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Unformatted text preview: MEEN 222502 Fall 2008 Homework #5 Due: 5 November 2008 at the beginning of class 1. Callister 8.4 The maximum allowable surface crack length for MgO may be determined using Equation 8.3; taking 225 GPa as the modulus of elasticity (Table 12.5), and solving for a , leads to mm 0.73 m 10 7.9 ) N/m 10 ( )(13. N/m) )(1.0 N/m 10 (2)(225 2 4 2 2 6 2 9 2 = = = = c s E a 2. Callister 8.7 This problem asks us to determine the stress level at which an a wing component on an aircraft will fracture for a given fracture toughness ( m MPa 26 ) and maximum internal crack length (6.0 mm), given that fracture occurs for the same component using the same alloy at one stress level (112 MPa) and another internal crack length (8.6 mm). It first becomes necessary to solve for the parameter Y for the conditions under which fracture occurred using Equation 8.5. Therefore, 2.0 2 m 10 8.6 ( MPa) (112 m MPa 26 3 = = = a K Y c I Now we will solve for...
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 Fall '08
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