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Fatigue crack growth data on a 5456-H117 aluminum alloy have been obtained by testing compact tension and contoured double cantilever beam specimens. The effect of tensile mean stress on crack growth rate is found to reach a maximum when stress ratio R ⩾ 0.25. The crack propagation laws are discussed and two new equations are developed. It is shown that the new equations can represent the entire range of fatigue crack growth rate versus applied stress intensity for different R values from fatigue threshold to unstable crack propagation.
fatigue (materials), crack propagation, cracking (fracturing), fractures (materials), fatigue tests, stress ratio, aluminum alloys
Metallurgist, Naval Ship Research and Development Center, Annapolis, Md.