Abstract
The application of active flow control via synthetic jet actuators for separation and roll control on a scaled Cessna 182 model was investigated experimentally in a low-speed wind tunnel. The model was instrumented with either ailerons or synthetic jets embedded within the outer portion of the wings' span, in lieu of ailerons. Force and moment measurements were performed for various aileron deflections and synthetic jet momentum coefficients (on either both wingtips or only on one). The sensor's rms output was monitored in real time by a computer. When the rms reached a predetermined threshold value, the computer automatically turned on the synthetic jet actuators. Using the appropriate threshold value resulted in complete avoidance of wingtip stall at the angle of attack where separation would have occurred. In addition, the shear stress sensor and wind tunnel force data were used to identify the system dynamics
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