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<p>Aircraft icing is a major challenge in the aviation field. Due to its large particle size and significant dynamic characteristics, supercooled large water droplets make the icing shape more complex, which seriously affects the aerodynamic performance and handling stability of the aircraft. In this paper, a fluid–solid coupling heat transfer model is established based on FLUENT and FENSAP-ICE software by combining computational fluid dynamics and icing thermodynamics theory. The icing mechanism, influencing factors and influencing factors of SLD·(supercooled large droplet) impacting wing are systematically analyzed and numerically simulated. On this basis, the fluid–solid coupling heat transfer characteristics of the hot air anti-icing system are analyzed. It is revealed that the temperature field of the leading edge of the wing is nonuniformly distributed due to the increase in the bleed air temperature. The absorption temperature of the latent heat in the icing area is lower than that in the non-icing area, and the latter is fully heated to increase the temperature difference by 67%. The purpose is to provide reference for the development of efficient and reliable anti-icing system, which is of great significance for ensuring the safety of aviation flight.</p>

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Study on fluid flow and heat transfer characteristics of supercooled large droplet impingement on wing surfaces

  • 期刊论文

  • 发表日期：

    2026年2月17日

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  • Xincheng Wang,
  • Yu Wang,
  • Guang Yang,
  • Senyun Liu,
  • Risto Kosonen,
  • Qipeng Li,
  • Zhengchao Yang,
  • Xuejing Yang,
  • Xiaoyi Sun,
  • Songqing Wang

摘要

Aircraft icing is a major challenge in the aviation field. Due to its large particle size and significant dynamic characteristics, supercooled large water droplets make the icing shape more complex, which seriously affects the aerodynamic performance and handling stability of the aircraft. In this paper, a fluid–solid coupling heat transfer model is established based on FLUENT and FENSAP-ICE software by combining computational fluid dynamics and icing thermodynamics theory. The icing mechanism, influencing factors and influencing factors of SLD·(supercooled large droplet) impacting wing are systematically analyzed and numerically simulated. On this basis, the fluid–solid coupling heat transfer characteristics of the hot air anti-icing system are analyzed. It is revealed that the temperature field of the leading edge of the wing is nonuniformly distributed due to the increase in the bleed air temperature. The absorption temperature of the latent heat in the icing area is lower than that in the non-icing area, and the latter is fully heated to increase the temperature difference by 67%. The purpose is to provide reference for the development of efficient and reliable anti-icing system, which is of great significance for ensuring the safety of aviation flight.