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An aircraft component is fabricated from an aluminum alloy that has a plane strain fracture toughness of 3 9 MPa m 2 . It has
An aircraft component is fabricated from an aluminum alloy that has a plane strain fracture toughness of MPa It has been determined that fracture results at a stress of MPa when the maximum or critical internal crack length is
a Determine the value of for this same component and alloy at a stress level of MPa when the maximum internal crack length is
MPa
b Under these circumstances will the component fail?
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