Problem 6 Estimate the Brinell and Rockwell hardness for the naval brass for which the stress-strain behavior is shown in the figure. Stress (MPa) 500 400 300 200 100 Tensile strength 450 MPa (65,000 psi) MPa 40 200 100 I 0.10 10³ psi I 30 20 10 I 0.20 Strain Yield strength 250 MPa (36,000 psi) 0.005 0.30 70 60 50 40 30 20 10 0.40 Stress (10³ psi)

Problem 6 Estimate the Brinell and Rockwell hardness for the naval brass for which the stress-strain behavior is shown in the figure. Stress (MPa) 500 400 300 200 100 Tensile strength 450 MPa (65,000 psi) MPa 40 200 100 I 0.10 10³ psi I 30 20 10 I 0.20 Strain Yield strength 250 MPa (36,000 psi) 0.005 0.30 70 60 50 40 30 20 10 0.40 Stress (10³ psi)

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

See similar textbooks

Similar questions

Draw the tensile curves of the following materials, taking into account the appropriate elongation at break, modulus of elasticity and tensile stress, on the side stress-strain graph. a)Low carbon steel (Ecelik=200Gpa),(Syield=300MPa),(Stensile=400MPa) b)High carbon steel (Esteel=200GPa),(Stensile=700MPa) c)Aluminum (Ealuminum=70GPa), (Syield=200MPa),(Stensile=300MPa) d)Cast iron (Ecast iron=120GPa),(Stensile=200MPa)
For a number of points during a tension test on Man-Ten steel, engineering stress and strain data are given in Table. Also given are minimum diameters measured in the necked region in the latter portions of the test. The initial diameter was 6.32 mm. (a) Determine the Young’s modulus; (b) Determine the true stress and strain throughout; (c) Calculate the true plastic strain for the beyond yielding.
10.3. Consider the state of stress shown below that exists at a location within a component made up ofa brittle material, where this brittle material has tensile and compressive ultimate strengths ofσ UT = 170 MPa and σ UC = 850 MPa, respectively. Has the material failed at this location in thecomponent? Please include a free body diagram.
Analyse the differences between the 2 attached stress-strain curves for 0.9% carbon steel and 0.15% carbon steel.
Sketch the typical engineering stress-strain diagram behaviour to fracture point, F and the tensile strength TS, together with the geometry of the deformed specimen at various point along the curve.
For a tensile test it can be shown that the percent cold work (%CW) is related to strain according to the following relationship: %CW=(εε+1) × 100 Using this equation, compute the percent cold work experienced by naval brass (for which the stress-strain behavior is shown in the Animated Figure 6.12) when a stress of 415 MPa (60190 psi) is applied.
Figure 6.23 shows the tensile engineering stress– strain curve in the elastic region for a gray cast iron. Determine (a) the tangent modulus at 25 MPa (3625 psi) and (b) the secant modulus taken to 35 MPa (5000 psi).
A 30 ?? square plate is subjected to uniform pressure as shown in Figure.1. The 2D loading stressesare described. If the modulus of elasticity is 200 ??? and the lateral constant (Poisson's ratio ? = 0.3). Estimatethe change in length in the vertical, horizontal and diagonal sides as well as determine the volumetric strain.Illustrate the effect of two-dimensionalstrain by constructing appropriate sketches (before and after deformation).Repeat the analysis for lower value of pressure and higher value in the range of [20 -100 MPa] and comment onthe overall results.
An NDT examination of a steel component reveals the presence of a 5 mm long edge crack. If plane - strain conditions prevail (KIC = 75 MPa.m0.5), what would be the residual service lifetime of the steel part if it were subjected to repeated stresses of 400 MPa? The Paris law equation for the steel has parameters of A=4X10-37 and m = 4
1. A cylindrical steel specimen, with an initial diameter of 7mm, has elongated by 40% at the point when it starts to neck down. The load at the start of necking is 35 kN. What is the true stress at the ultimate tensile stress? The answer is 1273, but I'm not getting that. Please answer soon and neatly. Don't copy or I will dislike u many.
The fuselage of an airliner can be considered as a thin-walled tubeinternally pressurized with a diameter of 7 m and a thickness of 3 mm. It is made withAluminum sheets with K ic fracture toughness of 100 MPa m1/2. At cruising altitudeinternal pressure gauge shows 0.0.Mn/m2.. In a horizontal row rivets have beencaused many fatigue cracks and have joined together to form a longitudinal crack thatit goes through the thickness of the fuselage. Estimate the critical length for this crack to propagate,causing the fuselage to break. (The pressure in a tube is resolved into a tension in the wallfrom ? = p r / t, where p = pressure, r = radius, t = thickness
A high-strength steel has a yield strength of 1,460 MPa and a KIC of 98 MPa √m. Calculate the size of a surface crack that will lead to catastrophic failure at an applied stress of 3/4Y.S.