An aircraft component is fabricated from an aluminum alloy that has a plane strain fracture toughness of 32 MPa √//m. It has been determined that fracture results at a stress of 215 MPa when the maximum (or critical) internal crack length is 2.29 mm. a) Determine the value of Yo√√a for this same component and alloy at a stress level of 279 MPa when the maximum internal crack length is 1.15 mm. i MPa √m b) Under these circumstances will the component fail?

An aircraft component is fabricated from an aluminum alloy that has a plane strain fracture toughness of 32 MPa √//m. It has been determined that fracture results at a stress of 215 MPa when the maximum (or critical) internal crack length is 2.29 mm. a) Determine the value of Yo√√a for this same component and alloy at a stress level of 279 MPa when the maximum internal crack length is 1.15 mm. i MPa √m b) Under these circumstances will the component fail?

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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1. A bronze alloy specimen having a diameter of 12.8 mm and a gage length of 50 mm was tested to fracture. Stress and strain data obtained during the test are shown in Figure. Determine: 400 Upper scale a. the modulus of elasticity. b. the proportional limit. c. the ultimate strength. 320 Lower scale 240- d. the yield strength (0.20% offset). 160 e. the modulus of resilience. f. the true fracture stress if the 80 final diameter of the specimen at the location of the fracture was 10.5 mm. 0.100 0.200 0.300 0.400 0.005 0.010 0.015 0.020 g. The Poisson's ratio. Strain (mm/mm) Stress (MPa)
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