$3.$ The image below shows the tapered tail section of a fuselage. The stringers all have areas of $\backslash (0\mathrm{.}5-\backslash$mathrm$\{$in$\}^\{2\}\backslash ).$ The left $($large$)$ end of this section is attached $($cantilevered$)$ to the main section of the fuselage. The vertical and horizontal tail structures $($housing the rudder and elevator$)$ are attached to the right $($small$)$ end of this section. If a maneuver in flight causes a vertical force from the elevator and a horizontal force from the rudder as shown, determine the shear flows created in the skin panels at cross$-$section A$-$A $($assume that the stringers carry all the bending loads$).$ For the ease of comparing results, number your stringers clockwise starting at the top$-$most stringer.