Foundations of Materials Science and Engineering
6th Edition
ISBN: 9781259696558
Author: SMITH
Publisher: MCG
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Chapter 7.10, Problem 49SEP
(a)
To determine
The metal which you select to avoid yielding.
(b)
To determine
The metal which you select to avoid yielding and have lightest component.
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Explain how fatigue failure occurs even if the material does not see overall stress levels higher than the yield strength.
A material has a fracture toughness of 70.0 MPa-m0.5 and a yield
strength of 1200 MPa and is to be made into a large panel.
If the panel is stressed to one-half the yield stress, what is the maximum central crack size 7 that can be tolerated without catastrophic failure?
Express your answer to three significant figures and include the appropriate units.
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7. By referring to a sketch showing a stress concentration, describe the phenomenon of crack initiation in high cycle fatigue and comment on the proportion of fatigue life that is used in initiating a crack under these conditions. 8. By considering a notched metal bar as an example, explain (with the aid of diagrams), how you would reduce the probability of fatigue failure by applying self-stresses. 9. Describe, with sketched examples, how the stress-raising effect of circular and elliptical holes can be considered qualitatively as being analogous to liquid flow. 10. By considering a circular hole in a thin elastic sheet, explain (with the aid of any diagrams as appropriate) how a stress concentration can magnify stress. 11. Explain the principles of designing alloys for oxidation resistance.12. Describe and explain (with the aid of a sketch) how crack propagation is enhanced through stress corrosion cracking
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Chapter 7 Solutions
Foundations of Materials Science and Engineering
Ch. 7.10 - What are the characteristics of the surface of a...Ch. 7.10 - Prob. 2KCPCh. 7.10 - Prob. 3KCPCh. 7.10 - Prob. 4KCPCh. 7.10 - Prob. 5KCPCh. 7.10 - Prob. 6KCPCh. 7.10 - Prob. 7KCPCh. 7.10 - Prob. 8KCPCh. 7.10 - Prob. 9KCPCh. 7.10 - How does the carbon content of a plain-carbon...
Ch. 7.10 - Describe a metal fatigue failure.Ch. 7.10 - What two distinct types of surface areas are...Ch. 7.10 - Prob. 13KCPCh. 7.10 - Prob. 14KCPCh. 7.10 - Prob. 15KCPCh. 7.10 - Describe the four basic structural changes that...Ch. 7.10 - Describe the four major factors that affect the...Ch. 7.10 - Prob. 18KCPCh. 7.10 - Prob. 19KCPCh. 7.10 - Prob. 20KCPCh. 7.10 - Prob. 21KCPCh. 7.10 - Determine the critical crack length for a through...Ch. 7.10 - Determine the critical crack length for a through...Ch. 7.10 - The critical stress intensity (KIC) for a material...Ch. 7.10 - What is the largest size (in mm) of internal...Ch. 7.10 - A Ti-6Al-4V alloy plate contains an internal...Ch. 7.10 - Using the equation KIC=fa, plot the fracture...Ch. 7.10 - (a) Determine the critical crack length (mm) for a...Ch. 7.10 - A fatigue test is made with a maximum stress of 25...Ch. 7.10 - A fatigue test is made with a mean stress of...Ch. 7.10 - A large, flat plate is subjected to...Ch. 7.10 - Prob. 32AAPCh. 7.10 - Refer to Problem 7.31: Compute the final critical...Ch. 7.10 - Prob. 34AAPCh. 7.10 - Prob. 35AAPCh. 7.10 - Equiaxed MAR-M 247 alloy (Fig. 7.31) is used to...Ch. 7.10 - Prob. 37AAPCh. 7.10 - If DS CM 247 LC alloy (middle graph of Fig. 7.31)...Ch. 7.10 - Prob. 39AAPCh. 7.10 - Prob. 40AAPCh. 7.10 - Prob. 41SEPCh. 7.10 - Prob. 42SEPCh. 7.10 - A Charpy V-notch specimen is tested by the...Ch. 7.10 - Prob. 44SEPCh. 7.10 - Prob. 45SEPCh. 7.10 - Prob. 46SEPCh. 7.10 - Prob. 47SEPCh. 7.10 - Prob. 48SEPCh. 7.10 - Prob. 49SEPCh. 7.10 - Prob. 50SEPCh. 7.10 - While driving your car, a small pebble hits your...Ch. 7.10 - Prob. 52SEPCh. 7.10 - Prob. 53SEPCh. 7.10 - Prob. 54SEPCh. 7.10 - Prob. 56SEPCh. 7.10 - Prob. 57SEPCh. 7.10 - Prob. 58SEPCh. 7.10 - Prob. 59SEPCh. 7.10 - The components in Figure P7.60 are high-strength...
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- Problem 4. A large flat plate is subjected to constant-amplitude uniaxial cyclic tensile and compressive stresses. Compute the final critical surface crack length if the fatigue life must be a minimum of 7.0 x 10^5 cycles. Assume the initial maximum edge surface crack length of 1.80 mm and a maximum tensile stress of 160 MPa. Assume m = 1.8 and A = 7.5 x 10^-13 in MPa and meter units. Assume Y = 1.25.arrow_forwardA three-point transverse bending test was performed on a glass specimen having a square cross-section of 18.5 mm length on each edge. The specimen fractured at a load of 4530 N when the distance between support points was 42 mm. A second test is to be performed on another specimen of this same glass material, but one that has a circular cross-section. What minimum specimen diameter is required to ensure that fracture will not occur when a load of 3480 N is applied? Assume that the support separation is maintained at 42 mm. mmarrow_forwardWhat is the magnitude of the maximum stress that exists at the tip of an internal crack having a radius of curvature of 1.9 x 10" mm and a crack length of 3.8 x 10 mm when a tensile stress of 140 MPa is applied? 4. 5. A ceramic matrix composite contains internal flaws as large as 0.001 cm in length. The plane strain fracture toughness of the composite is 45 and the tensile strength is 550 MPa. Will the flaw cause the composite to fail before the tensile strength is reached? Assume that Y 1 A cylindrical rod 500 mm long, having a diameter of 12.7 mm, is to be subjected to a tensile load. If the rod is to experience neither plastic deformation nor an elongation of more than 1.3 mm. when the applied load is 29,000 N, which of the four met ls or alloys listed below are possible cardidates? Justify your choice(s). Materia! Modulus of Yield Tensiie Strength (MPa) Elasticity(GPa) Strength(MPa) Aluminium alloy 70 255 420 Brass alloy 100 345 420 Сopper 110 210arrow_forward
- A wing component on an aircraft is fabricated from an aluminum alloy that has a plane strain fracture toughness of 28 . It has been determined that fracture results at a stress of 106 when the maximum internal crack length is 9.2 . For this same component and alloy, compute the stress level at which fracture will occur for a critical internal crack length of 6.6 .arrow_forward11. List the conditions that can induce brittle failure even in a ductile material.arrow_forwardComponents that suffered fatigue failure during operation can be identified byseveral characteristic features. In a few words, describe some of these features. Sketch orprovide an image of a component that has failed due to fatigue. Include labels on the imagedenoting the onset of crack propagation and hallmark features of fatigue failure.arrow_forward
- 1. Explain what is meant by the term fast fracture, stating its causes, and give two examples from which it might occur. 2. Briefly describe, with the aid of a sketch in each case, the appearance of a fracture surface that has undergone (i) ductile tearing and (ii) cleavage.3. Explain, with the aid of a diagram, how a crack propagates by ductile tearing within the plastic zone of an engineering metal.4. Explain, with the aid of diagrams, how crack propagation is affected by the presence of the fibers in glass fibre reinforced resins.5. With the aid of a sketch, describe and explain the fracture surface characteristics of a metal component that has undergone fatigue failure. 6. By referring to graphical representations of fatigue test results, explain the terms S-N curve, Fatigue Limit and Endurance Limit. Please answer all partsarrow_forwardImagine that you have two cracked components that are identical to one another except that Component A has a preexisting crack that is twice as long as that found in Component B. Does that mean that the fatigue lifetime of Component A will be 50% that of Component B?arrow_forwardA fuel transportation industry uses a spherical 1045 carbon steel pressure vessel with a diameter of 800 mm and a thickness of 30 mm, covered with a brittle varnish that cracks in the vessel cover when the deformation exceeds 200 x 106. What is the value of the internal pressure that causes the varnish to develop cracks? (Assume E = 205 GPa and v = 0.30). Explain you answer.arrow_forward
- Question 1 An aircraft component is fabricated from an aluminum alloy that has a plane- strain fracture toughness of 40 MPa√m. It has been determined that fracture occurs at a stress of 300 MPa when the maximum (or critical) internal crack length is 4.0 mm. For this same component and alloy, will fracture occur at a stress level of 260 MPa when the maximum internal crack length is 6.0 mm? why and why not?arrow_forwardA three-point bending test was performed on an aluminum oxide specimen having a circular cross section of radius 5.6 mm; the specimen fractured at a load of 4280 N when the distance between support points was 43 mm. Another test is to be performed on a specimen of this same material, but one that has a square cross section of 18 mm in length on each edge. At what load would you expect this specimen to fracture if the support point separation is maintained at 43 mm? Ff= Narrow_forward1.) 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 youarrow_forward
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