(Solved): please solve part (c) The fuselage section shown in Figure 3 has been idealised into an arrangement ...

The fuselage section shown in Figure 3 has been idealised into an arrangement of direct stress-carrying booms and shear stress-only carrying skin panels. The crosssectional area of each boom is $216.6{\mathrm{mm}}^2$. The section is subjected to an eccentric shear load of $100\mathrm{kN}$, as shown, and a positive bending moment of $200\mathrm{kNm}$, applied in the vertical plane of symmetry. Calculate: (a) The direct stress in the booms. (b) The shear flow in the panels. (Note: take the cut in wall 1-2). (c) Sketch the shear flow in the panels