Closed-Loop Feedback Control Algorithms for Flow Control over NACA 0015 Airfoil

摘要

This study investigates control algorithm for closed-loop feedback control system design aimed at reduction of turbulent flow separation over a NACA 0015 airfoil equipped with leading-edge synthetic jet actuators (SJAs). The algorithm employs system identification technique based on Nonlinear Auto Regressive Moving Average with exogenous inputs (NARMAX) method to model nonlinear dynamics of the flow and design controller for single-input single-output systems. The resulting closed loop response tracks the desired pressure value and significant improvement in the transient response over the open-loop system at high angles of attack is realized.