Foundations of Materials Science and Engineering
6th Edition
ISBN: 9781259696558
Author: SMITH
Publisher: MCG
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Chapter 7.10, Problem 32AAP
To determine
The fatigue life of the plate.
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Some aluminum aircraft components have a KIc = 35 MPa(m)1/2. It has been determined that failure occurs at a stress of 250 MPa when the critical internal crack length is 2 mm. Will this component achieve failure at a stress of 325 MPa when the critical internal crack length is 1.1 mm?
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4.
5. A ceramic matrix composite contains internal flaws as large as 0.001 cm in length. The
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Materia!
Modulus
of
Yield
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Strength
(MPa)
Elasticity(GPa)
Strength(MPa)
Aluminium alloy
70
255
420
Brass alloy
100
345
420
Сopper
110
210
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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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Need a deep-dive on the concept behind this application? Look no further. Learn more about this topic, mechanical-engineering and related others by exploring similar questions and additional content below.Similar questions
- A large flat plate is subjected to constant-amplitude uniaxial cyclic tensile and compressive stresses of 120 and 35MPa, respectively. If before testing the largest surface crack is 1.00 mm and the plain-strain fracture toughness of the plate is 35 MPa vm, estimate the fatigue life of the plate in cycles to failure. For the plate, m = 3.5 and A=5.0 x 10-12 in MPa and meter units. Assume Y = 1.3.arrow_forwardThe part of the vehicle is production from an magnesium alloy ,if KIC 40 MPa√m. The fracture occurred at a pressure of 195 MPa when the maximum edge crack length was 3.0 mm. Calculate the value Y. If a stress level is increased to 275 MPa and the maximum edge crack length is reduced to 2.3 mm, predict whether any fracture will occur. Compare your answer with existing data. Justify your answerarrow_forwardHelp me pleasearrow_forward
- Figure 5 shows a failure assessment diagram (FAD) from the R6 calculator spreadsheet. (a) Make a copy sketch of the FAD in Figure 5, and indicate the regions of brittle fracture and plastic collapse. (2 mark (b) Using Figure 5, calculate the reserve factor on load. Explain how you obtained your answer. (4 mark. (c) Indicate on your sketch the effect on the FAD if: (i) a residual stress were present in the vicinity of the crack (ii) the crack length were increased (iii) the toughness of the material were improved. (3 + 3 + 3 = 9 marks Plate in tension - through-thickness edge crack 1.2 08- 0 76. 0 81 *06- 20 46. 0 48 04- 02- 0O 02 04 0.6 0.8 10 1.2 1.4 1.6 L, Figure 5 FAD for Question 6arrow_forwardAn 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 55arrow_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
- Some aircraft component is fabricated from an aluminium alloy that has a plane strain fracture toughness of 40 MPa√m. It has been determined that fracture results 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 crack is 6.0 mm? Why or why not?arrow_forwardCompute the magnitude of the maximum stress that exists at the tip of an internal crack having a radius of curvature of 2.5 × 10-4 mm (10-5 in.) and a crack length of 2.5 × 10-2 mm when a tensile stress of 170 MPa is applied?arrow_forwardAn infinitely large sheet is subjected to a gross stress of 350 MPa. There is a central crack 5/π cm long and the material has a yield strength of 500 MPa. a. Calculate the stress-intensity factor at the tip of the crack. b. Calculate the plastic-zone size at the crack tip. c. Comment upon the validity of this plastic-zone correction factor for the above case.arrow_forward
- Question 6 What is the calculated fracture toughness, K, for the perspex specimen in MPa root m? Give your answer to 2 decimal places. P = 250 N, crack length = 5.5 mm W= 13.3 mm, B = 5.45 mm Note that the span length (s) is 38mm. Take f(a/W) as 0.78arrow_forwardA structural component in the shape of a flat plate 24.2 mm thick is to be fabricated from a metal alloy for which the yield strength and plane strain fracture toughness values are 537 MPa and 28.2 MPa-m¹/2, respectively. For this particular geometry, the value of Y is 1.9. Assuming a design stress of 0.4 times the yield strength, calculate the critical length of a surface flaw. i mmarrow_forwardSuppose you have a 1020 steel plate in axial loading, with an static axial F of 30000 lbf. The plate is 4" thick, 2" high, and 6" length. The hole is in the center of the plate, and is 1/4“ in diameter. The plate is at room temperature, and the strain at fracture is greater than ɛf > 0.1. If Sy = 80 ksi and Sut = 100 ksi, calculate the highest stress in the plate. Plate dimensions: 6.00" 2.00" 1.00" 0.25" 3.00"arrow_forward
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