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Proceedings Paper

Design, fabrication, and testing of scaled wind tunnel model for the Smart Wing Phase II program
Author(s): Christopher A. Martin; Lewis B. Scherer; John S. Flanagan; Bernie F. Carpenter
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Paper 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).

Paper Details

Date Published: 14 June 2001
PDF: 8 pages
Proc. SPIE 4332, Smart Structures and Materials 2001: Industrial and Commercial Applications of Smart Structures Technologies, (14 June 2001); doi: 10.1117/12.429681
Show Author Affiliations
Christopher A. Martin, Northrop Grumman Corp. (United States)
Lewis B. Scherer, Northrop Grumman Corp. (United States)
John S. Flanagan, Northrop Grumman Corp. (United States)
Bernie F. Carpenter, Lockheed Martin Astronautics 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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