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Sustained-load tests of partially cracked 0.220-in. solution-treated and aged Ti-6Al-4VLoad and fatigue tests on titanium aluminum vanadium alloy sheet metal
Document ID
19670014146
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Rawe, R. A. (Douglas Aircraft Co., Inc. Santa Monica, CA, United States)
Date Acquired
August 3, 2013
Publication Date
January 3, 1967
Subject Category
Materials, Metallic
Report/Patent Number
NASA-CR-83076
DAC-59532
Report Number: NASA-CR-83076
Report Number: DAC-59532
Accession Number
67N23475
Funding Number(s)
CONTRACT_GRANT: NAS7-101
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
FATIGUE TEST
ALUMINUM ALLOY
SHEET METAL
VANADIUM ALLOY
TITANIUM ALLOY
LOAD TEST

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