Design, fabrication, and testing of the DARPA/Wright Lab 'smart wing' wind tunnel model

Abstract

The concept of an adaptive aircraft wing, i.e., whose shape parameters such as camber, span-wise twist, and thickness can be varied to optimize the wing shape for various flight conditions, has been extensively studied by numerous researchers [1-8]. While the aerodynamic benefits (in terms of increased lift/drag ratios, improved maneuverability, and delayed flow separation) have been analytically and experimentally established, the complexity and weight penalty of the designs and actuation mechanisms have limited their practical implementation. Recent developments in sensors and actuators using materials could potentially alleviate the shortcomings of prior designs, leading the way to a more practical smart adaptive wing which responds to changes in flight and environmental conditions by optimally modifying its shape. This paper presents the results of recent work conducted under a Defense Advanced Research Projects Agency (DARPA) contract entitled Structures and Materials Development - Smart Wing. In particular, development and testing of the wing wind tunnel model are presented. Limitations and potential benefits of adaptive wing designs are also discussed, along with recommendations for future work required to develop an operational adaptive wing.