4 m P B 3 m 2 m 2 m

σ (MPa) 490 0.007 -e (mm/mm) A specimen has the stress-strain diagram shown. The specimen has an original diameter of 12.4 mm, and its modulus of rigidity is 27.4 GPa. Determine the specimen's diameter when the longitudinal stress is 325 MPa.

If DC has a normal strain € = 0.003, DA has a normal strain y = 0.004 and at D, Yzy = 0.02 rad, determine the average normal strain along diagonal CA. Express your answer in millimeters per millimeter to three significant figures.

Q6

The bar is made of an aluminum alloy having a stress–strain diagram that can be approximated by the straight line segments shown. Assuming that this diagram is the same for both tension and compression, determine the moment the bar will support if the maximum strain at the top and bottom fibers of the beam is Pmax = 0.05.

Please show all work!

Determine the shear strain gxy at corners A and B if the plastic distorts as shown by the dashed lines.

The force P at D causes the rigid bar CBD to rotate by 0 = 0.5°. The flexible cable AB was unstretched before the application of the force. Determine the normal strain in the cable and the horizontal displacement of point D. A 16" D B C -0-- 12" 12" P

The elastic portion of the tension stress–strain diagram for an aluminum alloy is shown in the figure. The specimen used for the test has a gage length of 2 in. and a diameter of 0.5 in. If the applied load is 10 kip, determine the new diameter of the specimen. The shear modulus is Gal = 3.811032 ksi.

1) An airplane's weight change is determined by reading the strain gauge A mounted on the plane's aluminum wheel strut. Before the plane is loaded, the strain gauge reading in the strut is &₁ = 0.00100 in./in., whereas after loading &2 = 0.00243 in./in. Determine the change in the force on the strut if the cross-sectional area of the strut is 3.5 in². and E = 10(10³) Ksi. O