Solution-Gradual crack growth of a preexisting crack

Gradual crack growth of a preexisting crack

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Reference no: EM13887295

A wing panel of a supersonic aircraft is made from a titanium alloy that has yield strength 1035 MPa and toughness KIc = 55 MPa√m. It is 3.0 mm thick, 2.40 m long, and 2.40 m wide. In service it is subjected to a cyclic stress of ±700 MPa, which is not enough to cause yielding but does cause gradual crack growth of a preexisting crack normal to the loading direction at the edge of the panel. Assume that the crack is initially 0.5 mm long and grows at a constant rate of da/dN = 120.

Reference no: EM13887295

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Gradual crack growth of a preexisting crack

Reference no: EM13887295

Reference no: EM13887295

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