Design, fabrication, and testing of scaled wind tunnel model for the Smart Wing Phase II program

Christopher A. Martin; Lewis B. Scherer; John S. Flanagan; Bernie F. Carpenter

doi:10.1117/12.429681

14 June 2001 Design, fabrication, and testing of scaled wind tunnel model for the Smart Wing Phase II program

Christopher A. Martin, Lewis B. Scherer, John S. Flanagan, Bernie F. Carpenter

Proceedings Volume 4332, Smart Structures and Materials 2001: Industrial and Commercial Applications of Smart Structures Technologies; (2001) https://doi.org/10.1117/12.429681
Event: SPIE's 8th Annual International Symposium on Smart Structures and Materials, 2001, Newport Beach, CA, United States

Abstract

Building on the research performed during the DARPA / AFRL Smart Wing Phase 1 program to improve vehicle aerodynamic efficiency using control surfaces actuated by smart materials, the goal of the Phase 2, Test 1 effort was to increase the size of the model and the control surfaces and conduct wind tunnel tests at higher dynamic pressure and Mach number. This paper describes 1) model design for required safety and increased aileron effectiveness at high dynamic pressure; 2) model instrumentation; 3) SMA actuator control system design and implementation and 4) wind tunnel test results. Pictured below (Figure 1) is the model installed in the NASA Langley's Transonic Dynamic Tunnel (TDT).

Citation Download Citation

Christopher A. Martin, Lewis B. Scherer, John S. Flanagan, and Bernie F. Carpenter "Design, fabrication, and testing of scaled wind tunnel model for the Smart Wing Phase II program", Proc. SPIE 4332, Smart Structures and Materials 2001: Industrial and Commercial Applications of Smart Structures Technologies, (14 June 2001); https://doi.org/10.1117/12.429681

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