HW-06%20Solutions - #1 8.6 We are asked to determine if an...

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8.6 We are asked to determine if an aircraft component will fracture for a given fracture toughness (40 MPa m ), stress level (260 MPa), and maximum internal crack length (6.0 mm), given that fracture occurs for the same component using the same alloy for another stress level and internal crack length. It first becomes necessary to solve for the parameter Y , using Equation 8.5, for the conditions under which fracture occurred (i.e., σ = 300 MPa and a = 4.0 mm). Therefore, Y = K Ic σπ a = 40 MPa m (300 MPa) ( π ) 4x1 0 3 m 2 = 1.68 Now we will solve for the product Y a for the other set of conditions, so as to ascertain whether or not this value is greater than the K Ic for the alloy. Thus, Y a = (1.68)(260 MPa) ( π ) 6x1 0 3 m 2 = 42.4 MPa m (39 ksi in. ) Therefore, fracture will occur since this value ( 42.4 MPa m ) is greater than the K Ic of the material, 40 MPa m .
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8.10 This problem asks that we determine whether or not a critical flaw in a wide plate is subject to detection given the limit of the flaw detection apparatus (3.0 mm), the value of
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HW-06%20Solutions - #1 8.6 We are asked to determine if an...

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