MSE 230 HW5 (due 02/11, 02/12) Spring 2010 1. Callister 8.7: Suppose that a wing component on an aircraft is fabricated from an aluminum alloy that has a plane strain fracture toughness of 26 MPa·m 1/2 . It is determined that fracture results at a stress of 112 MPa when the maximum internal crack length is 8.6 mm. For this same component and alloy, compute the stress level at which fracture will occur for a critical internal crack length of 6.0 mm. 2. Callister 8.9: Calculate the maximum internal crack length allowable for a Ti-6Al-4V titanium alloy component loaded to a stress one-half of its yield strength. Assume that the value of Y is 1.5. 3. The yield strength and fracture toughness of 4340 steel, in two different heat treatment conditions ("tempers"), are given below. (a) For a particular component ( Y = 1), the largest edge flaw is a = 0.5 mm. If the component were considered to fail if it yields or fractures, which condition (tempering temperature) would allow the higher design stress and what would be the value of that stress?
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