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Effect of service usage on tensile, fatigue, and fracture properties of 7075-T6 and 7178-T6 aluminum alloysA study has been made to determine the effects of extensive service usage on some basic material properties of 7075-T6 and 7178-T6 aluminum alloy materials. The effects of service usage were determined by comparing material properties for new material (generally obtained from the literature) with those for material cut from the center wing box of a C-130B transport airplane with 6385 flight-hours of service. The properties investigated were notched and unnotched fatigue strengths, fatigue-crack-growth rate, fracture toughness, and tensile properties. For the properties investigated and the parameter ranges considered (crack length, stress ratio, etc.), the results obtained showed no significant difference between service and new materials.
Document ID
19750007702
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Everett, R. A., Jr. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
February 1, 1975
Subject Category
Metallic Materials
Report/Patent Number
L-9952
NASA-TM-X-3165
Accession Number
75N15774
Funding Number(s)
PROJECT: RTOP 501-22-02-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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