Questi mm length and 700 kg weight which is homogenously distributed over the wing (downwa aircraft wing with tubular rectangular cross section (600mmx150mm) thickness 25mm has 3 Additionally, there is a flight load distributed over the wing through the length as below (w=25 k upward). Engine (950 kg mass) and landing gear (400 kg mass) are assembled 1600mm and 80 a cantilever beam, fixed by the body of plane. Hint: draw shear and bending diagrams. For rect away from plane body which can be taken as point load. g= 10 m/s E=79 GPa. Assume that w ICG 1/12 b h a) Find maximum normal stress on wing due to bending moment? b) Find maximum shear stress? W H H 800mm 800mm