4. (40 pts) The fiber orientation in a CFRP lamina is 0 = 45. The CFRP properties are E = 138 GPa, E2 = E3 = 10 GPa, V12 V13 =0.34, V23 =0.45, and G12=7 GPa. Assuming the composite is in the state of plane stress (see Figure 1), determine, by hand and computationally, the following when the lamina is under uniform stresses x = 70 MPa, y 14 MPa, and Txy=0: a. longitudinal, transverse and shear stresses along the 1-2 axes; b. longitudinal, transverse and shear strains along the 1-2 axes c. longitudinal, transverse and shear strains along the x-y axes; and d. out-of-plane strain Ez. 1 y