Abstract
Discrete-time, linear quadratic methods were used to design feedback controllers for reducing tones generated by
flow over a cavity. The dynamics of a synthetic-jet actuator mounted at the leading edge of the cavity as observed by
two microphones in the cavity were modeled over a broad frequency range using state space models computed from
experimental data. Variations in closed loop performance as a function of model order, control order, control
bandwidth, and state estimator design were studied using a cavity in the Probe Calibration Tunnel at NASA Langley
Research Center. The controller successfully reduced the levels of multiple cavity tones at the tested flow speeds of
Mach 0.275, 0.35, and 0.45. In some cases, the closed loop results were limited by excitation of sidebands of the cavity
tones, or the creation of new tones at frequencies away from the cavity tones. The models were not able to account for
nonlinear dynamics, such as interactions between tones at different frequencies. Nonetheless, the results validate the
combination of optimal control and experimentally generated state space models for the cavity tone problem.
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