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Statistical investigation of fatigue crack initiation and growth around chamfered rivet holes in Alclad 2024 T3 as affected by corrosionIn panel specimens with rivet holes cracks initiate in the blunted knife edge of the chamfered rivet hole and propagate inward as well as along the hole. The fatigue lifetime to dominant crack information was defined as the number of cycles, N500 micrometer, to formation of a 500 micrometer long crack. Statistical data on N500 micrometer and on crack propagation after N500 micrometer were obtained for a large number of uncorroded specimens and specimens corroded in an ASTM B 117 salt spray. Considerable variation in N500 micrometer and crack propagation behavior was observed from specimen to specimen of the same nominal geometry with chamfered rivet holes increased the probability for both early formation and later formation of a propagating 500 micrometer fatigue crack. The growth of fatigue cracks after 500 micrometer size was little affected by prior salt spray.
Document ID
19950008058
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Fadragas, M. I.
(Northwestern Univ. Evanston, IL, United States)
Fine, M. E.
(Northwestern Univ. Evanston, IL, United States)
Moran, B.
(Northwestern Univ. Evanston, IL, United States)
Date Acquired
September 6, 2013
Publication Date
September 1, 1994
Publication Information
Publication: NASA. Langley Research Center, FAA(NASA International Symposium on Advanced Structural Integrity Methods for Airframe Durability and Damage Tolerance
Subject Category
Structural Mechanics
Accession Number
95N14472
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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