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Potential Use of Work Hardening Aluminum Alloy X5090 Sheet in Civil Aircraft
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English
Abstract
Aluminum alloy X5090, containing a nominal 7% magnesium, is a recent introduction to the moderately high-strength class of alloys, but it represents a change from a heat-treatable to a work-hardening type. Advantages of low density, corrosion resistance, fatigue, and fracture toughness are stressed. Mechanical, physical, and corrosion properties are presented, with emphasis on problems related to stress-corrosion and formability, and their solutions. Potential uses are discussed.
Authors
Citation
Graham, D., Sperry, P., and Winter, J., "Potential Use of Work Hardening Aluminum Alloy X5090 Sheet in Civil Aircraft," SAE Technical Paper 740398, 1974, https://doi.org/10.4271/740398.Also In
References
- “Mechanical-Property Data X5090 Aluminum -H38 Sheet.” Air Force Materials Laboratory, Wright-Patterson Air Force Base Ohio October 1970
- “Specifications for Aluminum Structures.” New York Aluminum Association Second 1971
- “Alcoa Structural Handbook.” Pittsburgh Aluminum Company of America 1960
- Nelson F. G. Kaufman J. G. “Fracture Toughness of Plain and Welded 3-Inch Thick Aluminum Alloy Plate.” Special Technical Publication 536 ASTM 1973
- Booth F. F. Godard H. P. “An Anodic Stress-Corrosion Test for Aluminum-Magnesium Alloys.” First International Congress on Metallic Corrosion London, Butterworths 1961
- “Properties and Selection of Materials.” Metals Handbook I 8th Metals Park, Ohio American Society for Metals 1961