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Stall Control by Plasma Actuators: Characterization along the Airfoil Span

Author

Listed:
  • Giulia Zoppini

    (Department of Aerodynamics, TU Delft, Leeghwaterstraat 42, 2628 CA Delft, The Netherlands)

  • Marco Belan

    (DAER, Politecnico di Milano, Via La Masa 39, 20156 Milano, Italy)

  • Alex Zanotti

    (DAER, Politecnico di Milano, Via La Masa 39, 20156 Milano, Italy)

  • Lorenzo Di Vinci

    (DAER, Politecnico di Milano, Via La Masa 39, 20156 Milano, Italy)

  • Giuseppe Campanardi

    (DAER, Politecnico di Milano, Via La Masa 39, 20156 Milano, Italy)

Abstract

A dielectric barrier discharge actuator (DBD) is considered and studied as a stall recovery device. The DBD is installed on the nose of a NACA0015 airfoil with chord × span 300 × 930 mm. The geometry of the exposed electrode has periodic triangular tips purposely designed for the case under study. Wind tunnel tests have been carried out over a range of airspeeds up to 35 m/s with a Reynolds number of 700 k. The flow morphology has been characterized by means of the particle image velocimetry technique, obtaining velocity fields and pressure coefficients. By exploring different planes along the model span, the three-dimensional effect of the DBD has been reconstructed, identifying the flow region mainly sensitive to the plasma actuation. Finally, the actuator effectiveness has been quantified accounting for the power consumption data, leading to defining further design improvements in view of a better efficiency.

Suggested Citation

  • Giulia Zoppini & Marco Belan & Alex Zanotti & Lorenzo Di Vinci & Giuseppe Campanardi, 2020. "Stall Control by Plasma Actuators: Characterization along the Airfoil Span," Energies, MDPI, vol. 13(6), pages 1-20, March.
    • Handle: RePEc:gam:jeners:v:13:y:2020:i:6:p:1374-:d:333101
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