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Publication Title | Experimental study of an anti-icing method over an airfoil based on pulsed dielectric barrier discharge plasma

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Chinese Journal of Aeronautics, (2018), 31(7): 1449–1460
Chinese Society of Aeronautics and Astronautics & Beihang University
Chinese Journal of Aeronautics
cja@buaa.edu.cn
www.sciencedirect.com
Experimental study of an anti-icing method over an airfoil based on pulsed dielectric barrier discharge plasma
Yongqiang TIAN, Zhengke ZHANG, Jinsheng CAI *, Leilei YANG, Lei KANG National Key Laboratory of Science and Technology on Aerodynamical Design and Research, Northwestern Polytechnical
University, Xi’an 710072, China
Received 30 June 2017; revised 30 October 2017; accepted 9 January 2018 Available online 19 May 2018
KEYWORDS
Anti-icing;
Icing wind tunnel; Lissajous figures; Plasma actuator; Pulsed dielectric barrier discharge
Abstract Aircraft icing has long been a plague to aviation for its serious threat to flight safety. Even though lots of methods for anti-icing have been in use or studied for quite a long time, new methods are still in great demand for both civil and military aircraft. The current study in this paper uses widely used Dielectric Barrier Discharge (DBD) plasma actuation to anti-ice on a NACA0012 airfoil model with a chord length of 53.5 cm in a closed-circuit icing wind tunnel. An actuator was installed at the leading edge of the airfoil model, and actuated by a pulsed low-temperature plasma power source. The actuator has two types of layout, a striped electrode layout and a meshy electrode layout. The ice accretion process or anti-icing process was recorded by a CCD camera and an infrared cam- era. Instantaneous pictures and infrared contours show that both types of DBD plasma actuators have the ability for anti-ice under a freestream velocity of 90 m/s, a static temperature of 7 C, an Median Volume droplet Diameter (MVD) of 20 lm, and an Liquid Water Content (LWC) of 0.5 g/m3. The detected variations of temperatures with time at specific locations reveal that the tem- peratures oscillate for some time after spraying at first, and then tend to be nearly constant values. This shows that the key point of the anti-icing mechanism with DBD plasma actuation is to achieve a thermal equilibrium on the model surface. Besides, the power consumption in the anti-icing process was estimated in this paper by Lissajous figures measured by an oscilloscope, and it is lower than those of existing anti-icing methods. The experimental results presented in this paper indicate that the DBD plasma anti-icing method is a promising technique in the future.
! 2018 Chinese Society of Aeronautics and Astronautics. Production and hosting by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/).
* Corresponding author.
E-mail addresses: 904173655@qq.com (Y. TIAN), jcai@nwpu.edu. cn (J. CAI).
Peer review under responsibility of Editorial Committee of CJA.
Production and hosting by Elsevier
https://doi.org/10.1016/j.cja.2018.05.008
1. Introduction
Aircraft icing can occur both on ground and in flight under icing conditions. Typical ground icing types are slush, clear ice, and a combination of the two, which are usually caused by snow or freezing rain falling on the aircraft surface.
1000-9361 ! 2018 Chinese Society of Aeronautics and Astronautics. Production and hosting by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/).

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