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Aeroelastic Scaling of a Joined Wing Sensorcraft Concept

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Final rept. 30 Sep 2005-24 Jun 2009

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This report results from a contract tasking Instituto Superior Tecnico as follows The Grantee will investigate the aeroelastic performance of the joined wing concept. Dr. Suleman and his research team have proposed to investigate the aeroelastic performance of the joined wing concept by analyzing, designing, manufacturing, and wind tunnel testing a aeroelastically scaled models. The first step will include designing a test assembly to conduct aeroelastic flutter and gust response tests. A fairly flexible wing with low bending and torsion mode frequencies is envisioned in order to study the aeroelastic phenomena in a low subsonic regime. The structure of the joined wing will be analyzed in order to determine its vibrational behavior. Design aspects to be considered include the spanwise loadings and the design of wing camber and twist. A comparison of experimental and computational results will be conducted. Nonlinear structural issues will also be addressed. In order to predict the post-buckling behavior of the joined-wing structure, this task will concentrate on the development of higher-order geometric nonlinearity models for the joined-wing concept. Appropriate criteria will be determined for a stiffness and weight effects on vehicle handling and flutter, and b ultimate strength and stability c skin postbuckling and stringer column buckling of skinstringer configurations, and d critical damage conditions associated with ultimate strength.

Subject Categories:

  • Research and Experimental Aircraft
  • Test Facilities, Equipment and Methods
  • Fluid Mechanics

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