 2
xy 2 8x (y
My = EIfy -y
m,n parameters of axial and circumferential buckle wave lengths
M = ada
Nx axial normal load on cylinder, ots, Ib/in.
N shear load on cylinder, it, lb/in.
N circumferential normal load on cylinder, ytf, Ib/in.
Here’s what’s next.
This report can be searched. Note: Results may vary based on the legibility of text within the document.
Tools / Downloads
Get a copy of this page or view the extracted text.
Citing and Sharing
Basic information for referencing this web page. We also provide extended guidance on usage rights, references, copying or embedding.
Reference the current page of this Report.
Becker, Herbert. General Instability of Stiffened Cylinders, report, July 1958; (https://digital.library.unt.edu/ark:/67531/metadc57302/m1/4/: accessed May 25, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.