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A round-robin analysis was conducted by ASTM Task Group E24.06.01 on Application of Fracture Data to Life Prediction to predict the fatigue crack growth in 2219-T851 aluminum center-cracked-tension (CCT) specimens subjected to flight loadings in random cycle-by-cycle format. Baseline data furnished to each participant of the round-robin analysis are described. These data consisted of constant amplitude crack growth data, specimen dimensions, initial crack sizes, and test spectrum tables. Analytical predictions and their correlation to test data are summarized.
fatigue crack growth, random flight loadings, 2219-T851 aluminum, center cracked tension specimen, fatigue life predictions
Program manager/technical staff, North,