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Abstract
An experimental study was conducted to evaluate the anti-icing performance of NS-DBD plasma actuator under the conditions of airflow speed U = 65 m/s, ambient temperature T = −10 °C, liquid water content LWC = 0.5 g/m3, mean-volume diameter MVD = 25 μm, mainly to clarify the effect of pulse frequency and voltage amplitude of actuation on anti-icing performance. A NACA0012 airfoil model with a chord length of c = 280 mm was used in the tests. The NS-DBD plasma actuator was mounted at the front part of the airfoil. A FLIR infrared (IR) imager and CCD camera were used to record the anti-icing process of the NS-DBD plasma actuator. Two typical discharge conditions were selected for the anti-icing experiments. The first was HV-LF discharge, corresponding to discharge under higher voltage amplitude with lower pulse frequency; the second was LV-HF discharge, corresponding to discharge under lower voltage amplitude with higher pulse frequency. Results reveal that NS-DBD is a very promising method for anti-icing. With the same power consumption, the LV-HF discharge shows a better anti-icing performance compared to HV-LF discharge under the same icing conditions. In view of pulse duration and duty circle, combined with heat dissipation, it is suggested that there is a threshold frequency, corresponding to the voltage amplitude of electric actuation signal and the incoming flow condition, to achieve effective anti-icing performance.
Highlights
Icing can seriously threaten the safety and performance of aircraft [1,2]
The process of anti-icing and the surface temperature distribution of plasma actuator were analyzed through a CCD camera and infrared thermal imager, with the objective of exploring the anti-icing mechanism of NS-dielectric barrier discharge (DBD) plasma actuation
Experiments were conducted on the anti-icing performance of NS-DBD plasma actuator with two
Summary
Icing can seriously threaten the safety and performance of aircraft [1,2]. According to statistics from the AOPA Aviation Safety Foundation, in the decade between 1990 and 2000, about 3230 flight accidents occurred because of weather conditions, among which 388 were related to ice accretion, i.e., about 12% of the total [3]. Acting directly on the skin will work the through heating surface, causing a reduction in engine propulsion and affect service life ofthe the outer aircraft Both the hot air and the electric heating deicing efficiency systems work huge power consumption [11,12]. Anti-icing fluid technology would affect the carrying capacity of through heating the outer surface, causing a reduction in engine propulsion efficiency and huge power an aircraft [13]. Proposed the use of an AC-DBD plasma actuator for icing control; an experiment under the conditions of wind speed (15 m/s) and temperature (−10 ◦ C) was conducted to confirm the de-icing and anti-icing performances of plasma actuation. The anti-icing performance of NS-DBD plasma actuation and the influence of pulse frequency and voltage amplitude of electric actuation signal have not yet been evaluated. The process of anti-icing and the surface temperature distribution of plasma actuator were analyzed through a CCD camera and infrared thermal imager, with the objective of exploring the anti-icing mechanism of NS-DBD plasma actuation
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