9 July 1999 DARPA/ARFL/NASA Smart Wing second wind tunnel test results
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To quantify the benefits of smart materials and structures adaptive wing technology. Northrop Grumman Corp. built and tested two 16 percent scale wind tunnel models of a fighter/attach aircraft under the DARPA/AFRL/NASA Smart Materials and Structures Development - Smart Wing Phase 1. Performance gains quantified included increased pitching moment, increased rolling moment and improved pressure distribution. The benefits were obtained for hingeless, contoured trailing edge control surfaces with embedded shape memory alloy wires and spanwise wing twist effected by SMA torque tube mechanism, compared to convention hinged control surfaces. This paper presents an overview of the results from the second wind tunnel test performed at the NASA Langley Research Center's 16 ft Transonic Dynamic Tunnel in June 1998. Successful results obtained were: 1) 5 degrees of spanwise twist and 8-12 percent increase in rolling moment utilizing a single SMA torque tube, 2) 12 degrees of deflection, and 10 percent increase in rolling moment due to hingeless, contoured aileron, and 3) demonstration of optical techniques for measuring spanwise twist and deflected shape.
© (1999) COPYRIGHT Society of Photo-Optical Instrumentation Engineers (SPIE). Downloading of the abstract is permitted for personal use only.
Lewis B. Scherer, Lewis B. Scherer, Christopher A. Martin, Christopher A. Martin, Mark N. West, Mark N. West, Jennifer P. Florance, Jennifer P. Florance, Carol D. Wieseman, Carol D. Wieseman, Alpheus W. Burner, Alpheus W. Burner, Gary A. Fleming, Gary A. Fleming, } "DARPA/ARFL/NASA Smart Wing second wind tunnel test results", Proc. SPIE 3674, Smart Structures and Materials 1999: Industrial and Commercial Applications of Smart Structures Technologies, (9 July 1999); doi: 10.1117/12.351563; https://doi.org/10.1117/12.351563

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