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1100 ZHOU ET AL. Fig. 4 Corresponding surface temperature distributions over the plasma-on and plasma-off sides of the airfoil surface under the glaze-icing conditions of U∞ 40 m∕s, T∞ −5°C, and LWC 1.50 g∕m3. no obvious ice accretion was observed on both the plasma-on side and plasma-off sides of the airfoil surface in the snapshot image acquired by using the high-speed imaging system, the measured surface temperature distributions over the plasma-on side of the airfoil surface were found to be significantly different from those of the plasma-off side. As revealed clearly from the measured surface temperature distributions given in Fig. 4a, due to the release of the latent heat associated with the solidification process of the impinged supercooled water droplets over the airfoil surface (i.e., phase changing process from liquid state of water to solid state of ice), the surface temperatures in the region near the airfoil leading edge (i.e., the direct impinging region of the supercooled water droplets) on the plasma-off side of the airfoil surface were found to increase slightly (i.e., airfoil surface temperatures were found to increase from −5.0 up to −3.0°C), as expected. Because the surface temperatures were still found to be below the “frozen temperature” of water (i.e., Tw < 0°C), a thin layer of ice would be formed immediately after the supercooled water droplets impinged onto the plasma-off side of the airfoil surface. Because the ice layer formed over the airfoil surface was very thin at the time instance of t 0.3 s, it was almost unobservable in the snapshot image acquired by the high-speed imaging system given in Fig. 3a. However, as revealed clearly in the measured surface temperature distributions given in Fig. 4, due to the thermal effect induced by the DBD plasma generation as described by Joussot et al. [22], the surface temperature on the plasma-on side of the airfoil model was found to be well above the frozen temperature of water (i.e., Tw > 0°C). It suggests that, upon impinging onto the plasma-on side of the airfoil surface, the supercooled water droplets would be heated up. As a result, a layer of “warm” water film, instead of ice, would be formed over the airfoil surface. Thus, no ice was found to form over the plasma-on side of the airfoil surface, as shown clearly in Fig. 3. As the ice-accretion experiment went on, more supercooled water droplets carried by the incoming airflow would impinge onto the airfoil surface. Due to the relatively warm temperature (i.e., T∞ −5°C) and high LWC level (i.e., LWC 1.5 g∕m3) of the incoming airflow for this test case, the icing process over the airfoil surface would be of typical glaze-ice accretion if no anti-/deicing measures were applied. Similar to the scenario described by Waldman and Hu [7], with the continuous impingement of the supercooled water droplets onto the airfoil surface, more and more latent heat of fusion would be released to cause the slight temperature increase on the plasma-off side of the airfoil surface, as revealed quantitatively from the measured surface temperature distributions shown in Fig. 4. Because the heat transfer process was not fast enough to remove all of the released latent heat of fusion from the liquid water for this test case, only a portion of the impinged supercooled water droplets would be frozen into solid ice upon impacting onto the airfoil surface. The rest of the impinged water mass was found to stay in liquid state. As shown clearly at the plasma-off side of the acquired image given in Fig. 3b (i.e., the snapshot at the time instance of t 12.0 s), as driven by the boundary-layer airflow above the airfoil surface, the unfrozen water film flow was found to run back and form multiple fingerlike rivulet structures in the further downstream region. It also can be seen clearly that the runback surface water on the plasma-off side was found to eventually be frozen into solid ice at the further downstream region (i.e., in the region beyond of the direct impingement area of the supercooled water droplets). However, as shown in the snapshot image given in Fig. 3b, the left side (i.e., plasma-on side) of the airfoil surface was still found to be completely free of ice, due to the thermal effects induced by the DBD plasma generation. The surface temperature distributions given in Fig. 4 revealed quantitatively that the surface temperatures on the plasma-on side of the airfoil model were still well above the frozen temperature of water (i.e., Tw > 0°C). Especially in the regions where the plasma actuators were embedded, the local surface temperature was found to reach up to 15°C. As a result, instead of 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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