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Experimental study of an anti-icing method over an airfoil based on pulsed dielectric barrier discharge plasma 1451 was recorded by a CCD camera, and the surface temperature variation was captured by an infrared camera. The mechanism of DBD plasma anti-icing was investigated based on the tem- perature information. Finally, the power consumption of DBD anti-icing was estimated and compared with the results of some existing methods. 2. Experimental setup, instrumentation, and model Anti-icing experiments on an airfoil were conducted in the FL-61 icing wind tunnel located at the Aerodynamic Institute of Aviation Industry Corporation of China (AVIC). The tunnel is a closed-circuit continuous wind tunnel with a test sectional size of 0.6 m (width) 0.6 m (height). It can provide supercooled droplets of a Median Volume droplet Diameter (MVD) ranging from 15 lm to 50 lm by spraying atomized water into the tunnel circuit in the settling chamber. The wind tunnel flow has a Liquid Water Content (LWC) of 0.2 g/m3 to 3.0 g/m3 and a static temperature between 40 C and room temperature. Besides, the static pressure can vary from 39 kPa to 100 kPa, which can simulate a corresponding altitude from sea level to 7000 m. A schematic diagram of the icing wind tunnel is shown is Fig. 2. The model used in the experiments is an NACA0012 airfoil with a span of 600 mm and a chord length of 535 mm, which is made of Acrylonitrile-Butadiene-Styrene (ABS) for its good insulating and mechanical properties. A CTP-200 K pulsed low-temperature plasma power source was adopted in the experiments; its input voltage is 220 V and its output voltage can reach as high as 30 kV. The waveform of the output voltage is periodic with a period of microsecond order of magnitude and a frequency of 7–15 kHz. The maxi- mum output power is 1 kW. The power source has one high- voltage output monitor and two current output monitors. To detect the current, one current output monitor can output an instantaneous current on a 50 X sampling resistor, while the other can output a Lissajous figure via a 0.47 lF sampling capacitor. The experimental system is shown in Fig. 3. The NACA0012 airfoil was installed in the test section with a fixed angle of attack of 4. Two kinds of plasma actuators were mounted around the leading edge of the model. The covered electrodes of the two actuators are rectangular copper foils of 35 lm thickness, 153 mm length, and 87 mm width, respec- tively. The dielectric used in the actuators is ABS shells of 1 mm thickness, and is curved to conform to the shape of the model’s leading edge to minimize its influence on the model geometry. The only difference between the two kinds of actu- ators lies in that they have different geometric arrangements for their exposed electrodes. One geometric structure for the exposed electrode is a parallel layout in which 10 long straight striped copper electrodes are placed parallel to each other in the streamwise direction and connected parallel in an electrical sense (hereinafter referred to as ‘‘striped electrode”), where each striped electrode has a thickness of 35 lm, a width of 0.6 mm and a length of 133 mm, respectively, and the distance between each two adjacent electrodes is 6 mm (see Fig. 4). The other geometric structure, called ‘‘meshy electrode”, for the exposed electrode, which also has a thickness of 35 lm, is a squared-grid layout, where each squared cell has a size of 10 mm10mm, and each side of the cell has a width of 1mm (see Fig. 4). The electrodes mounted around the leading edge surface are actuated by the plasma power source. The striped electrode is a typical arrangement used in fluid flow control with the electrode lengthwise direction perpendicular to the free stream direction, whereas in the current experiments, the electrode lengthwise direction is in the streamwise direction. The meshy electrode increases the length of discharge edges in its lengthwise direction compared with the striped electrode in the same model surface area to make some difference in the arrangement. The voltage signals on the actuators were mea- sured and stored by an oscilloscope. The anti-icing process was recorded by a CCD camera which was mounted on the test section’s side-wall observation window, while the model surface temperature was measured and recorded by an infrared camera which was fixed on the test section’s top-wall observation window. 3. Experimental results Experiments were conducted under the condition of a free- stream velocity of 90 m/s, a static temperature of 7 C, an MVD of 20 lm, and an LWC of 0.5 g/m3. The peak-peak value of the pulsed voltage discharged from the exposed elec- trode was 17.79 kV with a frequency of 11.67 kHz in the striped-electrode case and 19.12kV with a frequency of 11.04 kHz in the meshy-electrode case. The waveforms of dis- charged voltages U are shown in Fig. 5, t is the time. When the test section flow was controlled to specified free- stream conditions, the plasma power source was turned on, and its parameters were adjusted to make the voltage of the actuator reach a preset value to discharge, and then the spray- ing system started at the same time when the anti-icing process started. Fig. 6 shows the anti-icing process of the striped electrode. In Fig. 6, before the spraying system started, the discharge glow from the striped electrode was bright and uniformly dis- tributed on both sides of each electrode. However, at the moment supercooled water droplets impacted on the leading edge just immediately after the spraying system started, the discharge glow at the leading edge disappeared as soon as the electrode was covered by a thin water film. Soon after- wards, the discharge glow reappeared gradually but with a lower brightness than before, and some areas were even fully dark without glow. At 30 s after the spraying started, the glow distribution became stable and began to remain unchanged. No ice accretion occurred on the area covered by the electrode, but other parts of the leading edge were covered by some ice crystals. As time went on, no ice accretion occurred on the area covered by the electrode, but the ice accretion on other areas of the leading edge grew thicker and thicker. Fig. 2 Schematic of FL-61 icing wind tunnel.PDF Image | Experimental study of an anti-icing method over an airfoil based on pulsed dielectric barrier discharge plasma
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