An Experimental Investigation on the Thermal Effects of NS-DBD and AC-DBD Plasma Actuators for Aircraft Icing Mitigation Conference Paper uri icon

abstract

  • © 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. Ice accretion on airframe surfaces occurs as aircraft come across supercooled water droplets in the cloud, which was found to greatly influence the flight performance and safety. In the present study, the thermal effect induced by DBD plasma actuation was experimentally investigated in order to explore its potential as an alternative strategy to current anti-/de-icing methods for aircraft icing mitigation. A series of experiments were conducted in the Iowa State University Icing Research Tunnel (ISU-IRT) with a NACA0012 airfoil/wing model embedded with DBD plasma actuators. During the experiments, in addition to recording the dynamic ice accretion process by using a high-speed imaging system, the quantitative surface temperature measurements were also obtained using an Infra-Red (IR) thermal imaging system. The thermal effects induced by conventional AC-DBD and nanosecond pulsed DBD (i.e., ns-DBD) plasma actuators were compared under the same power input and icing test conditions. The dynamic icing process was also investigated with the ns-DBD plasma actuation under different pulse repetition frequencies. It was found that the anti-/de-icing performance of ns-DBD plasma actuation would improve with increasing pulse repetition frequency.

author list (cited authors)

  • Kolbakir, C., Liu, Y., Hu, H., Starikovskiy, A., & Miles, R. B.

citation count

  • 12
  • 9

publication date

  • January 2018