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Aerospace 2020, 7, 123 11 of 15 0.0 80.0 [m/s] 10%c (a) Clean airfoil (b) Case 1 (c) Case 4 (d) Case 10 Figure 9. Streamline and icing shapes around the NACA 0012 airfoil. The color of the streamline indicates the velocity magnitude; the white and dark gray regions on the airfoil surface indicate the formed ice and heater location, respectively: (a) clean airfoil without icing; (b) Case 1; (c) Case 4; and, (d) Case 10. Figure 11 shows the pressure coefficients on the airfoil surface for Cases 1, 4, and 10, along with those of the clean airfoil. The upper and lower blanches are the pressure and suction sides, respectively. For the clean airfoil, the pressure coefficient peaked at x/c ≈ 0: on the pressure side, then gradually decreased and converged to a slightly negative value. On the suction side, the pressure coefficient suddenly decreased and gradually increased. In Case 1, the pressure coefficient dropped lower than that of clean airfoil, whose regions correspond with the flow separations caused by the icing. The decrease in pressure caused an increase in both lift and drag, as shown in Figure 7, and the decrease in Cp near the ice ridge was also reported in an experimental study [41]. In Case 4, the pressure coefficient peaked at the stagnation point close to the leading edge, but another peak (or discontinuity profile) appeared downstream of the leading edge, at the edge of the ice. Moreover, the suction peak on the suction surface was attenuated by the formed ice, and this resulted in the decrease in lift. For x/c 0.2, the pressure coefficient converged to that of clean airfoil. In Case 10, the profile agrees with that of clean airfoil, except for the second peak at x/c ≈ 0.15 because the heating area is wide and the icing layer is thin. Accordingly, the lift and drag contribution are small. In general, the lift decreases owing to icing, especially in experiments (e.g., [39,40,42]), and the present results are inconsistent with this tendency. In actual scenarios, the ice surface works as a rough surface because the shape of ice is three-dimensional and complex, and a hump-like ice formation appears behind the heater [40]. Accordingly, the icing shape deteriorates the aerodynamic performance of airfoil and the flow separation differs significantly from that in the present two-dimensional simulation. The present results are obtained using the two-dimensional simulation without considering the surface roughness and the icing helps in improving the aerodynamic performance. The lift is increased because of the large flow separation on the suction side for the small heating area cases and the thickened wing thickness for the large heating area cases. Moreover, the hump-like ice formedPDF Image | Anti-Icing Electric Heaters for Icing on the NACA 0012 Airfoil
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