A 7075-T651 alloy is used in a structural component in an airplane. The component mustnot fail when subjected to a stress of 250 MPa. Several surface flaws have been detected on thecomponent. What is the largest (deepest) surface flaw that could be permitted with the 250MPa maximum stress? Use data from Table 1 and assume this component geometry and loadingcondition result in a Y value of 1.25.Yield StrengthKIMaterialMPaksiMPa√mksiVin.MetalsAluminum alloy (7075-T651)495722422

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Steel Design (Activate Learning with these NEW titles from Engineering!)

6th Edition

ISBN:9781337094740

Author:Segui, William T.

Publisher:Segui, William T.

Chapter1: Introduction

Section: Chapter Questions

Problem 1.5.6P: The data in Table 1.5.3 were obtained from a tensile test of a metal specimen with a rectangular...

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The frame of a space shuttle type vehicle must have a high yield strength and high stillness, and the most important design factor is weight. Of all the materials presented in this chapter, what material might be the most suitable for the frame of a space shuttle? Assume that there will be both tensile and compressive stresses. For a space shuttle, cost is not a limiting factor. (a) You can eliminate entire classes of materials from consideration with a brief statement about their unsuitability. (b) What material has the highest specific yield strength? Give the yield strength, specific gravity, specific yield strength, elastic modulus, and specific elastic modulus for this material. (c) What material has the highest specific elastic modulus? Give the yield strength, specific gravity, specific yield strength, elastic modulus, and specific elastic modulus for this material. (d) Compare the materials with the highest specific yield strength and highest specific elastic modulus for suitability in the space shuttle frame. (C) Discuss the suitability of the top-rated material for this design from the viewpoint of the ability to produce a frame.
The data in Table 1.5.3 were obtained from a tensile test of a metal specimen with a rectangular cross section of 0.2011in.2 in area and a gage length (the length over which the elongation is measured) of 2.000 inches. The specimen was not loaded to failure. a. Generate a table of stress and strain values. b. Plot these values and draw a best-fit line to obtain a stress-strain curve. c. Determine the modulus of elasticity from the slope of the linear portion of the curve. d. Estimate the value of the proportional limit. e. Use the 0.2 offset method to determine the yield stress.
The results of a tensile test are shown in Table 1.5.2. The test was performed on a metal specimen with a circular cross section. The diameter was 3 8 inch and the gage length (The length over which the elongation is measured) was 2 inches. a. Use the data in Table 1.5.2 to produce a table of stress and strain values. b. Plot the stress-strain data and draw a best-fit curve. c. Compute the, modulus of elasticity from the initial slope of the curve. d. Estimate the yield stress.
A structural component in the shape of a flat plate 24.3 mm thick is to be fabricated from a metal alloy for which the yield strength and plane strain fracture toughness values are 533 MPa and 22.0 MPa-m1/2, respectively. For this particular geometry, the value of Y is 1.3. Assuming a design stress of 0.4 times the yield strength, calculate the critical length of a surface flaw. What formulas do i use ? And how do i use them?
Sample: Malleable Steel (AISI 4145) Original Diameter: 6.14mm Gauge Length: 55 mm Final Length: 68.12 mm Final Diameter: 3.54mm Load (kN) Deformation (mm) Stress (MPa) 12.95 Strain (%) 0.3838 0.54 0.7841 0.95 26.48 1.3899 1.63 1.9485 2.07 3.3090 3.10 4.5821 4.22 5.9359 5.03 7.0340 5.51 8.2413 6.22 10.9446 7.22 13.1951 8.18 12.8228 8.77 12.2583 9.11 12.5915 9.61 13.2536 10.33 13.6636 10.71 13.9772 11.35 14.5433 12.63 15.1155 13.88 15.4970 15.10 15.6484 17.09 15.4031 17.79 14.7655 18.73 13.6721 19.28 10.4617 19.88
Task (3) you are asked to perform tensile test on specimens of two different materials (A and B) and you obtained the stress-strain diagram of the two specimens as shown in Figure 2: 400 350 300 250 Material A 200 150 100 50 0.02 0.04 0.06 0.08 0.1 0.12 0.14 0.16 0.18 Strain (mm/mm) 50 Material B 30 20 10 0.02 0.04 0.06 0.08 0.1 Strain (mm/mm) Figure 2: Tensile Test Analysis Stress (MPa) Stress (MPa)
Is it possible to conduct a valid plane strain fracture toughness test for a CrMoV steel alloy under the following conditions: KIC = 53 MPa√m , σys = 620 MPa, W = 6 cm, and plate thickness B = 2.5 cm?
Question-5 The following engineering stress-strain data were obtained from the tensile test for a 0.2% plain carbon steel. (a) Plot the engineering stress-strain curve for these data. (b) Determine the 0.2 percent offset yield stress for this steel. (c) Determine the tensile elastic modulus of this steel. (d) Determine the ultimate tensile strength of the alloy. (e) Determine the percent elongation at fracture. Engineering stress (ksi) 0 30 55 60 68 72 74 75 Engineering strain (in./in.) 0 0.001 0.002 0.005 0.01 0.02 0.04 0.06 Engineering stress (ksi) 76 75 73 69 65 56 51 Engineering strain (in./in.) 0.08 0.10 0.12 0.14 0.16 0.18 (Fracture) 0.19 Question-6 A 20-cm-long rod with a diameter of 0.250 cm is loaded with a 5000 N weight. If the diameter decreases to 0.210 cm, determine (a) the engineering stress and strain at this load and (b) the true stress and strain at this load.

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