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Anti-Icing Electric Heaters for Icing on the NACA 0012 Airfoil

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Anti-Icing Electric Heaters for Icing on the NACA 0012 Airfoil ( anti-icing-electric-heaters-icing-naca-0012-airfoil )

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Aerospace 2020, 7, 123 9 of 15 Table 2. Numerical conditions for NACA 0012 [38]. Airfoil Chord length Angle of attack Freestream velocity Freestream temperature Reynolds number Median volume diameter (MVD) Liquid water content (LWC) Initial droplet temperature Total droplet number Exposure time Ambient pressure Heating condition Heating wall temperature Theater Heating region Wall material Wall thickness [m] [◦] [m/s] [◦C] [-] [μm] [g/m3] [◦C] [-] [s] [kPa] NACA 0012 0.53 4 58.1 −27.8 2,800,000 18.0 1.3 −27.8 1,000,000 480 95.61 Constant temperature [◦C] 10.0 1–12% chord (Case 1–Case 12) Aluminum [mm] 10 Figure 7 shows CL and CD normalized by the same values in the case without icing as a function of heating area. The normalized values are defined, as follows: CL∗ = CL −CLclean ×100 [%], (11) CL clean CD∗ = CD −CDclean ×100 [%], (12) CD clean where the subscript clean shows the value without icing. These coefficients exhibited different behavior for the heating region. As the heating area increased, CL decreased, exhibited a negative peak at 4%c of the heating area (Case 4), and then recovered. Moreover, CD gradually decreased and converged to 0%. Below, four cases, namely the clean airfoil without icing, Case 1, Case 4, and Case 10, are considered to discuss the flow fields. 20.0 15.0 10.0 5.0 0.0 −5.0 0 3 6 9 12 Heating Area [%] 􏳰CL* 􏳰CD* Figure 7. Aerodynamic performance of each heating area against performance of clean airfoil. Figure 8 shows the ice thicknesses. On the suction surface, the ice area decreases as the heating area increases. On the pressure side, the round ice forms very close to the leading edge in Cases 1 􏳱 Rate of Aerodynamic Coefficient to clean airfoil [%]

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