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An aircraft wing component made from an aluminium alloy fractures at a stress of...
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An aircraft wing component made from an aluminium alloy fractures at a stress of 350 MPa when the maximum internal crack is of length 2a=2.5 mm. For the same component, made from the same alloy in the same condition (i.e., with the same fracture toughness), determine the stress level at which fracture will occur with a critical internal crack of length 2a=4.0 mm. Assume that Y=1.
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