Fatigue life prediction of smooth and circular-hole specimens based on equivalent initial flaw size

Life prediction and failure analysis are necessary and critical for the aeronautical structures. In this paper, a general method is proposed to predict the fatigue life of smooth and circular-hole specimens using the equivalent initial flaw size (EIFS) concept. The proposed methodology is based on a previously developed method. Fatigue limit and threshold stress intensity factor are used to predict the life of smooth specimens. Quarter-circular corner crack is assumed to predict the life of circular-hole specimens. Model predictions are compared with experimental data and a good agreement is observed between model predictions and experimental data.

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