Abstract:
A continuous solution is derived for the stress distribution in a simple wing surface represented by a uniformly reinforced stri p bounded by equal constant area edge members, when the sections in the airstream experience a uniform temperature rise. The section shielded by the fuselage is assumed to remain at a constant temperature. This analysis, which takes into account the bending, shear and direct stiffness of the edge members, is used to evaluate the shear stress distribution in a specific strip used as an example. The stress distribution in this same specimen strip is also calculated by the Argyris matrix force method assuming a finite spanwise temperature gradient at the edges of the fuselage, both for a constant chordwise temperature and for a parabolic chordwise temperature variation in the airstream.
