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Deicing and Anti-Icing of Aircraft (Volume II)

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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 47751

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Dr. Hirotaka Sakaue

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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
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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

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Keywords

deicing
anti-icing
ice accretion
ice adhesion
ice cohesion

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Related Special Issues

Deicing and Anti-Icing of Aircraft (Volume III) in Aerospace (14 articles)
Deicing and Anti-Icing of Aircraft in Aerospace (12 articles)
Deicing and Anti-Icing of Aircraft (Volume IV) in Aerospace (1 article)

Published Papers (9 papers)

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Research

Jump to: Review

28 pages, 2014 KiB

Open AccessArticle

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://doi.org/10.3390/aerospace9020096 - 12 Feb 2022

Cited by 18 | Viewed by 4001

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, 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))

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14 pages, 1408 KiB

Open AccessArticle

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://doi.org/10.3390/aerospace8100294 - 12 Oct 2021

Cited by 4 | Viewed by 2977

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 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}^{\circ}

under a glaze ice condition. An asymmetric heating area was imposed on the suction and pressure surfaces considering a temperature of

10^{\circ}

C 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))

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15 pages, 1440 KiB

Open AccessArticle

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://doi.org/10.3390/aerospace8090270 - 18 Sep 2021

Cited by 3 | Viewed by 2460

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 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))

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7 pages, 1122 KiB

Open AccessArticle

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://doi.org/10.3390/aerospace8080219 - 8 Aug 2021

Cited by 8 | Viewed by 3174

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 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))

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19 pages, 8691 KiB

Open AccessArticle

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://doi.org/10.3390/aerospace8040098 - 2 Apr 2021

Cited by 18 | Viewed by 4102

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 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))

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24 pages, 9355 KiB

Open AccessArticle

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://doi.org/10.3390/aerospace8040096 - 1 Apr 2021

Cited by 24 | Viewed by 4473

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 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 (Nu_Ice) and (2) liquid water content (LWC) in the freestream with no ice (Nu_Wet). For the sake of comparison, the Nu_Wet and the Nu_Ice are compared to heat transfer values in dry runs (Nu_Dry). 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 Nu_Dry and the Nu_Wet directly increased with V_∝, r/R or Ω, mainly due to an increase in the Reynolds number (Re). Measurements indicate that the Nu_Wet to Nu_Dry ratio was always larger than 1 as a direct result of the water spray addition. Nu_Ice behavior was different and was largely affected by the ice thickness (t_ice) on the blade. However, the ice acted as insulation on the blade surface and the Nu_Ice to Nu_Dry ratio was always less than 1, thus minimizing the effect of convection. Four correlations are then proposed for the Nu_Dry, the Nu_Wet and the Nu_Ice, with an average error between 3.61% and 12.41%. The Nu_Dry correlation satisfies what is expected from heat transfer near the leading edge of an airfoil, where the Nu_Dry correlates well with Re^0.52. Full article

(This article belongs to the Special Issue Deicing and Anti-Icing of Aircraft (Volume II))

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15 pages, 4988 KiB

Open AccessArticle

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://doi.org/10.3390/aerospace8030083 - 18 Mar 2021

Cited by 42 | Viewed by 10252

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 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))

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25 pages, 7236 KiB

Open AccessArticle

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://doi.org/10.3390/aerospace8020053 - 20 Feb 2021

Cited by 11 | Viewed by 3676

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 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 (α_Eff). 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 Fr_x is correlated with the Re and α_Eff 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 × 10⁵ ≤ Re ≤ 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 Fr_x at the stagnation point was in the range of literature experimental data, and within 8% of fully turbulent CFD simulations. The Fr_Avg also agrees with CFD predictions, with an average discrepancy of 1.4%. For the rotor, the Ω caused a similar increase of Fr_x for the tests at θ = 0° and those at θ = 6°. Moreover, the Fr_x behavior changed significantly with r/R, suggesting the α_Eff had a significant effect on the Fr_x. Finally, the rotor data are first correlated with Re^m (at each S/c) for θ = 0° to establish the correlation parameters, and a term for the α_Eff 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))

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Review

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25 pages, 4184 KiB

Open AccessReview

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://doi.org/10.3390/aerospace8070188 - 14 Jul 2021

Cited by 60 | Viewed by 8034

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 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))

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