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Proceedings Paper

Aerodynamic and aeroelastic characteristics of the DARPA Smart Wing Phase II wind tunnel model
Author(s): Brian P. Sanders; Christopher A. Martin; David L. Cowan
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Paper Abstract

A wind tunnel demonstration was conducted on a scale model of an unmanned combat air vehicle (UCAV). The model was configured with traditional hinged control surfaces and control surfaces manufactured with embedded shape memory alloys. Control surfaces constructed with SMA wires enable a smooth and continuous deformation in both the spanwise and cordwise directions. This continuous shape results in some unique aerodynamic effects. Additionally, the stiffness distribution of the model was selected to understand the aeroelastic behavior of a wing designed with these control surfaces. The wind tunnel experiments showed that the aerodynamic performance of a wing constructed with these control surfaces is significantly improved. However, care must be taken when aeroelastic effects are considered since the wing will show a more rapid reduction in the roll moment due to increased moment arm about the elastic axis. It is shown, experimentally, that this adverse effect is easily counteracted using leading edge control surfaces.

Paper Details

Date Published: 14 June 2001
PDF: 9 pages
Proc. SPIE 4332, Smart Structures and Materials 2001: Industrial and Commercial Applications of Smart Structures Technologies, (14 June 2001); doi: 10.1117/12.429679
Show Author Affiliations
Brian P. Sanders, Air Force Research Lab. (United States)
Christopher A. Martin, Northrop Grumman Corp. (United States)
David L. Cowan, Boeing Co. (United States)


Published in SPIE Proceedings Vol. 4332:
Smart Structures and Materials 2001: Industrial and Commercial Applications of Smart Structures Technologies
Anna-Maria Rivas McGowan, Editor(s)

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