The objectives of this investigation have been to design a variable camber system, establish its performance capabilities and provide data to support a decision for flight demonstration. This report describes the structural loads and stress calculations. The variable camber wing consists of leading and trailing edge flaps that can be deflected to match the camber requirements of any flight condition. Wing leading and trailing edge flaps with flexible skins, combined with a simple internal mechanism, are used to achieve smoothly curved upper surfaces so that an optimum wing shape can be provided throughout the flight spectrum.


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