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).
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