Closed-Loop Stall Control System

摘要

A closed-loop, stall sense and control system was demonstrated on a morphing airfoil. The FlexSys, Inc. MissionnAdaptive Compliant Wing was modified to accept a Boeing Co. dielectric barrier discharge actuator panel in anlocation immediately upstream of the trailing-edge morphing flap, and hot-film sensors were installed on the modelnsurface. A signal analysis algorithm, developed by Tao Systems, Inc., was applied to the hot-film signals to detectnseparation and trigger activation of the dielectric barrier discharge actuators. The system was successfullyndemonstrated in the U.S. Air Force Research Laboratory Phillip P. Antonatos Subsonic Aerodynamics ResearchnLaboratory wind-tunnel facility, and an improvement in lift of about 10% was observed at Mach 0.05 (chordnReynolds number 9 u0001 105n) under closed-loop control and a turbulent boundary-layer state. Actuator effectivenessnwas demonstrated up toMach 0.1, butmust be extended toMach 0.2–0.3 to enable a practical stall control systemforntakeoff and approach of large aircraft. It may be possible to obtain that level of performance by optimizing thenactuator locations and input waveforms.