2. (20%) Consider a doubly symmetrical fuselage section shown in Figure 2. Assume that the fuselage has been idealized into an arrangement of normal stress carrying booms and shear stress carrying skin panels; the boom areas are all 150 mm². Find the shear flows in the panels when the section is subjected to a shear load of 50 kN and a bending moment of 100 kNm. Please just describe the major solution procedures and equations needed, without actually solving for the shear flows. 250 mm 10 50 kN 1 2 9 45° 500 mm 3 8 7 6 Timure 5 100 kNm 500mm