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Article

Evaluation of Anti-Icing Performance for an NACA0012 Airfoil with an Asymmetric Heating Surface

by 1,*,†, 1,†, 1, 2,† and 1,†
1
Department of Mechanical Engineering, Tokyo University of Science, Tokyo 125-8585, Japan
2
Department of Mechanical and Intelligent Systems Engineering, The University of Electro-Communications, Chofu 182-8585, Japan
*
Author to whom correspondence should be addressed.
These authors contributed equally to this work.
Academic Editor: Hirotaka Sakaue
Aerospace 2021, 8(10), 294; https://doi.org/10.3390/aerospace8100294
Received: 18 July 2021 / Revised: 15 September 2021 / Accepted: 4 October 2021 / Published: 12 October 2021
(This article belongs to the Special Issue Deicing and Anti-Icing of Aircraft (Volume II))
Heating devices on airfoil surfaces are widely used as an anti-icing technology. This study investigated the aerodynamic performance with a static heating surface based on the modified extended Messinger model. The predicted ice shape was validated through a comparison with the experimental results for HAARP-II. A reasonable agreement was found for both the icing area and the ice mass on the suction surface. Then, the prediction method was adopted for an NACA0012 airfoil at an attack angle of 4.0 under a glaze ice condition. An asymmetric heating area was imposed on the suction and pressure surfaces considering a temperature of 10C near the leading edge. As a result of heating, the round ice formation when was no longer observed, and the formed ice volume decreased. However, bump-shaped pieces of ice were formed downstream of the heater owing to runback water; these bump-shaped pieces of ice formed on the suction surface significantly increased the flow drag and reduced the lift. The results indicated that extending the heating area on the suction surface can improve the aerodynamic performance. Consequently, the overall aerodynamic performance is deteriorated by adding static heating compared to the case without heating. View Full-Text
Keywords: airfoil; ice accretion; anti-icing method; heating surface; super-cooled water droplet airfoil; ice accretion; anti-icing method; heating surface; super-cooled water droplet
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MDPI and ACS Style

Fukudome, K.; Tomita, Y.; Uranai, S.; Mamori, H.; Yamamoto, M. Evaluation of Anti-Icing Performance for an NACA0012 Airfoil with an Asymmetric Heating Surface. Aerospace 2021, 8, 294. https://doi.org/10.3390/aerospace8100294

AMA Style

Fukudome K, Tomita Y, Uranai S, Mamori H, Yamamoto M. Evaluation of Anti-Icing Performance for an NACA0012 Airfoil with an Asymmetric Heating Surface. Aerospace. 2021; 8(10):294. https://doi.org/10.3390/aerospace8100294

Chicago/Turabian Style

Fukudome, Koji, Yuki Tomita, Sho Uranai, Hiroya Mamori, and Makoto Yamamoto. 2021. "Evaluation of Anti-Icing Performance for an NACA0012 Airfoil with an Asymmetric Heating Surface" Aerospace 8, no. 10: 294. https://doi.org/10.3390/aerospace8100294

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