Al-Rubaie, Kassim Shamil FadhilBarroso, Emerson Kellem LanaGodefroid, Leonardo Barbosa2015-05-192015-05-192006AL-RUBAIE, K. S.; BARROSO, E. K. L.; GODEFROID, L. B. Fatigue crack growth analysis of pre-strained 7475–T7351 aluminum alloy. International Journal of Fatigue, v. 28, n.8, p. 934-942, 2006. Disponível em: <http://www.sciencedirect.com/science/article/pii/S0142112305002847>. Acesso em: 09 abr. 2015.0142-1123http://www.repositorio.ufop.br/handle/123456789/5401Aluminum alloys are widely used in aeronautical design due to their good mechanical properties and low densities. Among these alloys, 7475 (Al–Zn–Mg–Cu), modified from 7075, is successfully used due to strength similar to that of 7075 and superior fracture toughness. In this study, strips of 7475–T7351 were subjected to two tensile pre-strain levels of 3 and 5%. Using compact tension C(T) specimens, fatigue crack growth (FCG) tests were conducted in air under constant amplitude loading at a stress ratio of 0.5. Three FCG rate models, namely Collipriest, Priddle, and modified Forman were examined. The results showed that both fracture toughness and FCG resistance decreased with an increase in the prestrain level. Both Collipriest and Priddle models fit the FCG rate data in a similar fashion. However, the Priddle model provided a better fit than Collipriest. The modified Forman model provided the best fit to the FCG rate data as compared with the other two models. The modified Forman model used to fit other unpublished FCG data and its response was also superior to the others. Therefore, this model may be suggested for use in critical applications, such as aeronautical structural design.en-USPre-strainFatigue crack growth rateStatistical analysisModelingArtigo publicado em periodicoO periódico International Journal of Fatigue concede permissão para depósito deste artigo no Repositório Institucional da UFOP. Número da licença: 3624210855661.https://doi.org/10.1016/j.ijfatigue.2005.09.008