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CLOSED-LOOP FEEDBACK CONTROL OF THE TURBULENT FLOW OVER A NACA-4412 AIRFOIL

Julie M. Ausseur
Department of Mechanical and Aerospace Engineering Syracuse University Syracuse, NY 13244, USA

Jeremy T. Pinier
Department of Mechanical and Aerospace Engineering Syracuse University Syracuse, NY 13244, USA

Mark N. Glauser
Department of Mechanical and Aerospace Engineering Syracuse University Syracuse, NY 13244, USA

Hiroshi Higuchi
Department of Mechanical, Aerospace and Manufacturing Engineering, Syracuse University, Syracuse, New York 13244-1240, USA

Resumo

We are developing methods to predict the dynamics of the flow field above a NACA-4412 airfoil using real-time measurements of the pressure from the surface of the airfoil only. Through Proper Orthogonal Decomposition (POD) and modified Linear Stochastic Measurement (mLSM) low-dimensional techniques (Lumley (1967), Adrian (1975), Taylor & Glauser (2004)) these pressure measurements are coupled to Particle Image Velocimetry (PIV) data of the flow to estimate the time dependent coefficients describing the flow. Based on a least-squares technique applied to the POD spatial modes, we obtain a system of ODEs that are solved to get the time-evolution of the POD coefficients, whereby an estimate of the evolution equation of the flow is obtained. This low-dimensional estimated plant will be used to explore different Proportional, Integral & Derivative (PID) control parameters and will enable us to implement a controller of the flow state above the airfoil using leading-edge zero net-mass flow actuators while pitching the airfoil.