Axial fatigue tests at zero mean stress of 24S-T aluminum-alloy sheet with and without a circular hole

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Description

Axial fatigue tests were made on 189 coupon specimens of 0.032-inch 24S-T aluminum-alloy sheet and a few supplementary specimens of 0.004-inch sheet. The mean load was zero. The specimens were restrained against lateral buckling by lubricated solid guides described in a previous report on this project. About two-thirds of the 0.032-inch specimens were plain coupons nominally free from stress raisers. The remainder contained a 0.1285-inch drilled hole at the center where the reduced section was 0.5 inch wide. S-N diagrams were obtained for cycles to failure between about 1000 and 10 to the 7th power cycles for the plain specimens ... continued below

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Brueggeman, W. C.; Mayer, M., Jr. & Smith, W. H. November 1944.

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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 160 times . More information about this report can be viewed below.

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  • Main Title: Axial fatigue tests at zero mean stress of 24S-T aluminum-alloy sheet with and without a circular hole
  • Series Title: NACA Technical Notes

Description

Axial fatigue tests were made on 189 coupon specimens of 0.032-inch 24S-T aluminum-alloy sheet and a few supplementary specimens of 0.004-inch sheet. The mean load was zero. The specimens were restrained against lateral buckling by lubricated solid guides described in a previous report on this project. About two-thirds of the 0.032-inch specimens were plain coupons nominally free from stress raisers. The remainder contained a 0.1285-inch drilled hole at the center where the reduced section was 0.5 inch wide. S-N diagrams were obtained for cycles to failure between about 1000 and 10 to the 7th power cycles for the plain specimens and 17 and 10 to the 7th power cycles for the drilled specimens. The fatigue stress concentration factor increased from about 1.08 for a stress amplitude causing failure at 0.25 cycles (static) to a maximum of 1.83 at 15,000 cycles and then decreased gradually. The graph for the drilled specimens showed less scatter than that for the plain specimens.

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  • Accession or Local Control No: 93R14279
  • URL: http://hdl.handle.net/2060/19930084989 External Link
  • Report No.: NACA-TN-955
  • Center for AeroSpace Information Number: 19930084989
  • Archival Resource Key: ark:/67531/metadc56844

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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

  • November 1944

Added to The UNT Digital Library

  • Nov. 17, 2011, 10:13 p.m.

Description Last Updated

  • April 9, 2018, 12:16 p.m.

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Brueggeman, W. C.; Mayer, M., Jr. & Smith, W. H. Axial fatigue tests at zero mean stress of 24S-T aluminum-alloy sheet with and without a circular hole, report, November 1944; (digital.library.unt.edu/ark:/67531/metadc56844/: accessed May 22, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.