Plasma actuator: influence of dielectric surface temperature

Article English OPEN
Erfani, R. ; Zare-Behtash, H. ; Kontis, K. (2012)

Plasma actuators have become the topic of interest of many researchers for the purpose of flow control. They have the advantage of manipulating the flow without the need for any moving parts, a small surface profile which does not disturb the free stream flow, and the ability to switch them on or off depending on the particular situation (active flow control). Due to these characteristics they are becoming very popular for flow control over aircraft wings. The objective of the current study is to examine the effect of the actuator surface temperature on its performance. This is an important topic to understand when dealing with real life aircraft equipped with plasma actuators. The temperature variations encountered during a flight envelope may have adverse effects in actuator performance. A peltier heater along with dry ice are used to alter the actuator temperature, while particle image velocimetry (PIV) is utilised to analyse the flow field. The results show a significant change in the induced flow field by the actuator as the surface temperature is varied. It is found that for a constant peak-to-peak voltage the maximum velocity produced by the actuator depends directly on the dielectric surface temperature. The findings suggest that by changing the actuator temperature the performance can be maintained or even altered at different environmental conditions.
  • References (16)
    16 references, page 1 of 2

    CV1 CV2

    44(7):1572-1578, 2006. [12] C.C. Wang and S. Roy. Electrodynamic enhancement of film cooling of turbine blades. Journal

    of Applied Physics, 104(7):073305, 2008. [13] J. Huang, T.C. Corke, and F.O. Thomas. Plasma actuators for separation control of low-

    pressure turbine blades. AIAA Journal, 44(1):51-57, 2006. [14] M.L. Post and T.C. Corke. Separation control on high angle of attack airfoil using plasma

    actuators. AIAA Journal, 42(11):2177-2184, 2004. [15] S. Grundmann and C. Tropea. Delay of Boundary-Layer Transition Using Plasma Actuators.

    In 46th AIAA Aerospace Sciences Meeting and Exhibit, Paper Number AIAA-2008-1369, 2008. [16] C. He, T.C. Corke, and M.P. Patel. Plasma flaps and slats: an application of weakly ionized

    plasma actuators. Journal of Aircraft, 46(3):864-873, 2009. [17] M.L. Post and T.C. Corke. Separation control using plasma actuators: dynamic stall vortex

    control on oscillating airfoil. AIAA Journal, 44(12):3125-3135, 2006. [18] F.O. Thomas, A. Kozlov, and T.C. Corke. Plasma actuators for cylinder flow control and

    noise reduction. AIAA Journal, 46(8):1921-1931, 2008. [19] M.P. Patel, T.T. Ng, S. Vasudevan, T.C. Corke, and C. He. Plasma actuators for hingeless

    aerodynamic control of an unmanned air vehicle. Journal of Aircraft, 44(4):1264-1274, 2007. [20] B. Goksel, D. Greenblatt, I. Rechenberg, R. Bannasch, and C.O. Paschereit. Plasma Flow

  • Metrics
    No metrics available
Share - Bookmark