The stress state on the inside flange of an aluminum alloy 2024-T3 wheelhub is found to...

The stress state on the inside flange of an aluminum alloy 2024-T3 wheelhub is found to beσxx=−83 MPa,σyy=−145 MPa,σzz=−35 MPa,σxy= 44 MPa,σxz= 0, .σyz=−22 MPa. What is the safety factor guarding against failure assuming theloads are static?(A) 2.4(B) 3.7(C) 1.8(D) 2.7

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samet mamat answered 2 years ago

. A 20 mm diameter sphere made of aluminum alloy 2024 initially at a uniform temperature...

. A 20 mm diameter sphere made of aluminum alloy 2024 initially at a uniform temperature of 500 ºC is suddenly immersed in a saturated water bath maintained at atmospheric pressure. The surface of the sphere has an emissivity or 0.25. Determine. a.) the total heat transfer coefficient for this initial condition, and b.) what fraction of the total coefficient is contributed by radiation. (~180 W/m2 -K, ~ 7%)

A 2024-T3 aluminum bar has rectangular cross section dimensions of 2" x 0.5". The length of...

A 2024-T3 aluminum bar has rectangular cross section dimensions of 2" x 0.5". The length of the column is 9.0 inches. A) Calculate the transition slenderness ratio (Sr)D for this column. [Answer should be 69.9] B) Calculate the slenderness ratio for your assigned column length. [Answer should be 62] C) Calculate the maximum unit load (Pcr/A) for the bar. Indicate whether the column is a Johnson or Euler column. [Numerical answer should be 25296 psi but I don't know Johnson...

a rectangular slab of 2024-T6 alluminium alloy is to be machined by a cutting tool of...

a rectangular slab of 2024-T6 alluminium alloy is to be machined by a cutting tool of a rake angle of 6.5 degrees. the friction coefficiet between the tool and the slabmaterial was found to be 0.32 . if the shear yield stress of the alluminium alloy is 210 MN/m^2 , calculate the force in the direction of the tool feed (Fx) for a depth cut (t) of 0.8 mm and a unit tool width of 1mm.

Assume you have a metal alloy - an aluminum alloy for example - that has been...

Assume you have a metal alloy - an aluminum alloy for example - that has been welded and then heat treated in a way that leaves you uncertain as to the microstructure. Since the component is to be used for a critical application, you want to be sure of both the structure and mechanical properties. You want to create a single phase structure so that you can "start over" with a new heat treat cycle to more exactly and carefully...

identify the stages in the appropriate order in the precipitation hardening of an aluminum alloy

The average thickness of a flange on an aircraft component is found to be 1 mm...

The average thickness of a flange on an aircraft component is found to be 1 mm (from a sample of 36 measurements). a) Find the 95% and 99% confidence intervals for the mean thickness. Assume the population standard deviation is 0.1 mm. b) If we want to be 95% confident that our estimate of µ is off by less than 0.02 mm, how large of a sample is required?

An annealed aluminum alloy slab with a thickness of 12 mm and width of 1m is...

An annealed aluminum alloy slab with a thickness of 12 mm and width of 1m is to be cold rolled to a thickness of 9 mm using 2-high rolls with roll diameter of 1m. The rolls have a coefficient of friction of 0.08 and they are rotating with a speed of 18 RPM. The aluminum has an entrance speed of 50 m/min and a width that does not change as a result of drawing. The strength coefficient K =240 and...

The diameters of aluminum alloy rods produced on an extrusion machine are known to have a...

The diameters of aluminum alloy rods produced on an extrusion machine are known to have a standard deviation of 0.0001 in. A random sample of 25 rods has an average diameter of 0.5046 in. (a) Test the hypothesis that mean rod diameter is 0.5025 in. Assume a two-sided alternative and use (b) Find the P-value for this test. (c) Construct a 95% two-sided confidence interval on the mean rod diameter.

A wing component on an aircraft is fabricated from an aluminum alloy that has a plane...

A wing component on an aircraft is fabricated from an aluminum alloy that has a plane strain fracture toughness of 30 MPa (m) 1/2 . It has been determined that fracture results at a stress of 120 MPa when the maximum internal crack length is 8.4 mm. For this same component and alloy, Compute the stress level at which fracture will occur for a critical internal crack length of 5.6 mm?

For a bronze alloy, the stress at which plastic deformation begins is 300 MPa and the...

For a bronze alloy, the stress at which plastic deformation begins is 300 MPa and the modulus of elasticity is 115 GPa. What is the maximum load (in kN) that may be applied to a specimen having a cross-sectional area of 70 mm2 without plastic deformation? And if the original specimen length is 100 mm, what is the maximum length (in mm) to which it may be stretched without causing plastic deformation?

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