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5) An aircraft component is fabricated from an aluminum alloy that has a fracture toughness of 35MPam It has been determined that fracture results

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5) An aircraft component is fabricated from an aluminum alloy that has a fracture toughness of 35MPam It has been determined that fracture results at a stress of 250MPa when the maximum (or critical) internal crack length is 2.0mm. For this same component and alloy, will fracture occur at a stress level of 325MPa when the maximum internal crack length is 1.0mm? Why or why not?

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