Engineering, 22.10.2020 16:01 izaiahfieods
A wing component on an aircraft is fabricated from an aluminum alloy that has a plane strain fracture toughness of 28 . It has been determined that fracture results at a stress of 120 when the maximum internal crack length is 9.2 . For this same component and alloy, compute the stress level at which fracture will occur for a critical internal crack length of 6.6 .(Enter your answer to three significant figures.)
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