An investigation of sheet-stiffener panels subjected to compression loads with particular reference to torsionally weak stiffeners

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Description

A total of 183 panel specimens of 24ST aluminum alloy with nominal thickness of 0.020, and 0.040 inch with extruded bulb-angle sections of 12 shapes spaced 4 and 5 inches as stiffeners were tested to obtain the buckling stress and the amplitude of the maximum wave when buckled. Bulb angles from 3 to 27 1/2 inches long were tested as pin-end columns. The experimental data are presented as stress-strain and column curves and in tabular form. Some comparisons with theoretical results are presented. Analytical methods are developed that make it possible for the designer to predict with reasonable accuracy the ... continued below

Creation Information

Dunn, Louis G February 1, 1940.

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This report is part of the collection entitled: National Advisory Committee for Aeronautics Collection and one other and was provided by UNT Libraries Government Documents Department to Digital Library, a digital repository hosted by the UNT Libraries. It has been viewed 133 times , with 4 in the last month . More information about this report can be viewed below.

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  • Main Title: An investigation of sheet-stiffener panels subjected to compression loads with particular reference to torsionally weak stiffeners
  • Series Title: NACA Technical Notes

Description

A total of 183 panel specimens of 24ST aluminum alloy with nominal thickness of 0.020, and 0.040 inch with extruded bulb-angle sections of 12 shapes spaced 4 and 5 inches as stiffeners were tested to obtain the buckling stress and the amplitude of the maximum wave when buckled. Bulb angles from 3 to 27 1/2 inches long were tested as pin-end columns. The experimental data are presented as stress-strain and column curves and in tabular form. Some comparisons with theoretical results are presented. Analytical methods are developed that make it possible for the designer to predict with reasonable accuracy the buckling stress and the maximum-wave amplitude of the sheet in stiffened-panel combinations. The scope of the tests was insufficient to formulate general design criteria but the results are presented as a guide for design and an indication of the type of theoretical and experimental work that is needed.

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Identifier

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  • : 93R10829
  • URL: http://hdl.handle.net/2060/19930081539 External Link
  • Report No.: NACA-TN-752
  • Center for AeroSpace Information Number: 19930081539
  • Archival Resource Key: ark:/67531/metadc54575

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National Advisory Committee for Aeronautics Collection

The National Advisory Committee for Aeronautics (NACA) was a U.S. federal agency founded on March 3, 1915 to undertake, promote, and institutionalize aeronautical research. On October 1, 1958 the agency was dissolved, and its assets and personnel transferred to the newly created National Aeronautics and Space Administration (NASA).

Technical Report Archive and Image Library

This selection of materials from the Technical Report Archive and Image Library (TRAIL) includes hard-to-find reports published by various government agencies. The technical publications contain reports, images, and technical descriptions of research performed for U.S. government agencies. Topics range from mining, desalination, and radiation to broader physics, biology, and chemistry studies. Some reports include maps, foldouts, blueprints, and other oversize materials.

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Creation Date

  • February 1, 1940

Added to The UNT Digital Library

  • Nov. 14, 2011, 10:28 p.m.

Description Last Updated

  • Feb. 2, 2017, 8:22 p.m.

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Citations, Rights, Re-Use

Dunn, Louis G. An investigation of sheet-stiffener panels subjected to compression loads with particular reference to torsionally weak stiffeners, report, February 1, 1940; (digital.library.unt.edu/ark:/67531/metadc54575/: accessed October 22, 2017), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.