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The increasing process of the surface temperature undergoes three near linear phases. At the first instance of plasma formation, the temperature increasing rate can reach 24 ◦C/s at Vp−p = 15 kV. The surface temperature of the actuator is determined by the plasma rotational temperature. For the plasma deicing test, the ice layer of 5 mm thickness was completely deleted from the surface of the cylinder model after plasma actuating on about 150 s. For the plasma anti-icing test, there no ice accretion on the surface of the cylinder model once the plasma is activated and after 180 s duration of the plasma actuation. The minimum active power consumption of unit area for anti-icing test is about 13 kW/m2. It shows that the plasma actuation has a good anti-icing performance with relative low power consumption. The introduced plasma icing control approach thus appears highly promising and will be further inves- tigated. For instance, the future work will investigate the mechanism for plasma de- and anti-icing. The optimization of plasma actuator distribution and the control mode will be studied. Furthermore, the cur- rent study will also be extended to include airfoil and nacelle geometries to examine the de- and anti-icing performance for realistic configurations. Acknowledgements This work is supported by the National Natural Science Foundation of China (51107101), the NPU Foundation for Fundamental Research (310201401JCQ01003), and the Nation Key Laboratory Research Foundation of China (9140C420301110C42). References 1Petty, K. R. and Floyd, C. D. J., “A Statistical Review of Aviation Airframe Icing Accidents in the US,” National Transportation Safety Board, 2004. 2Li, H., Waldman, R. M., and Hu, H., “An Experimental Investigation on Unsteady Heat Transfer and Transient Icing Process upon Impingement of Water Droplets,” AIAA Paper 2016-0510, 2016. 3Nagappan, N., Golubev, V. V., and Habashi, W. G., “Parametric Analysis of Icing Control Using Synthetic Jet Actua- tors,” AIAA Paper 2013-2453, 2013. 4Boeke, F. L. and Paselk, R. A., “Icing Problems and the Thermal Anti-Icing System,” AIAA Journal, Vol. 13, No. 9, 1946, pp. 485–497. 5Pourbagian, M., Talgorn, B., Habashi, W., Kokkolaras, M., and Digabel, S. L., “On power optimization of aircraft electro-thermal anti-icing systems,” G-2014-72, 2014. 6Thomas, S. K., Cassoni, R. P., and MacArthur, C. D., “Aircraft anti-icing and de-icing techniques and modeling,” Journal of Aircraft, Vol. 33, No. 5, 1996, pp. 841–854. 7Pellissier, M., Habashi, W. G., and Pueyo, A., “Design optimization of hot-air anti-icing systems by FENSAP-ICE,” AIAA Paper 2010-1238, 2010. 8Dong, W., Zhu, J., Zheng, M., , and Y.Chen, “Thermal Analysis and Testing of a Cone with Leading Edge Hot Air Anti-icing System,” AIAA Paper 2014-0739, 2014. 9Corke, T. C., Enloe, C. L., and Wilkinson, S. P., “Dielectric Barrier Discharge plasma actuators for flow control,” Annual Review of Fluid Mechanics, Vol. 42, 2010, pp. 505–529. 10Moreau, E., “Airflow control by non thermal plasma actuators,” Journal of Physics D : Applied Physics, Vol. 40, No. 3, 2007, pp. 605–636. 11Little, J. C., Takashima, K., and Nishihara, M., “Separation Control with Nanosecond Pulse Driven Dielectric Barrier Discharge Plasma Actuators,” AIAA Journal, Vol. 50, No. 2, 2012, pp. 350–365. 12Wu, Y. and Li, Y., “Progress and Outlook of Plasma Flow Control,” ACTA AERONAUTICA ET ASTRONAUTICA SINICA, Vol. 36, No. 2, 2015, pp. 381–405. 13Wang, J., Choi, K. S., Feng, L., Jukesb, T. N., and Whalley, R. D., “Recent devel-opments in DBD plasma flow control,” Progress in Aerospace Sciences, Vol. 62, 2013, pp. 52–78. 14Luo, Z., Xia, Z., and Liu, B., “New Generation of Synthetic Jet Actuators,” AIAA Journal, Vol. 44, No. 10, 2006, pp. 2418–2420. 15Joussot, R., Hong, D., Rabat, H., Boucinha, V., Rozenbaum, R. W., and Chesneau, A. L., “Thermal Characterization of a DBD Plasma Actuator: Dielectric Temperature Measurements using Infrared Thermography,” AIAA Paper 2010-5102, 2010. 16Stanfield, S. A. and Menart, J., “Rotational and vibrational temperatures for a dielectric barrier discharge in air using emission spectroscopy,” AIAA Paper 2007-3876, 2007. 17Dong, B., Bauchire, J. M., Pouvesle, J. M., Magnier, P., and Hong, D., “Experimental study of a DBD surface discharge for the active flow control of subsonic airflow,” Journal of Physics D: Applied Physics, Vol. 41, No. 15, 2008, pp. 1–9. 18Jukes, T. N., Choi, K.-S., Segawa, T., and Yoshida, H., “Jet flow induced by a surface plasma actuator,” Proceedings of the Institution of Mechanical Engineers - Part I , Vol. 222, No. I5, 2007, pp. 347–356. 19Winkel, R., Correale, G., and Kotsonis, M., “Effect of dielectric material on thermal effect produced by ns-DBD plasma actuator,” AIAA Paper 2014-2119, 2014. 13 of 14 American Institute of Aeronautics and Astronautics Downloaded by NORTHWESTERN POLYTECHICAL UNIV. on June 23, 2016 | http://arc.aiaa.org | DOI: 10.2514/6.2016-4019PDF Image | Experimental Study of Deicing and Anti-icing on a Cylinder by DBD Plasma Actuation
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