An aircraft component is fabricated from an aluminum alloy that has a plane strain fracture toughness of
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An aircraft component is fabricated from an aluminum alloy that has a plane strain fracture toughness of 40 MPa (36.4 ksi). It has been determined that fracture results at a stress of 300 MPa (43,500 psi) when the maximum (or critical) internal crack length is 4.0 mm (0.16 in.). For this same component and alloy, will fracture occur at a stress level of 260 MPa (38,000 psi) when the maximum internal crack length is 6.0 mm (0.24 in.)? Why or why not?
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Related Book For 
Materials Science and Engineering An Introduction
ISBN: 978-1118324578
9th edition
Authors: William D. Callister Jr., David G. Rethwisch
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