Fracture and Fatigue Crack Growth Behavior of Surface Flaws and Flaws Originating at Fastener Holes, Volume II. Tabulated Data.
Final technical rept. Jun 72-Sep 73,
BOEING AEROSPACE CO SEATTLE WASH
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The report contains tabulations of raw fatigue crack growth rate data generated during tests of surface flaws and flaws originating at fastener holes. The surface flaw tests involved a number of variables including alloy, flaw shape, initial flaw depth, loading profile, and stress ratio. Three alloys were tested including 2219-T851 aluminum, 9Ni-4Co-0.2C steel 190-210 ksi, and 6Al-4V standard ELI beta annealed titanium, all in plate form. Most specimens contained two or three flaws having initial depth-to-length ratios of 0.15, 0.30, or 0.45, and initial depth-to-thickness ratios ranging from 20 to 80 percent of the specimen thickness. Three different loading profiles were investigated including constant cyclic load, periodic overload, and spectrum loadings.
- Metallurgy and Metallography