Engineering
Engineering, 05.11.2020 18:50, LaDariusL33

An aircraft component is fabricated from an aluminum alloy that has a plane strain fracture toughness of 36 . It has been determined that fracture results at a stress of 225 MPa when the maximum (or critical) internal crack length is 2.44 mm. Determine the value of for this same component and alloy at a stress level of 337 MPa when the maximum internal crack length is 1.22 mm.

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