Suppose that a wing component on an aircraft is fabricated from an aluminum alloy (E = 73 GPa) that has a plane-strain fracture toughness of 28.0 MPa√m. It has been determined that fracture results at a stress of 160 MPa. If we use another alloy (E = 150 GPa) with a plane-strain fracture toughness of 35.0 MPa√m, assuming that the size of the maximum internal crack is half in this new material for this same component. With appropriate calculations show whether the component can tolerate a stress of 145 MPa without fracture or not.
Suppose that a wing component on an aircraft is fabricated from an aluminum alloy (E =...
2. An aircraft component is fabricated from an aluminum alloy that has a plane strain fracture toughness of 35 MPa m. It has been determined that fracture results at a stress of 250 MPa when the maximum (or critical) internal crack length is 2.0 mm. For this same component and alloy, will fracture occur at a stress level of 325 MPa when the maximum internal crack length is 1.0 mm? (10 points)
An aircraft component is fabricated from an Al alloy that has a plane strain fracture toughness of 32 MPa·m1/2. It has been determined that fracture results at a stress of 235 MPa when the maximum internal crack length is 1.8 mm. For the same component and alloy, will fracture occur at a stress level of 310 MPa when the maximum internal crack length is 0.9 mm?
Canvas P O words </> Question 2 10 pts 2. An aircraft component is fabricated from an aluminum alloy that has a plane strain fracture toughness of 35 MPaT. It has been determined that fracture results at a stress of 250 MPa when the maximum (or critical) internal crack length is 2.0 mm. For this same component and alloy, will fracture occur at a stress level of 325 MPa when the maximum internal crack length is 1.0 mm? (10 points)...
3. A structural component is fabricated from an alloy that has a plane-strain fracture toughness of 69 MPa, m (69 MPa square root of "m"). It has been determined that this component fails at a stress of 250 MPa when the maximum length of a surface crack is 1.6 mm. What is the maximum allowable surface crack length (in mm) without fracture for this same component exposed to a stress of 250 MPa and made from another alloy that has...
Question 10 (7 marks) Suppose that a BMW car component fabricated from 4340 steel alloy having a plane strain fracture toughness of 50 MPavm is exposed to a stress of 950 MPa. NDT results show there are two cracks. One is a surface crack of 0.60 mm long, and the other is an internal crack of 2 mm long. Will this component experience fracture? Why or why not? Assume that the parameter Y has a value of 1.0. Kjc: Plane...
1. A large plate is fabricated from a steel alloy that has a plane strain fracture toughness of 82.4 MPavm. If the plate is exposed to a tensile stress of 345 MPa during service use, determine the minimum length of a surface crack that will lead to fracture. Assume a value of 1.0 for Y. Maximum stress at tip of elliptically shaped crack Pt 2Ery, 1/2 critical stress required for crack propagation in a brittle material πα KIe YoeVra Fracture...
A large plate is fabricated from a steel alloy that has a plane strain fracture toughness of 75 MPam (68.25 ksi vin.). If the plate is exposed to a tensile stress of 347 MPa (50330 psi) during use, determine the minimum length of a surface crack that will lead to fracture. Assume a value of 0.94 for Y. mm
1. AA 6061, a high-strength aluminum alloy, has a 0.2% offset yield strength of 37,500-psi and a plane strain fracture toughness (Kic) 26,400-psi (inch) At a service stress equivalent to 80% of the yield strength, will this structure fracture if it contains an edge crack of length 2.24-inches. Assume that the geometric factor, f, is 1.12. 2. A steel alloy, which has a plane strain fracture toughness (Kle) of 49-MPa(m) is exposed to a service stress of 1010-MPa. Is fracture...
the value of a parameter is not given, USE A SYMBOL in its place alues in parenthesis are points awarded to a complete solution. cademic dishonesty will automatically result in spective of points obtained. Question 1 10 pts 1. Consider a metal single crystal oriented such that the normal to the slip plane and the slip direction are at angles of 43.1° and 47.9° respectively, with the tensile axis. If the critical resolved shear stress is 20.7 MPa will an...
Problem 1 A component in the shape of a large sheet is to be fabricated from 4340 steel, which has a fracture toughness Kc 989 MPa-m's and a tensile yield,strength of 860 MPa. Ihe sheets are inspected for crack flaws after fabrication, but the inspection device cannot detect flaws smaller than 5 mm. The part is too heavy as designed. An engineer has suggested that the thickness be reduced and the material be heat-treated to increase its tensile strength to...