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Aerodynamic and Thermal Effects of Plasma Actuators on Anti-icing over an Airfoil

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The Proceedings of the 2018 Asia-Pacific International Symposium on Aerospace Technology (APISAT 2018) (APISAT 2018)

Part of the book series: Lecture Notes in Electrical Engineering ((LNEE,volume 459))

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Abstract

An anti-icing application of AC-SDBD plasma actuator has been explored through experiments. The purpose of this study is to study both the thermal and aerodynamic effects on plasma anti-icing. Two types of multi-SDBD actuators were designed with different induced flow directions. One type (Type-1) is designed to generate an induced flow with direction same to the incoming flow, while the other (Type-2) is used to generate an induced flow with an opposite direction to the incoming flow. The anti-icing tests were carried out in an icing-wind-tunnel. The ice accretion and corresponding surface temperature have been recorded using a high-speed digital camera and infrared imaging system respectively. The results show that the Type-1 actuator can ensure that the leading edge of the airfoil remained smooth and did not have the ice accretion, while the Type-2 actuator had ice accumulation on the leading edge, but it can effectively postpone the ice location on the upper surface of the airfoil. Such results show that the anti-icing effects are directly related to both the thermal and aerodynamic effects of the DBD plasma actuator.

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Abbreviations

AoA :

= Angle of attack, deg

A p :

= Surface area of multi-SDBD plasma actuator, m2

A a :

= Surface area without ice accretion on the plasma-on side, m2

c :

= Chord length, m

F :

= Frequency of AC waveform, kHz

I :

= Current, A

LWC :

= Liquid water content, g/m3

P :

= Power consumption, W

P t :

= Power evolution, W

P I :

= Instantaneous power, kW

q :

= Power density, kW/m2

Re :

= Chord Reynolds number without water pray

SDBD :

= Surface Dielectric Barrier Discharge

t :

= Time, s

T ∞ :

= Air static temperature, °C

T :

= Surface temperature, °C

U ∞ :

= Freestream velocity, m/s

V p- p :

= Peak-to-peak voltage amplitude of the source, kV

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Acknowledgments

This work is supported by the National Natural Science Foundation of China (Grant Nos. 11672245), the National Key Laboratory Research Foundation of China (Grant No. 9140C420301110C42), the Fundamental Research Funds for the Central Universities (3102018JCC008), and the 111 Project (B17037). The authors are grateful to Dr. Yang Liu and Wenwu Zhou, Iowa State University for their helps on this research.

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Authors and Affiliations

  1. Department of Fluid Mechanics, Northwestern Polytechnical University, Xi’an, 710072, China

    Chang Li, Haiyang Hu, Xuanshi Meng & Jinsheng Cai

  2. Department of Aerospace Engineering, Iowa State University, Ames, IA, 50011, USA

    Haiyang Hu & Hui Hu

Authors
  1. Chang Li
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  2. Haiyang Hu
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  3. Xuanshi Meng
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  4. Jinsheng Cai
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  5. Hui Hu
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Corresponding author

Correspondence to Xuanshi Meng .

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Editors and Affiliations

  1. Chinese Society of Aeronautics and Astronautics, Beijing, Beijing, China

    Xinguo Zhang

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Li, C., Hu, H., Meng, X., Cai, J., Hu, H. (2019). Aerodynamic and Thermal Effects of Plasma Actuators on Anti-icing over an Airfoil. In: Zhang, X. (eds) The Proceedings of the 2018 Asia-Pacific International Symposium on Aerospace Technology (APISAT 2018). APISAT 2018. Lecture Notes in Electrical Engineering, vol 459. Springer, Singapore. https://doi.org/10.1007/978-981-13-3305-7_81

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  • DOI: https://doi.org/10.1007/978-981-13-3305-7_81

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  • Publisher Name: Springer, Singapore

  • Print ISBN: 978-981-13-3304-0

  • Online ISBN: 978-981-13-3305-7

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