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Fatigue crack growth life predictions were made for a bolthole specimen geometry as part of an ASTM round robin. Constant amplitude crack growth rate data for 7075-T651 aluminum generated with standard specimens were supplied. A hyperbolic sine model was used to describe these data. Life predictions were made for the bolthole geometry with several maximum stress levels, stress ratios, and initial flaw sizes. Verification tests conducted by the Air Force for a bolthole specimen under these same conditions were used to evaluate the predictive capability of the life prediction model. Very good correlation was observed between the predictions and the test results.
Assistant professorASTM member, Florida Atlantic University, Boca Raton, FL
Stock #: JTE10733J