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enamel coating and wet sanded to a smooth surface by using 2000- grit sand paper. During the experiments, the DBD plasma actuators on the left side of the airfoil/wing model were powered by a high-voltage alternating current power source (Nanjing Suman Company, model CTP- 2000 K) with an output voltage of Vp−p 6.71 kV (i.e., peak-to- peak value) and a constant frequency of f 8.9 kHz. Although the ac current was measured by using a high-response current probe (Pearson Electronics, Inc., model Pearson 2877), the voltage was monitored by using an oscilloscope (Tektronix DPO3054). Following the work of Dong et al. [25], the power inputs P to the ac DBD plasma actuators were calculated, which were found to be P 102 W for the present study. The corresponding power density (q P∕Ap) was found to be 25.3 kW∕m2, where Ap was the covered area of the plasma actuators (i.e., 96 × 42 mm). In the present study, a high-speed imaging system (PCO Tech, Dimax, with a spatial resolution of 2000 by 2000 pixels) along with a 60 mm optical lens (Nikon, 60 mm Nikkor 2.8D) were used to record the dynamic ice-accretion process over the pressure side of the airfoil surface. As shown schematically in Fig. 1, the high-speed imaging system was mounted above the airfoil/wing model with a measurement window size of 210 × 210 mm (i.e., with a spatial resolution of 9.5 pixels∕mm) to record the ice-accretion or water runback process over both the plasma-on and plasma-off sides of the airfoil surfaces simultaneously. An infrared (IR) thermal imaging system (FLIR-A615) was used to map the corresponding temperature distributions over the surface of the airfoil/wing model during the ice-accretion process simultaneously. The measurement uncertainty for the IR thermal imaging system was estimated to be within 0.50°C. For acquiring the IR thermal images, an infrared emission transmissible window (FLIR IR Window-IRW-4C) was embedded on the top plate of the ISU-IRT test section. The IR thermal imaging system was focused on the front portion (i.e., the region near the airfoil leading edge) of the airfoil/wind model with a measurement window size of 110 × 90 mm. As a result, the spatial resolution of the IR thermal images was 5.3 pixels∕mm. Before conducting the ice-accretion experiment, an in situ calibration experiment was performed to validate the IR thermal imaging system by using high-precision thermocouples in the range of 20 to −20°C. The differences between the measurement results of the IR thermal imaging system and those of the thermocouples were found to be within 0.50°C. During the experiment, both the high-speed imaging system and the IR thermal imaging system were connected to a digital delay generator (Berkeley Nucleonics, model 575) to Fig. 3 airfoil surface under the glaze-icing conditions of U∞ 40 m∕s, T∞ −5°C, and LWC 1.50 g∕m3. ZHOU ET AL. 1099 Fig. 2 Schematic of airfoil/wing model used in the present study. synchronize the timing for the image acquisitions after switching on the spray system of the ISU-IRT to start the ice-accretion process. III. Measurement Results and Discussions A. Effects of Plasma Generation on Ice-Accretion Under Glaze-Icing Conditions In performing the ice-accretion experiments, the ISU-IRT was operatedataprescribedfrozentemperaturelevel(e.g.,T∞ −5and −15°C for the present study) for at least 20 min in order to ensure the ISU-IRT reaching a thermal steady state. Then, the DBD plasma actuators embedded over the left side of the airfoil/wind model were switched on for about 10 s before turning on the water spray system of the ISU-IRT. After the water spray system was switched on at t 0 s, the supercooled water droplets carried by the incoming airflow would impinge onto the surface of the airfoil/wing model to start the ice-accretion process. During the experiments, the high- speed imaging system and the IR thermal imaging system were synchronized with the switch of the ISU-IRT water spray system to reveal the dynamic ice-accretion process over the airfoil surface simultaneously. Figure 3 shows four typical snapshots of the instantaneous ice- accretion images acquired by using the high-speed imaging system under the glaze-icing condition of U∞ 40 m∕s, T∞ −5°C, and LWC 1.50 g∕m3. The box in red dashed lines in Fig. 3 indicates the measurement window of the IR thermal imaging system, and the corresponding surface temperature distributions measured simulta- neously by using the IR thermal imaging system are given in Fig. 4. Note that, because very similar features were also observed for other test cases, only the measurement results obtained under the test condition of LWC 1.5 g∕m3 were shown and analyzed here for conciseness. As shown clearly in Fig. 3a, at the very beginning of the ice- accretion experiment (i.e., at the time instance of t 0.3 s), although Typical snapshots of the dynamic ice-accretion process over the Downloaded by IOWA STATE UNIVERSITY on October 5, 2018 | http://arc.aiaa.org | DOI: 10.2514/1.J056358PDF Image | Utilization of Thermal Effect Induced by Plasma Generation for Aircraft Icing Mitigation
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