An aircraft component is fabricated from an aluminum alloy that ha determined that fracture results at a stress of 249 MPa when the m a) Determine the value of Yora for this same component and a length is 1.08 mm. i MPa/m

39)A tensile test specimen has a gage length=3.0 inches and a diameter=  .75 inches. Yielding occurs at a load of 38000lbs. The corresponding gage length=3.0103 inches (neglect the .0.2% yield point). The maximum load of 54000lbs is reached at a gage length =3.453 inches. If fracture occurs at a gage length of 3.873inches, determine the percent elongation at fracture (Round to the nearest whole %)

A tensile specimen havign a diameter of 6 mm and a gauge length of 50 mm was tested to fracture and the stress-strain diagram is show. Poisson's ratio of material, v = 0.3   Determine the load P that the sample is subjected to when a stress of 300 MPa is applied. What is the instantaneous diameter of the sample given a longitudinal strain of 0.002?