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Aerospace
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Deicing and Anti-Icing of Aircraft (Volume IV)
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Deicing and Anti-Icing of Aircraft (Volume IV)

A special issue of Aerospace (ISSN 2226-4310). This special issue belongs to the section "Aeronautics".

Deadline for manuscript submissions: 30 November 2025 | Viewed by 3113

Special Issue Editors

Dr. Hirotaka Sakaue

E-Mail Website
Guest Editor
Department of Aerospace and Mechanical Engineering, University of Notre Dame, Notre Dame, IN 46556, USA
Interests: pressure- and temperature-sensitive paint technique; advanced flow diagnostics by luminescent imaging; micro-fiber coating as chemical flow control; ice-phobic coating for anti- and de-icing; unsteady aerodynamics; wind tunnel testing (low-speed, transonic-speed, high-speed, and high Reynolds-number flows); two phase flows; heat transfer in hypersonic flow; fluid-thermal-structure interactions; environmental and energy engineering; biomedical and biological applications
Special Issues, Collections and Topics in MDPI journals
Dr. Xiaobin Shen

E-Mail Website
Guest Editor
Laboratory of Fundamental Science on Ergonomics and Environmental Control, School of Aeronautic Science and Engineering, Beihang University, Beijing 100191, China
Interests: aircraft icing; anti-icing and de-icing system; heat and mass transfer; thermal management
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

Aircraft icing is still a critical issue in aircraft operations. In recent years, multidisciplinary approaches have been attempted to tackle to this problem. One of the outcomes is the development of icephobic coating; nevertheless, there are many challenges that need to be overcome to fix aircraft icing from a fundamental to application basis. This Special Issue aims to provide an overview of recent advances in deicing and anti-icing of aircraft. Authors are invited to submit full research articles and review manuscripts addressing (but not limited to) the following topics:

  • Novel experimental methods to simulation droplet icing, ice accretion and practical applications
  • Novel numerical methods in droplet icing, ice accretion, and practical applications
  • Icephobic coating
  • Hybrid system for deicing and anti-icing of aircraft

Dr. Hirotaka Sakaue
Dr. Xiaobin Shen
Guest Editors

Manuscript Submission Information

Manuscripts should be submitted online at www.mdpi.com by registering and logging in to this website. Once you are registered, click here to go to the submission form. Manuscripts can be submitted until the deadline. All submissions that pass pre-check are peer-reviewed. Accepted papers will be published continuously in the journal (as soon as accepted) and will be listed together on the special issue website. Research articles, review articles as well as short communications are invited. For planned papers, a title and short abstract (about 100 words) can be sent to the Editorial Office for announcement on this website.

Submitted manuscripts should not have been published previously, nor be under consideration for publication elsewhere (except conference proceedings papers). All manuscripts are thoroughly refereed through a single-blind peer-review process. A guide for authors and other relevant information for submission of manuscripts is available on the Instructions for Authors page. Aerospace is an international peer-reviewed open access monthly journal published by MDPI.

Please visit the Instructions for Authors page before submitting a manuscript. The Article Processing Charge (APC) for publication in this open access journal is 2400 CHF (Swiss Francs). Submitted papers should be well formatted and use good English. Authors may use MDPI's English editing service prior to publication or during author revisions.

Keywords

  • deicing
  • anti-icing
  • ice accretion
  • ice adhesion
  • ice cohesion

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Related Special Issues

Published Papers (3 papers)

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Research

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16 pages, 8895 KiB  
Article
Influence of Ice Growth Mode on the Ice Thickness and Shape Prediction of Two-Dimensional Airfoil
by Xiaobin Shen, Jingyu Zhao, Zekun Ye, Huanfa Wang and Guiping Lin
Aerospace 2024, 11(12), 1010; https://doi.org/10.3390/aerospace11121010 - 8 Dec 2024
Viewed by 817
Abstract
Computational results of aircraft icing and predictions of ice shape are not only determined by the solutions of air-supercooled droplet two-phase flow and icing thermodynamic models of surface water film, but are also influenced by the growth mode of the ice layer. Two [...] Read more.
Computational results of aircraft icing and predictions of ice shape are not only determined by the solutions of air-supercooled droplet two-phase flow and icing thermodynamic models of surface water film, but are also influenced by the growth mode of the ice layer. Two ice growth modes were established in a two-dimensional (2D) icing process simulation framework to calculate the ice thickness and ice shape, depending on whether surface deformation of the icing process was considered. Ice accretion simulations were performed with the two ice growth modes for an NACA0012 airfoil under rime ice and mixed ice conditions, and the results of ice amount, ice thickness, and ice shape were compared and analyzed. Under the same amount of ice formation, the ice thickness and ice shape obtained using different ice growth modes vary. The ice thickness and the ice shape size are relatively large without considering surface deformation, whereas the results with growth correction show a certain degree of reduction, which is more noticeable around the leading edge and the ice horns. However, the degrees of difference in ice thickness and ice shape are not the same, and the deviation in ice thickness is more obvious. Furthermore, the ice thickness and ice shape obtained using the ice growth correction mode are more consistent with experimental data and commercial software results, verifying the accuracy of the ice simulation method and the necessity of considering ice surface deformation. This paper is an essential guide for understanding the icing mechanism and accurately predicting two-dimensional ice shape. Full article
(This article belongs to the Special Issue Deicing and Anti-Icing of Aircraft (Volume IV))
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20 pages, 4479 KiB  
Article
Prediction of Temperature Distribution on an Aircraft Hot-Air Anti-Icing Surface by ROM and Neural Networks
by Ziying Chu, Ji Geng, Qian Yang, Xian Yi and Wei Dong
Aerospace 2024, 11(11), 930; https://doi.org/10.3390/aerospace11110930 - 11 Nov 2024
Cited by 1 | Viewed by 1084
Abstract
To address the inefficiencies and time-consuming nature of traditional hot-air anti-icing system designs, reduced-order models (ROMs) and machine learning techniques are introduced to predict anti-icing surface temperature distributions. Two models, AlexNet combined with Proper Orthogonal Decomposition (POD-AlexNet) and multi-CNNs with GRU (MCG), are [...] Read more.
To address the inefficiencies and time-consuming nature of traditional hot-air anti-icing system designs, reduced-order models (ROMs) and machine learning techniques are introduced to predict anti-icing surface temperature distributions. Two models, AlexNet combined with Proper Orthogonal Decomposition (POD-AlexNet) and multi-CNNs with GRU (MCG), are proposed by comparing several classic neural networks. Design variables of the hot-air anti-icing cavity are used as inputs of the two models, and the corresponding surface temperature distribution data serve as outputs, and then the performance of these models is evaluated on the test set. The POD-AlexNet model achieves a mean prediction accuracy of over 95%, while the MCG model reaches 96.97%. Furthermore, the proposed model demonstrates a prediction time of no more than 5.5 ms for individual temperature samples. The proposed models not only provide faster predictions of anti-icing surface temperature distributions than traditional numerical simulation methods but also ensure acceptable accuracy, which supports the design of aircraft hot-air anti-icing systems based on optimization methods such as genetic algorithms. Full article
(This article belongs to the Special Issue Deicing and Anti-Icing of Aircraft (Volume IV))
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Review

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17 pages, 2448 KiB  
Review
A Literature Review on Numerical Simulation of Thermal Anti-Icing
by Ningli Chen, Xian Yi, Qiang Wang, Delin Chai and Cong Li
Aerospace 2025, 12(2), 83; https://doi.org/10.3390/aerospace12020083 - 24 Jan 2025
Viewed by 801
Abstract
This paper reviews the numerical simulation method for thermal anti-icing. Typically, the numerical study of an anti-icing system involves a coupled simulation of various physical processes: airflow, droplet flow, thin water film flow on the wall, and heat conduction within the solid wall. [...] Read more.
This paper reviews the numerical simulation method for thermal anti-icing. Typically, the numerical study of an anti-icing system involves a coupled simulation of various physical processes: airflow, droplet flow, thin water film flow on the wall, and heat conduction within the solid wall. Airflow is commonly simulated using the Reynolds-Averaged Navier–Stokes method, while droplet flow can be modeled using either the Eulerian or Lagrangian approach. For simulating water film flow, there are three primary models: the Messinger model, the SWIM model, and the Myers model. The heat transfer process within the solid wall can be coupled with the external air/droplet and film flow using either a tight-coupling or a loose-coupling method. When simulating an electrothermal anti-icing system, methods such as the equivalent heat conductivity scheme or shell conduction method are employed to handle heat conduction in multi-layer thin walls. To improve the accuracy of thermal anti-icing simulations, additional research is still necessary, focusing on studies on rivulet flow, bead flow, and the heat convection coefficient on the system’s wall. Full article
(This article belongs to the Special Issue Deicing and Anti-Icing of Aircraft (Volume IV))
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