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1M03 2009 ASSIGNMENT 5-2 &Acirc;&iquest;&Acirc;&macr;

# 1M03 2009 ASSIGNMENT 5-2...

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View Results Assignment 5 (Ch 8 & 9) Name: SOO NAM Attempt: 2 / 3 Out of: 15 Started: March 24, 2009 1:56pm Finished: March 24, 2009 2:01pm Time spent: 5 min. 45 sec. Question 1 (1 point) True or False? The degree of brittleness of a material is not a function of temperature. Student response: Correct Response Student Response Answer Choices a. True b. False General feedback: False . Most materials become more ductile as the temperature increases. For more information, see the section on Fundamentals of Fracture in the text. Score: 0 / 1 Question 2 (1 point) A structural component in the shape of a flat plate 47.6 mm thick is to be fabricated from a metal alloy for which the yield strength and plane strain fracture toughness values are 528 MPa and 32.4 MPa-m 1/2 , respectively. For this particular geometry, the value of Y is 1.71. Assuming a design stress of 0.461 times the yield strength, calculate the critical length of a surface flaw (in mm). The critical length of a surface flaw is given by Here σ d is the design stress. Use decimal notation, digits after decimal: 2 Student response: Not answered Correct answer: 1.93 mm General feedback: Use the equation given to solve for a c . Remember that σ d = 0.461 * σ y . Score: 0 / 1 ( Question not answered. ) Question 3 (1 point) 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 has been determined that the wing component will fracture when a stress of 112 MPa is applied and the maximum (or critical) internal crack length is 8.6 mm. Will the wing component fracture when 125 MPa is applied to it and the critical internal crack length is 6.0 mm? Student response: Correct Response Student Response Answer Choices a. Yes, the wing component will fracture under those conditions.

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