Suppose that a wing component on an aircraft is fabricated from an aluminum alloy that has a plane strain fracture toughness of 28MPaym (25.48 ksi,in). It has been determined that fracture results at a stress of 119 MPa (17260 psi) when the maximum internalcrack length is 9.3 mm (0.3661 in.). For this same comnponent and alloy, compute the stress level at which fracture will occur for acritical internal crack length of 5.8 mm (0.2283 in.),MPa

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Answered: Suppose that a wing component on an…

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

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Problem 1.1MA

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. Suppose that a wing component on an aircraft is fabricated from analuminum alloy that has a plane strain fracture toughness of 40 MPa√m. It has been determined that fracture results at a stress of 365MPa when the maximum internal crack length is 2.6 mm. For thissame component and alloy, compute the stress level at whichfracture will occur for a critical internal crack length of 4.0 mm.
Suppose that a wing component on an air- craft is fabricated from an aluminum alloy that has a plane strain fracture toughness of 40 MPaVm (36.4 ksi Vin.). It has been deter- mined that fracture results at a stress of 365 MPa (53,000 psi) when the maximum internal crack length is 2.5 mm (0.10 in.), For this same component and alloy, compute the stress level at which fracture will occur for a critical in- ternal crack length of 4.0 mm (0.16 in.).
Suppose that a wing component on an aircraft is fabri- cated from an aluminum alloy that has a plane-strain fracture toughness of 26.0 MPa Vm (23.7 ksi Vin.). It has been determined that fracture results at a stress of 112 MPa (16,240 psi) when the maximum internal crack length is 8.6 mm (0.34 in.). For this same component and alloy, compute the stress level at which fracture will occur for a critical internal crack length of 6.0 mm (0.24 in.).
A large plate is fabricated from a steel alloy that has a plane strain fracture toughness of 55 MPa√m. If during service use, the plate is exposed to a tensile stress of 200 MPa, compute the minimum length of a surface crack that will lead to a fracture. Assume the value of 1.0 for Y.
A material has a yield strength of 1150Mpa and a fracture toughness of 47 Mpa m^1/2. If the applied stress is 0.3 of the yield strength.Find the size of an internal crack that can lead to failure.
A high-strength steel has yield strength of 1165 MPa and fracture toughness of 95 MPavm. Calculate the size of an internal crack that will lead to catastrophic failure at an applied stress of 80% yield strength. (Y = 1.00 for internal crack, and Y=1.12 for surface crack)
Find the tensile toughness for a metal alloy with modulus of elasticity of 103 ???. Assume the plastic deformation begins at a strain value of 0.007 and fracture occurs at a strain value of 0.60. Assume also that fracture occurs at the point where necking begins and that the Κ and ? values are 1520 ??? and 0.15 respectively.
The flexural (or fracture) strength of brittle materials may be determined using a variation ofEquation 8.1. Compute the critical crack tip radius (row sub t in nm) for an Al2O3 specimen thatexperiences tensile fracture at an applied stress (sigma initial) of 275 MPa. Assume a critical surfacecrack length (a) of 2 * 10^-3 mm and a theoretical fracture strength of E/10, where E is themodulus of elasticity (393 GPa). Note, fracture will occur when sigma sub m reaches the theoreticalfracture strength of the material.given equation: sigma sub n = 2*sigma initial*sqrt(a/row sub t)
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.
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 MPaym. 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
In the Table below Data for Mar M 247-a Nickel base superalloy is shown. (1) Plot the steady state strain rate and time to rupture to predict a relationship between the two variables. Provide an equation for the relationship that you see. (2) Give an explanation as to why the fracture elongation is going up with stress.
An annealed-steel specimen has a 0.750 in. diameter and a 12.000 in. gage length. Maximum load is reached at 60,000 lbs and fracture occurs at 30,000 Ibs. For this steel, E= 360 x 10° psi. (a) Draw a sketch of stress-strain diagram for a typical steel in tension? (b) What is the ultimate tensile strength (UTS)? (c) Why does fracture occur at a lower load than the maximum load? (d) What is the elongation when a tensile stress of 30,000 psi is applied? A 400-mm-long rod with a diameter of 4.5 mm is loaded with a 5000-N weight. If the diameter decreases to 3.5 mm, compute the final length of the rod. 3. 4. A steel rod 1.5 m long and 75 mm x 75 mm in cross-section is subjected to a tensile force of 160 kN. Determine the elongation of the rod, if modulus of elasticity for the rod material is 900 GPa. 5. A hollow cylinder 4.5 m long has an outside diameter of 80 mm and inside diameter of 60 mm. If the cylinder is carrying a load of 75 kN, find the stress in the cylinder. Also find the…

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