Calculate shell section like wing type of aircraft. 1. To determine normal and shear stresses. Draw plots oz q. 2. To determine the coordinates of the center of bending. 3. To determine the running angle of torsional deflection. Y F H 0 A B C F Mx Qy Mx Input: 81=1,58,F=1,3F1=1,2F2, H1=0,5H Materials shall section: duralumin (E=7,2-105kgcm2) B A H H H2 F 9 front middle back cm cm cm cm cm cm cm2 cm kg kg.cm 320 170 140 16 20 15 18 0,3 20000 9.105 Note: skin 8 perceives normal stresses, 81 does not perceive normal stresses.