A component made of 7075-T6 aluminum alloy has an edge crack of 1.4 mm in length. Plane strain fracture toughness of this alloy is given as 27 MPavm. Geometrical factor of the crack is given as 1.2. (a) If this alloy is subjected to uniaxial tensile stress of 380 MPa, determine whether sudden brittle fracture occurs or not. (b) Calculate the maximum allowable crack size for this component in order not to be failed in brittle manner under a stress of 1000 MPa (Density of steel 7.85 g/cm³, 9.80665 N = 1 kg). Modulus of elastisity, GPa Ultimate tensile Yield strength, Alloy strength, MPa MPa 2014 Al alloy Bronze (92Cu-8Sn) High carbon steel Pure Titanium 97 186 380 72 110 152 380 615 215 240 330 107

A component made of 7075-T6 aluminum alloy has an edge crack of 1.4 mm in length. Plane strain fracture toughness of this alloy is given as 27 MPavm. Geometrical factor of the crack is given as 1.2. (a) If this alloy is subjected to uniaxial tensile stress of 380 MPa, determine whether sudden brittle fracture occurs or not. (b) Calculate the maximum allowable crack size for this component in order not to be failed in brittle manner under a stress of 1000 MPa (Density of steel 7.85 g/cm³, 9.80665 N = 1 kg). Modulus of elastisity, GPa Ultimate tensile Yield strength, Alloy strength, MPa MPa 2014 Al alloy Bronze (92Cu-8Sn) High carbon steel Pure Titanium 97 186 380 72 110 152 380 615 215 240 330 107

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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A component made of 7075-T6 aluminum alloy has an edge crack of 1.4 mm in length. Plane strain fracture toughness of this alloy is given as 27 MPavm. Geometrical factor of the crack is given as 1.2.| (a) If this component is subjected to uniaxial tensile stress of 380 MPa, determine whether sudden brittle fracture will occur or not. (b) Calculate the maximum allowable crack size for this component in order not to be failed in brittle manner under a stress of 1000 MPa.
(a) An AISI 4340 steel plate has a width W of 30 cm and has a central crack 2a of 3 mm. The plate is under a uniform stress σ. This steel has a KIc value of 50 MPa m1/2. Find the maximum stress for this crack length. (b) If the operating stress is 1,500 MPa, compute the maximum crack size that the steel may have without failure
A mechanical component is fabricated from a metallic alloy. From the experiment, it is obtained that the fracture of this material occured at a stress of 36 ksi when the maximum internal crack length is 0.10 in. The plain strain fracture toughness of this material is 30 ksi sqrt(in) for this same component and alloy, investigate whether fracture will occur at stress level of 55 ksi when the internal crack length is 0.06 in.
1.) Assume that a wing component on an airplane is made of an aluminum alloy with a plane strain fracture toughness of It was found that when the maximum internal crack length is 2.5 mm, breakage occurs at a load of 365 MPa. Find the stress level at which a critical internal crack length of 5.0 mm will fracture for the identical component and alloy. 2.) An S-five ninety alloy specimen nine hundred mm long will be subjected to eighty MPa tensile stress at eight hundred and fifteen degrees celcius. Later after five thousand of hours, compute its elongation. Consider a sum of one point five mm in the both immediate and main creep elongations. - Please answer this 2 and indicate the givens. Thank you
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1. Give an example of a creep plot for some material. From the creep plot, determinea. the steady-state creep rate and (b) the rupture lifetime.2. Describe the mechanism of crack propagation for both ductile and brittle modes offracture.
An airplane part is to be designed from view point of Fracture Toughness for which two materials are available. Consider Y=1.2 and ow =400 MPa, calculate (a) maximum internal crack length under the given condition for each material type. (b) How much stress on Aluminum part can be increased/decreased to comply with the critical crack length of 3 mm. 1/2 Кіс, МPa m Aluminum (7075-T3) 30 Titanium Ti-6AI-4Va 55
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For a piece of copper alloy, a standard stress test was applied to it, the following data was collected, from which a stress-strain diagram must be generated, where as data it is known that the initial diameter of the element is 0.505in. The analysis must include the following: 1.Modulus of Elasticity and modulus of resilience. 2.Percentage of elongation. 3.Percentage of area reduction. 4.Real and engineering stress at fracture. It is known that after the specimen fractures, its dimensions in terms of length and diameter are 3.014 and 0.374in, respectively.