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This document discusses analyzing stresses on an unsymmetrical tapered fuselage structure due to applied loads. It provides an example problem to determine stringer stresses and forces at two stations, section 0 and section 30, given loads applied at station 150. The solution strategy is outlined, which involves using the general bending stresses equation and calculating the centroid position with respect to the Z and Y axes. Steps are shown for calculating stresses at each section.Read less