Deicing and Anti-Icing of Aircraft (Volume II)

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

Deadline for manuscript submissions: closed (30 November 2021) | Viewed by 38009

Special Issue 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

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 aircrafts

Dr. Hirotaka Sakaue
Guest Editor

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

Related Special Issues

Published Papers (9 papers)

Order results
Result details
Select all
Export citation of selected articles as:

Research

Jump to: Review

28 pages, 2014 KiB  
Article
Neural Network Prediction for Ice Shapes on Airfoils Using iceFoam Simulations
by Sergei Strijhak, Daniil Ryazanov, Konstantin Koshelev and Aleksandr Ivanov
Aerospace 2022, 9(2), 96; https://0-doi-org.brum.beds.ac.uk/10.3390/aerospace9020096 - 12 Feb 2022
Cited by 12 | Viewed by 2854
Abstract
In this article the procedure and method for the ice accretion prediction for different airfoils using artificial neural networks (ANNs) are discussed. A dataset for the neural network is based on the numerical experiment results—obtained through iceFoam solver—with four airfoils (NACA0012, General Aviation, [...] Read more.
In this article the procedure and method for the ice accretion prediction for different airfoils using artificial neural networks (ANNs) are discussed. A dataset for the neural network is based on the numerical experiment results—obtained through iceFoam solver—with four airfoils (NACA0012, General Aviation, Business Jet, and Commercial Transport). Input data for neural networks include airfoil and ice geometries, transformed into a set of parameters using a parabolic coordinate system and Fourier series expansion. Besides input features include physical parameters of flow (velocity, temperature, droplets diameter, liquid water content, time of ice accretion) and angle of attack. The novelty of this work is in that the neural network dataset includes various airfoils and the data augmentation technique being a combination of all time slices. Several artificial neural networks (ANNs), fully connected networks (FCNNs), and convolutional networks (CNNs) were trained to predict airfoil ice shapes. Two different loss functions were considered. In order to improve performance of models, batch normalization and dropout layers were used. The most accurate results of ice shape prediction were obtained using CNN and FCNN that applied batch normalization and dropout layers to output neurons of each layer. Full article
(This article belongs to the Special Issue Deicing and Anti-Icing of Aircraft (Volume II))
Show Figures

Figure 1

14 pages, 1408 KiB  
Article
Evaluation of Anti-Icing Performance for an NACA0012 Airfoil with an Asymmetric Heating Surface
by Koji Fukudome, Yuki Tomita, Sho Uranai, Hiroya Mamori and Makoto Yamamoto
Aerospace 2021, 8(10), 294; https://0-doi-org.brum.beds.ac.uk/10.3390/aerospace8100294 - 12 Oct 2021
Cited by 2 | Viewed by 2238
Abstract
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 [...] Read more.
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. Full article
(This article belongs to the Special Issue Deicing and Anti-Icing of Aircraft (Volume II))
Show Figures

Figure 1

15 pages, 1440 KiB  
Article
Description of a Eulerian–Lagrangian Approach for the Modeling of Cooling Water Droplets
by Rúben Meireles, Leandro Magalhães, André Silva and Jorge Barata
Aerospace 2021, 8(9), 270; https://0-doi-org.brum.beds.ac.uk/10.3390/aerospace8090270 - 18 Sep 2021
Cited by 2 | Viewed by 1875
Abstract
The present paper describes a tool developed in-house for the modeling of free-falling water droplet cooling processes. A two-way coupling model is employed to account for the interactions between the droplets and the carrier fluid, following a Eulerian–Lagrangian approach. In addition, a stochastic [...] Read more.
The present paper describes a tool developed in-house for the modeling of free-falling water droplet cooling processes. A two-way coupling model is employed to account for the interactions between the droplets and the carrier fluid, following a Eulerian–Lagrangian approach. In addition, a stochastic separated flow technique is employed, involving random sampling of the fluctuating fluid velocity. In physical modeling, two empirical correlations are considered for determining the heat and mass transfer coefficients, with the possibility of accounting for vibrations. The numerical results indicate the preponderance of the interactions between droplet and carrier fluid at various humidity ratios. Full article
(This article belongs to the Special Issue Deicing and Anti-Icing of Aircraft (Volume II))
Show Figures

Figure 1

7 pages, 1122 KiB  
Article
Behavior of Sliding Angle as Function of Temperature Difference between Droplet and Superhydrophobic Coating for Aircraft Ice Protection Systems
by Mitsugu Hasegawa, Haruka Endo, Katsuaki Morita, Hirotaka Sakaue and Shigeo Kimura
Aerospace 2021, 8(8), 219; https://0-doi-org.brum.beds.ac.uk/10.3390/aerospace8080219 - 08 Aug 2021
Cited by 5 | Viewed by 2390
Abstract
A hybrid anti-/de-icing system combining a superhydrophobic coating and an electrothermal heater is an area of active research for aircraft icing prevention. The heater increases the temperature of the interaction surface between impinging droplets and an aircraft surface. One scientific question that has [...] Read more.
A hybrid anti-/de-icing system combining a superhydrophobic coating and an electrothermal heater is an area of active research for aircraft icing prevention. The heater increases the temperature of the interaction surface between impinging droplets and an aircraft surface. One scientific question that has not been studied in great detail is whether the temperatures of the droplet and the surface or the temperature difference between the two dominate the anti-/de-icing performance. Herein, this scientific question is experimentally studied based on the mobility of a water droplet over a superhydrophobic coating. The mobility is characterized by the sliding angle between the droplet and the coating surface. It was found that the temperature difference between the droplet and the coating surface has a higher impact on the sliding angle than their individual temperatures. Full article
(This article belongs to the Special Issue Deicing and Anti-Icing of Aircraft (Volume II))
Show Figures

Graphical abstract

19 pages, 8691 KiB  
Article
Design and Development of an Experimental Setup of Electrically Powered Spinning Rotor Blades in Icing Wind Tunnel and Preliminary Testing with Surface Coatings as Hybrid Protection Solution
by Eric Villeneuve, Caroline Blackburn and Christophe Volat
Aerospace 2021, 8(4), 98; https://0-doi-org.brum.beds.ac.uk/10.3390/aerospace8040098 - 02 Apr 2021
Cited by 15 | Viewed by 3386
Abstract
In order to study ice protection systems for rotating blades, a new experimental setup has been developed at the Anti-Icing Materials International Laboratory (AMIL). This system consists of two small-scale rotating blades in a refrigerated icing wind tunnel where atmospheric icing can be [...] Read more.
In order to study ice protection systems for rotating blades, a new experimental setup has been developed at the Anti-Icing Materials International Laboratory (AMIL). This system consists of two small-scale rotating blades in a refrigerated icing wind tunnel where atmospheric icing can be simulated. Power is brought to the blades through a slip ring, through which the signals of the different sensors that are installed on the blades also pass. As demonstrated by the literature review, this new setup will address the need of small-scale wind tunnel testing on electrically powered rotating blades. To test the newly designed apparatus, preliminary experimentation is done on a hybrid ice protection system. Electrothermal protection is combined with different surface coatings to measure the impact of those coatings on the power consumption of the system. In anti-icing mode, the coatings tested did not reduce the power consumption on the system required to prevent ice from accumulating on the leading edge. The coatings however, due to their hydrophobic/superhydrophobic nature, reduced the power required to prevent runback ice accumulation when the leading edge was protected. One of the coatings did not allow any runback accumulation, limiting the power to protect the whole blades to the power required to protect solely the leading edge, resulting in a potential 40% power reduction for the power consumption of the system. In de-icing mode, the results with all the substrates tested showed similar power to achieve ice shedding from the blade. Since the coatings tested have a low icephobicity, it would be interesting to perform additional testing with icephobic coatings. Also, a small unheated zone at the root of the blade prevented complete ice shedding from the blade. A small part of the ice layer was left on the blade after testing, meaning that a cohesive break had to occur within the ice layer, and therefore impacting the results. Improvements to the setup will be done to remedy the situation. Those preliminary testing performed with the newly developed test setup have demonstrated the potential of this new device which will now allow, among other things, to measure heat transfer, force magnitudes, ice nucleation, and thermal equilibrium during ice accretion, with different innovative thermal protection systems (conductive coating, carbon nanotubes, impulse, etc.) as well as mechanical systems. The next step, following the improvements, is to measure forced convection on a thermal ice protection system with and without precipitation and to test mechanical ice protection systems. Full article
(This article belongs to the Special Issue Deicing and Anti-Icing of Aircraft (Volume II))
Show Figures

Graphical abstract

24 pages, 9355 KiB  
Article
An Experimental Investigation of the Convective Heat Transfer on a Small Helicopter Rotor with Anti-Icing and De-Icing Test Setups
by Abdallah Samad, Eric Villeneuve, Caroline Blackburn, François Morency and Christophe Volat
Aerospace 2021, 8(4), 96; https://0-doi-org.brum.beds.ac.uk/10.3390/aerospace8040096 - 01 Apr 2021
Cited by 21 | Viewed by 3590
Abstract
Successful icing/de-icing simulations for rotorcraft require a good prediction of the convective heat transfer on the blade’s surface. Rotorcraft icing is an unwanted phenomenon that is known to cause flight cancelations, loss of rotor performance and severe vibrations that may have disastrous and [...] Read more.
Successful icing/de-icing simulations for rotorcraft require a good prediction of the convective heat transfer on the blade’s surface. Rotorcraft icing is an unwanted phenomenon that is known to cause flight cancelations, loss of rotor performance and severe vibrations that may have disastrous and deadly consequences. Following a series of experiments carried out at the Anti-icing Materials International Laboratory (AMIL), this paper provides heat transfer measurements on heated rotor blades, under both the anti-icing and de-icing modes in terms of the Nusselt Number (Nu). The objective is to develop correlations for the Nu in the presence of (1) an ice layer on the blades (NuIce) and (2) liquid water content (LWC) in the freestream with no ice (NuWet). For the sake of comparison, the NuWet and the NuIce are compared to heat transfer values in dry runs (NuDry). Measurements are reported on the nose of the blade-leading edge, for three rotor speeds (Ω) = 500, 900 and 1000 RPM; a pitch angle (θ) = 6°; and three different radial positions (r/R), r/R = 0.6, 0.75 and 0.95. The de-icing tests are performed twice, once for a glaze ice accretion and another time for rime ice. Results indicate that the NuDry and the NuWet directly increased with V, r/R or Ω, mainly due to an increase in the Reynolds number (Re). Measurements indicate that the NuWet to NuDry ratio was always larger than 1 as a direct result of the water spray addition. NuIce behavior was different and was largely affected by the ice thickness (tice) on the blade. However, the ice acted as insulation on the blade surface and the NuIce to NuDry ratio was always less than 1, thus minimizing the effect of convection. Four correlations are then proposed for the NuDry, the NuWet and the NuIce, with an average error between 3.61% and 12.41%. The NuDry correlation satisfies what is expected from heat transfer near the leading edge of an airfoil, where the NuDry correlates well with Re0.52. Full article
(This article belongs to the Special Issue Deicing and Anti-Icing of Aircraft (Volume II))
Show Figures

Figure 1

15 pages, 4988 KiB  
Article
Experimental Heat Loads for Electrothermal Anti-Icing and De-Icing on UAVs
by Richard Hann, Adriana Enache, Mikkel Cornelius Nielsen, Bård Nagy Stovner, Jeroen van Beeck, Tor Arne Johansen and Kasper Trolle Borup
Aerospace 2021, 8(3), 83; https://0-doi-org.brum.beds.ac.uk/10.3390/aerospace8030083 - 18 Mar 2021
Cited by 35 | Viewed by 8930
Abstract
Atmospheric in-flight icing on unmanned aerial vehicles (UAVs) is a significant hazard. UAVs that are not equipped with ice protection systems are usually limited to operations within visual line of sight or to weather conditions without icing risk. As many military and commercial [...] Read more.
Atmospheric in-flight icing on unmanned aerial vehicles (UAVs) is a significant hazard. UAVs that are not equipped with ice protection systems are usually limited to operations within visual line of sight or to weather conditions without icing risk. As many military and commercial UAV missions require flights beyond visual line of sight and into adverse weather conditions, energy-efficient ice protection systems are required. In this experimental study, two electro-thermal ice protection systems for fixed-wing UAVs were tested. One system was operated in anti-icing and de-icing mode, and the other system was designed as a parting strip de-icing system. Experiments were conducted in an icing wind tunnel facility for varying icing conditions at low Reynolds numbers. A parametric study over the ice shedding time was used to identify the most energy-efficient operation mode. The results showed that longer intercycle durations led to higher efficiencies and that de-icing with a parting strip was superior compared to anti-icing and de-icing without a parting strip. These findings are relevant for the development of energy-efficient systems in the future. Full article
(This article belongs to the Special Issue Deicing and Anti-Icing of Aircraft (Volume II))
Show Figures

Figure 1

25 pages, 7236 KiB  
Article
A Numerical and Experimental Investigation of the Convective Heat Transfer on a Small Helicopter Rotor Test Setup
by Abdallah Samad, Eric Villeneuve, François Morency and Christophe Volat
Aerospace 2021, 8(2), 53; https://0-doi-org.brum.beds.ac.uk/10.3390/aerospace8020053 - 20 Feb 2021
Cited by 8 | Viewed by 2982
Abstract
In-flight icing affects helicopter performance, limits its operations, and reduces safety. The convective heat transfer is an important parameter in numerical icing simulations and state-of-the-art icing/de-icing codes utilize important computing resources when calculating it. The BEMT–RHT and UVLM–RHT offer low- and medium-fidelity approaches [...] Read more.
In-flight icing affects helicopter performance, limits its operations, and reduces safety. The convective heat transfer is an important parameter in numerical icing simulations and state-of-the-art icing/de-icing codes utilize important computing resources when calculating it. The BEMT–RHT and UVLM–RHT offer low- and medium-fidelity approaches to estimate the rotor heat transfer (RHT). They are based on a coupling between Blade element momentum theory (BEMT) or unsteady vortex lattice method (UVLM), and a CFD-determined heat transfer correlation. The latter relates the Frossling number (Fr) to the Reynolds number (Re) and effective angle of attack (αEff). In a series of experiments carried out at the Anti-icing Materials International Laboratory (AMIL), this paper serves as a proof of concept of the proposed correlations. The objective is to propose correlations for the experimentally measured rotor heat transfer data. Specifically, the Frx is correlated with the Re and αEff in a similar form as the proposed CFD-based correlations. A fixed-wing setup is first used as a preliminary step to verify the heat transfer measurements of the icing wind tunnel (IWT). Tests are conducted at α = 0°, for a range of 4.76 × 105Re ≤ 1.36 × 106 and at 10 non-dimensional surface wrap locations − 0.62 ≤ (S/c) ≤ + 0.87. Later, a rotor setup is used to build the novel heat transfer correlation, tests are conducted at two pitch angles ((θ) = 0° and 6°) for a range of rotor speeds (500 RPM ≤ (Ω) ≤ 1500 RPM), three different radial positions ((r/R) = 0.6, 0.75 and 0.95), and 0 ≤ S/c ≤ + 0.58. Results indicate that the fixed-wing Frx at the stagnation point was in the range of literature experimental data, and within 8% of fully turbulent CFD simulations. The FrAvg also agrees with CFD predictions, with an average discrepancy of 1.4%. For the rotor, the Ω caused a similar increase of Frx for the tests at θ = 0° and those at θ = 6°. Moreover, the Frx behavior changed significantly with r/R, suggesting the αEff had a significant effect on the Frx. Finally, the rotor data are first correlated with Rem (at each S/c) for θ = 0° to establish the correlation parameters, and a term for the αEff is then added to also account for the tests at θ = 6°. The correlations fit the data with an error between 2.1% and 14%, thus justifying the use of a coupled approach for the BEMT–RHT and UVLM–RHT. Full article
(This article belongs to the Special Issue Deicing and Anti-Icing of Aircraft (Volume II))
Show Figures

Figure 1

Review

Jump to: Research

25 pages, 4184 KiB  
Review
A Review on the Current Status of Icing Physics and Mitigation in Aviation
by Masafumi Yamazaki, Aleksandar Jemcov and Hirotaka Sakaue
Aerospace 2021, 8(7), 188; https://0-doi-org.brum.beds.ac.uk/10.3390/aerospace8070188 - 14 Jul 2021
Cited by 35 | Viewed by 5520
Abstract
Icing on an aircraft is the cause of numerous adverse effects on aerodynamic performance. Although the issue was recognized in the 1920s, the icing problem is still an area of ongoing research due to the complexity of the icing phenomena. This review article [...] Read more.
Icing on an aircraft is the cause of numerous adverse effects on aerodynamic performance. Although the issue was recognized in the 1920s, the icing problem is still an area of ongoing research due to the complexity of the icing phenomena. This review article aims to summarize current research on aircraft icing in two fundamental topics: icing physics and icing mitigation techniques. The icing physics focuses on fixed wings, rotors, and engines severely impacted by icing. The study of engine icing has recently become focused on ice-crystal icing. Icing mitigation techniques reviewed are based on active, passive, and hybrid methods. The active mitigation techniques include those based on thermal and mechanical methods, which are currently in use on aircraft. The passive mitigation techniques discussed are based on current ongoing studies in chemical coatings. The hybrid mitigation technique is reviewed as a combination of the thermal method (active) and chemical coating (passive) to lower energy consumption. Full article
(This article belongs to the Special Issue Deicing and Anti-Icing of Aircraft (Volume II))
Show Figures

Figure 1

Back to TopTop