Characterization of fatigue behavior of AA2024‐T351 aluminum alloy

Abstract The paper aims to investigate the fatigue behavior of widely used AA2024‐T351 aluminum alloy in aircraft industry. An experimental program was conducted study life and damage under symmetrical tensile‐compressive loading. Cyclic tests low cycle regime were performed fully reversed total strain amplitudes from 0.6% 1.2%. exhibited cyclic hardening until failure. Symmetric high also parameters for estimation using Manson–Coffin–Basquin model identified. Elasto‐plastic analyzed through stress–strain hysteresis loops, evaluating kinematic isotropic hardenings. Kinematic found be amplitude dependent, unlike hardening. evolution variable with percentage could described by an exponential law. Fractography investigations showed crack initiation at specimen border quasi‐cleavage then propagating striation before ductile fracture.