Control of aeroelastic response via synthetic jet actuators Conference Paper uri icon


  • Active control of aeroelastic response using synthetic jet actuators is considered. Flow control experiments conducted on the surface of the NACA 0015 airfoil in the water tunnel reveal that a motor-powered zero mass flux jet can eliminate separation, even in the post stall region. A digital Particle Image Velocimetry system is employed to quantitatively characterize the flow control. A novel, compact configuration of the synthetic jet actuator is prototyped for a wing section. The exit velocity of this actuator is measured using hot wire anemometry. Flow visualization and measurement is undertaken to characterize the shear layer flow on the NACA 0015 airfoil under limit cycle oscillations. The work involves the mounting and testing of a wing section with the synthetic jet actuator in a wind tunnel for suppressing aeroelastic flutter, limit cycle oscillations and control reversal. Initially, we focus on control reversal. © 2000 by the authors Published by the American Institute of Aeronautics and Astronautics, Inc.

name of conference

  • 41st Structures, Structural Dynamics, and Materials Conference and Exhibit

published proceedings

  • 41st Structures, Structural Dynamics, and Materials Conference and Exhibit

author list (cited authors)

  • Rao, P., Strganac, T., & Rediniotis, O.

citation count

  • 11

complete list of authors

  • Rao, Preetham||Strganac, Thomas||Rediniotis, Othon

publication date

  • April 2000