Abstract
A model for the analysis of the growth of fatigue cracks in residual stress fields is developed by integrating notch-strain analysis techniques with linear-elastic fracture-mechanics-based crack-growth analysis techniques. The method by which elastic-plastic response stress gradients are estimated is presented along with a discussion of the use of those gradients in a fatigue crack-growth analysis. The modeling of crack-growth acceleration and retardation effects and their use after the stress response calculations are discussed. And in conclusion, the results of a newly developed computer program, which incorporates the combined techniques, are compared with crack-growth data from an in-service U.S. Air Force aircraft.
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