Abstract
The drive for more fuel efficient transports is pushing designs to higher aspect ratio light weight configurations which are more flexible than in the past. A promising configuration to reduce weight and enable high aspect ratio wings is a truss braced wing (TBW). In Phase II of the NASA Subsonic Ultra Green Research (SUGAR) contract a truss braced wing (TBW) configuration was studied for future 737 size transports. This paper presents a summary of the FEM based aeroelastic analysis preformed in Phase II. The analysis included structural optimization using strength, buckling, and flutter constraints. A dynamically scaled aeroelastic wind tunnel test was completed in NASA’s Transonic Dynamics Tunnel. A discussion of setting requirements for the test and a brief description of the wind tunnel model will be included. Wind tunnel test results will be summarized including the result that the TBW flutter boundary is non-linear and varied at different tested angles of attack. This result has been modeled with structural non-linear preload and large displacement effects. A discussion of the implications to vehicle design and test caused by non-linear stability is included. Structural weight benefits of a TBW will be shown along with a linear and non-linear flutter weight penalty.
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