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suppose that a wing component on an aircraft is fabricated from an aluminum alloy that has a plane strain fracture toughness of 26 MPa.

suppose that a wing component on an aircraft is fabricated from an aluminum alloy that has a plane strain fracture toughness of 26 MPa. It has been determined that fracture results at a stress of 112 MPa when the maximum internal crack length is 8.6 mm long. For this same component and alloy, compute the stress level at which fracture will occur for a critical internal crack length of 6.0mm

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