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Engineering, 17.12.2019 20:31 ineedtopeebeforethec

Some aircraft component is fabricated from an aluminum alloy that has a plane strain fracture toughness
of 35 mpa m (31.9 ksi in. ). it has been determined that fracture results at a stress of 250 mpa (36,250 psi)
when the maximum (or critical) internal crack length is 2.0 mm (0.08 for this same component and alloy, will
fracture occur at a stress level of 325 mpa (47,125 psi) when the maximum internal crack length is 1.0 mm (0.04
why or why not?

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