An angle composite laminate $[+45/-45]32$S has the following stiffness matrices and subjected to Nxx $=0\mathrm{.}1$ N$/$mm$.$The ply thickness is $0\mathrm{.}013$mm$.$Determine the stresses in each layer of the laminate.

$=-45$deg: Q$11=40\mathrm{.}11$GPa$,$ Q$22=40\mathrm{.}11$GPa$,$ Q$12=33\mathrm{.}61$GPa$,$ Q$66=34\mathrm{.}57$GPa$,$ Q$16=-31\mathrm{.}3$GPa, Q$26=-31\mathrm{.}3$GPa

$=+45$deg: Q$11=40\mathrm{.}11$GPa$,$ Q$22=40\mathrm{.}11$GPa$,$ Q$12=33\mathrm{.}61$GPa$,$ Q$66=34\mathrm{.}57$GPa$,$ Q$16=31\mathrm{.}3$GPa, Q$26=31\mathrm{.}3$GPa

$($Reference "FIBER REINFORCED COMPOSITES: Materials, Manufacturing, and Design $3$rd$"$edition chapter $3$example $3\mathrm{.}6$& problem $3\mathrm{.}48)$