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Journal articles on the topic 'Icing of aerodynamic surfaces'

Author: Grafiati

Published: 30 May 2022

Last updated: 31 July 2025

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1

Ma, Liqun, Zichen Zhang, Linyue Gao, Yang Liu, and Hui Hu. "Bio-Inspired Icephobic Coatings for Aircraft Icing Mitigation: A Critical Review." Reviews of Adhesion and Adhesives 8, no. 2 (2020): 168–99. http://dx.doi.org/10.7569/raa.2020.097307.

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A critical review is provided to summarize our recent efforts to utilize the state-of-the-art bio-inspired icephobic coatings/surfaces, i.e., 1). Lotus-leaf-inspired superhydrophobic surfaces (SHS) and 2). Pitcher-plant-inspired slippery liquid-infused porous surfaces (SLIPS) for aircraft icing mitigation. By leveraging the unique Icing Research Tunnel of Iowa State University (i.e., ISU-IRT), an experimental campaign was performed to evaluate the effectiveness of using SHS and SLIPS coatings to suppress impact ice accretion over the surfaces of typical airfoil/wing models. While both SHS and

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Akhazhanov, Sungat, and Sergey Skorobogatov. "CONDITIONS FOR THE OCCURRENCE OF ICING ON AERODYNAMIC PROFILES AND METHODS OF THEIR CALCULATION." Herald of Kazakh-British technical university 18, no. 2 (2021): 20–25. http://dx.doi.org/10.55452/1998-6688-2021-18-2-20-25.

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This article analyzes the methods and models suitable for studying the icing of the aerodynamic surface (wing). Systems to counteract the unifying effect are considered. Methods and models for calculating ice formations on aerodynamic surfaces are studied. Further study of the effect of icing will be conducted in the light of the characteristics of flow around bodies of viscous compressible medium in terms of load and liquid phase in case of changes in the geometric parameters of the bodies and reflect this change in the external stream.

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Knyaz, V. A., E. V. Ippolitov, and M. M. Novikov. "3D RECONSTRUCTION OF ICE SHAPE USING VISIBLE AND THERMAL RANGE IMAGING FOR AIRCRAFT ICING STUDY." International Archives of the Photogrammetry, Remote Sensing and Spatial Information Sciences XLIII-B2-2021 (June 28, 2021): 527–32. http://dx.doi.org/10.5194/isprs-archives-xliii-b2-2021-527-2021.

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Abstract. Aircraft icing is one of the main factors decreasing the flight safety. Qualitative and quantitative understanding of the icing process is crucially needed for developing anti-icing measures and safety recommendations. Changes in aerodynamic characteristics of aircraft caused by changes in shape of aircraft surfaces due to the ice accretion can lead to significant aerodynamic performance degradation. So the reliable and accurate information of how the shape of the ice accretion influences on aerodynamic characteristics is a key point for predicting the changes in aerodynamic performa

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4

Xia, Annan, Lei He, Shihang Qie, et al. "Fabrication of an Anti-Icing Aluminum Alloy Surface by Combining Wet Etching and Laser Machining." Applied Sciences 12, no. 4 (2022): 2119. http://dx.doi.org/10.3390/app12042119.

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The phenomenon of icing on the surface of the fuselage while aircraft pass through clouds has an impact on flight safety. This aircraft icing may adversely affect metrological conditions and cause aerodynamic mechanical effects, resulting in a threat to flight safety. This research aims to fabricate an anti-icing surface on a 2524 aluminum alloy material by combining laser machining and wet etching. The microstructure surfaces were obtained by laser, the nanostructured surfaces were obtained by wet etching, and the hierarchical structures were prepared through a combination of these two proces

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Moghtadernejad, S., M. Jadidi, N. Esmail, and A. Dolatabadi. "Shear-driven droplet coalescence and rivulet formation." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 230, no. 5 (2015): 793–803. http://dx.doi.org/10.1177/0954406215590186.

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Icing on aerodynamic surfaces occurs due to the accumulation of rain droplets when the surrounding temperature is below the freezing temperature. It is well known that icing phenomenon alters the aircraft aerodynamic forces and may cause serious damage. Therefore, studying water droplet behavior, such as shedding and coalescence serves as the primary step which can lead to understanding the fundamental physics of aircraft icing. Hence, in this study an experimental approach is used to investigate the shear-driven droplet shedding and coalescence on a hydrophilic substrate which can serve as th

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6

Pan’kov, A. A., and P. V. Pisarev. "Anti-icing indicator polymer coating with built-in fiber-optic PEL-sensor for indication, location and de-icing of aerodynamic surfaces." PNRPU Mechanics Bulletin, no. 4 (December 15, 2021): 111–21. http://dx.doi.org/10.15593/perm.mech/2021.4.11.

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A mathematical model was developed and a numerical modal analysis of the anti-icing mode of operation of the new indicator polymer coating with an integrated optical fiber piezoelectroluminescent (PEL) sensor for icing indication, location and self-cleaning from icing of aerodynamic surfaces was given. The fiber optic PEL-sensor is located in the plane of the coating. Receiver-analyzer of informative integral intensities of light signals is installed at output from optical fiber of sensor. Alternating voltage generator is connected to outputs of two control electrodes of sensor. The anti-icing

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7

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

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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 s

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Fürbacher, Roland, Gerhard Liedl, Gabriel Grünsteidl, and Andreas Otto. "Icing Wind Tunnel and Erosion Field Tests of Superhydrophobic Surfaces Caused by Femtosecond Laser Processing." Wind 4, no. 2 (2024): 155–71. http://dx.doi.org/10.3390/wind4020008.

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Ice accumulation on lift-generating surfaces, such as rotor blades or wings, degrades aerodynamic performance and increases various risks. Active measures to counteract surface icing are energy-consuming and should be replaced by passive anti-icing surfaces. Two major categories of surface treatments—coating and structuring—already show promising results in the laboratory, but none fulfill the current industry requirements for performance and durability. In this paper, we show how femtosecond laser structuring of stainless steel (1.4301) combined with a hydrocarbon surface treatment or a vacuu

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Milles, Stephan, Vittorio Vercillo, Sabri Alamri, et al. "Icephobic Performance of Multi-Scale Laser-Textured Aluminum Surfaces for Aeronautic Applications." Nanomaterials 11, no. 1 (2021): 135. http://dx.doi.org/10.3390/nano11010135.

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Ice-building up on the leading edge of wings and other surfaces exposed to icing atmospheric conditions can negatively influence the aerodynamic performances of aircrafts. In the past, research activities focused on understanding icing phenomena and finding effective countermeasures. Efforts have been dedicated to creating coatings capable of reducing the adhesion strength of ice to a surface. Nevertheless, coatings still lack functional stability, and their application can be harmful to health and the environment. Pulsed laser surface treatments have been proven as a viable technology to indu

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Milles, Stephan, Vittorio Vercillo, Sabri Alamri, et al. "Icephobic Performance of Multi-Scale Laser-Textured Aluminum Surfaces for Aeronautic Applications." Nanomaterials 11, no. 1 (2021): 135. http://dx.doi.org/10.3390/nano11010135.

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Ice-building up on the leading edge of wings and other surfaces exposed to icing atmospheric conditions can negatively influence the aerodynamic performances of aircrafts. In the past, research activities focused on understanding icing phenomena and finding effective countermeasures. Efforts have been dedicated to creating coatings capable of reducing the adhesion strength of ice to a surface. Nevertheless, coatings still lack functional stability, and their application can be harmful to health and the environment. Pulsed laser surface treatments have been proven as a viable technology to indu

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Konovalov, Anatoly, Alexander Skripko, and Ivan Kvaschin. "Optimization of a complex of technological equipment for aircraft processing." E3S Web of Conferences 592 (2024): 07005. http://dx.doi.org/10.1051/e3sconf/202459207005.

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When icing, aerodynamic surfaces of the aircraft, negative changes in the impact of the air flow on them occur, which leads to a noticeable drop in wing lift, a decrease in the efficiency of the rudders, a decrease in the aircraft and loss of control. In order to optimize the complex of technological equipment for anti-icing treatment of the aircraft, the necessary studies of materials and methods of anti-icing treatment of aircraft were carried out, based on the KNO-AERO-MA complex, designed for processing (washing, anti-icing protection) of the outer surfaces of aircraft, due to the existing

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Rotich, Ibrahim Kipngeno, and László E. Kollár. "Numerical study of ice accretion on blade surface with varying cloud characteristics." Journal of Computational and Applied Mechanics 19, no. 1 (2024): 17–35. https://doi.org/10.32973/jcam.2024.002.

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Wind turbines experience the threat of ice accretion under extreme weather conditions. A numerical modeling approach was applied using FENSAP ICE to simulate turbine blade icing and to determine the aerodynamic performance degradation due to ice accretion. Particular attention is paid to the combined effects of the cloud characteristics, i.e. median volume diameter (MVD), liquid water content (LWC) and ambient air temperature, in a relatively wide range that covers in-cloud icing and precipitation icing as well. Depending on these parameters, aerodynamic performance degradation may not occur p

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Sergey, Alekseyenko, and Yushkevich Оleg. "THE DEVELOPMENT OF A THREE-DIMENSIONAL MODEL OF THE ICE GROWTH PROCESS ON AERODYNAMIC SURFACES." Technology audit and production reserves 4, no. 1 (48) (2019): 11–18. https://doi.org/10.15587/2312-8372.2019.145296.

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<em>The object of research is the processes of hydroaerodynamics and heat and mass transfer that occur when icing the aerodynamic surfaces of aircraft during flight in adverse weather conditions. One of the problem areas in the development of software and methodological support that allows to simulate the icing processes, there are difficulties in the transition to solving the problem in three-dimensional formulation. As well as the presence of contradictions in existing methods in describing the physical picture and, accordingly, the thermodynamics of the process of ice growth.</em> <em>Durin

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14

Przybyszewski, Bartlomiej, Rafal Kozera, Zuzanna D. Krawczyk, et al. "A Wind Tunnel Experimental Study of Icing on NACA0012 Aircraft Airfoil with Silicon Compounds Modified Polyurethane Coatings." Materials 14, no. 19 (2021): 5687. http://dx.doi.org/10.3390/ma14195687.

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Ice formation on the aerodynamic surfaces of an aircraft is regarded as a major problem in the aerospace industry. Ice accumulation may damage parts, sensors and controllers and alter the aerodynamics of the airplane, leading to a range of undesired consequences, including flight delays, emergency landings, damaged parts and increased energy consumption. There are various approaches to reducing ice accretion, one of them being the application of icephobic coatings. In this work, commercially available polyurethane-based coatings were modified and deposited on NACA 0012 aircraft airfoils. A hyb

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15

Villeneuve, Eric, Jean-Denis Brassard, and Christophe Volat. "Effect of Various Surface Coatings on De-Icing/Anti-Icing Fluids Aerodynamic and Endurance Time Performances." Aerospace 6, no. 10 (2019): 114. http://dx.doi.org/10.3390/aerospace6100114.

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The Anti-icing Materials International Laboratory (AMIL) has been testing SAE AMS1424 and AMS1428 ground de-icing/anti-icing fluids for more than 30 years. With the introduction of new surface coatings and their investigation as potential passive ice protection systems, or for hybrid use with other methods, it is important to understand their interaction with the ground de-icing/anti-icing fluids prior to applications on aircraft. In this study, five different surface coatings, both commercially available and under development, have been tested under two current test methods used to qualify th

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Lu, Hao, Yongzhong Xu, Hongchang Li, and Wenjun Zhao. "Numerical Study on Glaze Ice Accretion Characteristics over Time for a NACA 0012 Airfoil." Coatings 14, no. 1 (2023): 55. http://dx.doi.org/10.3390/coatings14010055.

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Ice accretion on wind turbine blades can significantly impact their aerodynamic performance, increasing additional load and reducing power generation. This paper utilizes numerical simulation to predict the cross-section at the blade tip of a small wind turbine and study the ice accretion process and aerodynamic characteristics of the airfoil. The research investigates the dynamic characteristics of ice accretion on NACA 0012 airfoil, as well as the influence of dynamic icing at different angles of attack and airflow velocities on the lift coefficient of the airfoil. The findings show that ice

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Zhigulin, Ilya, Kirill Emel'yanenko, and Natalia Sataeva. "Super-hydrophobic coatings application to counteract aircraft aerodynamic surfaces icing." Vestnik Moskovskogo aviatsionnogo instituta 28, no. 1 (2021): 200–212. http://dx.doi.org/10.34759/vst-2021-1-200-212.

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Liu, Bo, Zhiyuan Liu, Yan Li, and Fang Feng. "A Wind Tunnel Test of the Anti-Icing Properties of MoS2/ZnO Hydrophobic Nano-Coatings for Wind Turbine Blades." Coatings 13, no. 4 (2023): 686. http://dx.doi.org/10.3390/coatings13040686.

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Wind turbines operating in cold regions are prone to blade icing, which seriously affects their aerodynamic characteristics and safety performance. Coatings are one of the effective solutions to the icing problem on wind turbine blades. In this study, MoS2/ZnO/PDMS superhydrophobic nano-anti-icing coatings were prepared using the hydrothermal method and the liquid phase method. SEM revealed that the MoS2/ZnO coating was a typical superhydrophobic nanostructure with an ultra-thin sheet-like morphology of clusters and a hilly nano-rough structure, with contact angles (CA) of 152.1° and 4.7° with

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19

Kangash, A. I., E. V. Pankratov, I. A. Kosarev, P. A. Maryandyshev, and M. S. Virk. "Investigation of ice accretion effect on the aerodynamic characteristics of a wind turbine blade tip after a short icing event." IOP Conference Series: Earth and Environmental Science 1154, no. 1 (2023): 012079. http://dx.doi.org/10.1088/1755-1315/1154/1/012079.

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Abstract The paper investigates the flow behavior near the NACA 64-618 airfoil profile of the blade tip section of a wind turbine for electric power production after a short icing event. The flow simulation considering the rotation speed of the wind turbine blade is performed to assess the effect of icing on the aerodynamic characteristics. Degradation of aerodynamic characteristics affects the electrical energy production of the wind turbine. The aerodynamic lift and drag coefficients are calculated for different angles of attack. The flow velocity fields near the airfoil are analyzed. The pr

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Li, Sibo, and Roberto Paoli. "Aircraft Icing Severity Evaluation." Encyclopedia 2, no. 1 (2022): 56–69. http://dx.doi.org/10.3390/encyclopedia2010005.

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Aircraft icing refers to the ice buildup on the surface of an aircraft flying in icing conditions. The ice accretion on the aircraft alters the original aerodynamic configuration and degrades the aerodynamic performances and may lead to unsafe flight conditions. Evaluating the flow structure, icing mechanism and consequences is of great importance to the development of an anti/deicing technique. Studies have shown computational fluid dynamics (CFD) and machine learning (ML) to be effective in predicting the ice shape and icing severity under different flight conditions. CFD solves a set of par

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Maria De Pratti, Giovanni. "New Rotor Blade Profiles Performance Decay in Horizontal Axis Wind Turbines Operating in Aggressive Environment." E3S Web of Conferences 312 (2021): 11013. http://dx.doi.org/10.1051/e3sconf/202131211013.

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At the present time many wind power plants have been developed in mountainous areas, in off-shore sites also at high latitudes and however operating in harsch climate or aggressive environment conditions. In these conditions HAWT’s rotor blades may experiment erosion, corrosion, exfoliation and icing and these operative conditions may cause a remarkable aerodynamical performance decay resulting in a reduction in energy production due to a lower machines availability too. Traditional aerodynamic profiles, as NACA ones, can show high sensitivity to the surface damage or augmented roughness, whil

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G., Prasad, and Bruce Ralphin Rose J. "Experimental and computational study of ice accretion effects on aerodynamic performance." Aircraft Engineering and Aerospace Technology 92, no. 6 (2020): 827–36. http://dx.doi.org/10.1108/aeat-03-2019-0039.

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Purpose The purpose of this paper is to analyse an actual representation of ice accretions, which are important during the certification process. Design/methodology/approach Ice accretion experiments are conducted in a low-speed subsonic wind tunnel testing facility to evaluate the influence of various ice shapes around the airfoil sections. Ice accumulation changes the shapes of local airfoil sections and thereby affects the aerodynamic performance characteristics of the considered NACA 23012 profile. The ice profiles are impregnated using balsa wood with glace, horn and mixed ice accretion c

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Alekseenko, S. V., and O. P. Yushkevich. "Icing of aerodynamic surfaces: modelling the shape of large ice growths." Physical Metallurgy and Heat Treatment of Metals, no. 4 (December 26, 2018): 16–24. http://dx.doi.org/10.30838/j.pmhtm.2413.261218.16.560.

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Li, Sibo, Jingkun Qin, Miao He, and Roberto Paoli. "Fast Evaluation of Aircraft Icing Severity Using Machine Learning Based on XGBoost." Aerospace 7, no. 4 (2020): 36. http://dx.doi.org/10.3390/aerospace7040036.

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Aircraft icing represents a serious hazard in aviation which has caused a number of fatal accidents over the years. In addition, it can lead to substantial increase in drag and weight, thus reducing the aerodynamics performance of the airplane. The process of ice accretion on a solid surface is a complex interaction of aerodynamic and environmental variables. The complex relationship makes machine learning-based methods an attractive alternative to traditional numerical simulation-based approaches. In this study, we introduce a purely data-driven approach to find the complex pattern between di

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Liang, Dong, Pengyu Zhao, He Shen, et al. "An Experimental Study of Surface Icing Characteristics on Blade Airfoil for Offshore Wind Turbines: Effects of Chord Length and Angle of Attack." Coatings 14, no. 5 (2024): 623. http://dx.doi.org/10.3390/coatings14050623.

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Offshore wind turbines operating in frigid and humid climates may encounter icing on the blade surface. This phenomenon adversely impacts the aerodynamic efficiency of the turbine, consequently diminishing power generation efficacy. Investigating the distribution characteristics of icing on the blade surface is imperative. Hence, this study undertook icing wind tunnel tests on segments of DU25 airfoil, a prevalent type for offshore wind turbines, to examine such characteristics as different chord lengths and angles of attack. The results show a simultaneous increase in the blade icing area and

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Lindner, Matthias, Andrei V. Pipa, Norbert Karpen, et al. "Icing Mitigation by MEMS-Fabricated Surface Dielectric Barrier Discharge." Applied Sciences 11, no. 23 (2021): 11106. http://dx.doi.org/10.3390/app112311106.

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Avoiding ice accumulation on aerodynamic components is of enormous importance to flight safety. Novel approaches utilizing surface dielectric barrier discharges (SDBDs) are expected to be more efficient and effective than conventional solutions for preventing ice accretion on aerodynamic components. In this work, the realization of SDBDs based on thin-film substrates by means of micro-electro-mechanical-systems (MEMS) technology is presented. The anti-icing performance of the MEMS SDBDs is presented and compared to SDBDs manufactured by printed circuit board (PCB) technology. It was observed t

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Prykhodko, A. A., and S. V. Alekseyenko. "NUMERICAL INVESTIGATION OF THE INFLUENCE OF SURFACE ROUGHNESS ON CONVECTIVE HEAT TRANSFER AT AIRFOIL ICING PROCESS." Industrial Heat Engineering 40, no. 2 (2018): 65–71. http://dx.doi.org/10.31472/ihe.2.2018.09.

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The technique of the processes of investigating of convective heat transfer determining in the problems of icing of aerodynamic surfaces on the basis of the solution of the Reynolds-averaged Navier- Stokes equations and the one-parameter Spalart-Allmaras turbulence differential model with correction for a rough wall is presented. A methodology that allowed to simulate airfoils icing processes taking into account the ice surface roughness is presented. For the description of the external air-droplet flow a model of interpenetrating media was used. For the description of the ice growing pr

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Mikhailovskiy, K. V., and S. V. Baranovski. "Accounting for Icing in the Design Analysis of Polymer Composite Wings." Proceedings of Higher Educational Institutions. Маchine Building, no. 3 (708) (March 12, 2019): 61–70. http://dx.doi.org/10.18698/0536-1044-2019-3-61-70.

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The aircraft aerodynamic characteristics are directly dependent on their geometry, in particular, on the wing airfoil. The airfoil can change significantly in-flight due to the growth of ice, which can impact effectiveness of the airfoil. Accounting for this phenomenon is a multidisciplinary task that requires an appropriate solution, making it relevant for design calculations. The process of obtaining an ice-covered surface of the aircraft using the performed calculation of the external aerodynamics problem is described in this paper. The shape and geometry, as well as the ice effect on the a

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Niu, Qingfeng, and Mingchuan Yuan. "Numerical Simulation on Dynamic Stall Characteristics of Iced Airfoil for Helicopter Rotor." Journal of Physics: Conference Series 2890, no. 1 (2024): 012061. http://dx.doi.org/10.1088/1742-6596/2890/1/012061.

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Abstract The icing of the rotor blade will change the aerodynamic surface shape of the rotor blade, which will affect the aerodynamic performance of the rotor. In order to study the effect of icing on the stall characteristics of rotor-blade airfoil, especially the dynamic stall characteristics, the airfoil icing shape is obtained by using FENSAP-ICE software, and the dynamic stall characteristics of rotor-blade airfoil OA209 are calculated by using Computational Fluid Dynamics(CFD) software STAR CCM+. The grid of the icing airfoil is an O-shaped grid topology and the background grid adopts a

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Chen, Xi, Wei Bian, Qijun Zhao, and Guoqing Zhao. "Numerical Investigations of Synthetic Jet Control Effects on Iced Airfoils." Energies 16, no. 22 (2023): 7487. http://dx.doi.org/10.3390/en16227487.

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Based on the numerical method, the effects of synthetic jet control (SJC) on the aerodynamic characteristics of iced airfoils are systematically analyzed for the first time. First, an analysis method for the airfoil flowfield under SJC in icing conditions is developed, which contains the CFD method, the icing prediction method, and the boundary conditions of the synthetic jet. Then, the variation in the aerodynamic characteristics of different iced airfoils under the SJC are analyzed, and the flow separation near the ice shape is discussed in detail. Finally, parameters, such as the jet positi

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Ruan, Qikang. "Analysis of the types of aircraft icing and the solutions." Applied and Computational Engineering 9, no. 1 (2023): 177–81. http://dx.doi.org/10.54254/2755-2721/9/20230082.

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Aircraft ice accumulation has a negative impact on flight safety, the smooth flow field on the aircraft surface, flight drag, flight control accuracy, and lift. It interferes with the smooth flow field of the aircraft's surface, increases flight drag, lessens the accuracy of the flight controls, diminishes the lift of the aircraft, and affects the stability and operation of the aircraft. The primary scientific challenge is to catalog the several forms of icing that exist, along with their sources and aerodynamic configuration-related impacts. This paper primarily examines the most efficient de

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Gan, Gan. "The influence of temperature on the properties of anti - ice materials." Journal of Physics: Conference Series 2608, no. 1 (2023): 012006. http://dx.doi.org/10.1088/1742-6596/2608/1/012006.

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Abstract The results of experimental research and practical application of anti-icing surface fully show that its performance is greatly affected by temperature. The anti-icing measures of anti-icing surface can be divided into three stages: before icing, during icing and after icing. In these three stages, the influence brought by temperature change is respectively reflected in: the adhesion of water droplets to the surface, the time it takes for ice nucleation, the adhesion of ice to the surface. Surface anti-ice technology has important application in aviation and aerospace field. The surfa

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Jiang, Feihong, Xiaoxiong Liu, Tongwen Chen, and Kecheng Li. "Research on an Ice Tolerance Control Method for Large Aircraft Based on Adaptive Dynamic Inversion." Actuators 13, no. 6 (2024): 227. http://dx.doi.org/10.3390/act13060227.

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Considering the effect of icing on aircraft control performance, this paper proposes an adaptive dynamic inverse ice tolerance control method based on piecewise constant. A control allocation algorithm is introduced to compensate for the change of control surface performance caused by icing. This method can achieve satisfactory disturbance estimation accuracy under a given sampling time, and thus ensure a closed-loop system error within an acceptable range. The proposed design method is applied to the design of a flight control law for a transport aircraft, aiming to solve the problem of ice-t

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Serino, Andrea, Alberto Dagna, Eugenio Brusa, and Cristiana Delprete. "Digital Twin-Driven Design of an Ice Prediction Model." Aerospace 12, no. 2 (2025): 107. https://doi.org/10.3390/aerospace12020107.

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This paper describes the development of an ice creation model to be used within the framework of a model-based systems engineering approach to predict the amount of ice growing on aircraft wings during flight. This model supports the preliminary design of the ice protection system, as well as the implementation of a control system, in real-time. When the aircraft meets a high concentration of super-cooled water in the atmosphere and a low temperature, the risk of ice formation on its external surfaces is significant. This causes a decrease in aerodynamic performance, with potential loss of con

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Elfitra Desifatma. "Electrical Wing Prototype Anti Icing pada Pesawat Komersil." Jurnal Jaring SainTek 2, no. 2 (2020): 34–41. http://dx.doi.org/10.31599/jaring-saintek.v2i2.331.

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The accumulation of ice on the aircraft's wings can cause a decrease in the aerodynamic properties of the aircraft, increase in weight, and it is difficult to control the aircraft so that it affects aircraft safety. Icing handling on aircraft is growing. One of the newest systems being developed is electrical anti-icing. Therefore, the researcher designed a prototype of an anti-icing electrical wing on a commercial aircraft with advantages in terms of maintenance and lighter components. The purpose of making this prototype is to design an anti-icing electrical wing in the form of a prototype a

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Mu, Zhongqiu, Yan Li, Wenfeng Guo, He Shen, and Kotaro Tagawa. "An Experimental Study on Adhesion Strength of Offshore Atmospheric Icing on a Wind Turbine Blade Airfoil." Coatings 13, no. 1 (2023): 164. http://dx.doi.org/10.3390/coatings13010164.

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When wind turbines work in a cold and humid environment, especially offshore condition, ice accretion on the blade surfaces has a negative effect on the aerodynamic performance. In order to remove the ice from the wind turbine blade, the adhesive characteristics of atmospheric icing on the blade surface should be mastered under various conditions. The objective of this study is to evaluate the effects of offshore atmospheric conditions, including wind speeds, ambient temperatures and, especially, the salt contents on ice adhesion strength for wind turbine blades. The experiments were conducted

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Wang, Kang, Yuan Xue, Hongfeng Tian, Miaosen Wang, and Xiaolong Wang. "The Impact of Icing on the Airfoil on the Lift-Drag Characteristics and Maneuverability Characteristics." Mathematical Problems in Engineering 2021 (June 12, 2021): 1–16. http://dx.doi.org/10.1155/2021/5568740.

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Icing has now become an important factor endangering flight safety. This paper takes the icing data of the NACA 23012 airfoil as an example, establishes an icing influence model for real-time simulation based on icing time and aircraft angle of attack, and analyzes the influence of different icing geometry on aircraft characteristics. The two-dimensional interpolation method is used to improve the model of the aircraft’s stall area, which is mainly divided into the correction of the lift-drag coefficient linear area and the stall area and the correction of the aircraft stability derivative and

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Wang, Guoqiang, Qiuyun Mo, Rongjiang Tang, et al. "Numerical Calculation Method of Spanwise Icing Characteristics and Performance Loss of Three-Dimensional Vertical Axis Wind Turbine Blades." Journal of Sensors 2022 (October 10, 2022): 1–13. http://dx.doi.org/10.1155/2022/1527169.

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Most icing studies use 2D or quasi-3D models, ignoring the effects of blade span and tip icing. In this paper, a new model for predicting 3D vertical axis wind turbine blades icing by supplementing the blade span is established, the icing characteristics of blades under multiple working conditions are simulated step by step from the time scale, and the unsteady icing laws are compared and analyzed. Ice properties and surface temperature distribution determine the corresponding deicing power. The analysis results show that the unfrozen water film flows in the spanwise direction of the blade, re

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39

Rodrigues, Frederico, Mohammadmahdi Abdollahzadehsangroudi, João Nunes-Pereira, and José Páscoa. "Recent Developments on Dielectric Barrier Discharge (DBD) Plasma Actuators for Icing Mitigation." Actuators 12, no. 1 (2022): 5. http://dx.doi.org/10.3390/act12010005.

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Ice accretion is a common issue on aircraft flying in cold climate conditions. The ice accumulation on aircraft surfaces disturbs the adjacent airflow field, increases the drag, and significantly reduces the aircraft’s aerodynamic performance. It also increases the weight of the aircraft and causes the failure of critical components in some situations, leading to premature aerodynamic stall and loss of control and lift. With this in mind, several authors have begun to study the thermal effects of plasma actuators for icing control and mitigation, considering both aeronautical and wind energy a

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Zhang, Ting, Yangyang Lian, Zhi Xu, and Yan Li. "Effects of Wind Speed and Heat Flux on De-Icing Characteristics of Wind Turbine Blade Airfoil Surface." Coatings 14, no. 7 (2024): 852. http://dx.doi.org/10.3390/coatings14070852.

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The icing on wind turbines reduces their aerodynamic performance and can cause other safety issues. Accordingly, in this paper, the de-icing characteristics of a wind turbine blade airfoil under different conditions are investigated using numerical simulation. The findings indicate that when the de-icing time is 10 s, the peak ice thickness on the leading edge of the airfoil surface decreases from 0.28 mm to 0.068 mm and from 0.77 mm to 0.45 mm at low (5 m/s) and high (15 m/s) wind speeds, respectively. This is due to the fact that the ice melting rate is much greater than the icing rate at lo

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Caccia, Francesco, and Alberto Guardone. "Numerical simulations of ice accretion on wind turbine blades: are performance losses due to ice shape or surface roughness?" Wind Energy Science 8, no. 3 (2023): 341–62. http://dx.doi.org/10.5194/wes-8-341-2023.

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Abstract. Ice accretion on wind turbine blades causes both a change in the shape of its sections and an increase in surface roughness. These lead to degraded aerodynamic performances and lower power output. Here, a high-fidelity multi-step method is presented and applied to simulate a 3 h rime icing event on the National Renewable Energy Laboratory 5 MW wind turbine blade. Five sections belonging to the outer half of the blade were considered. Independent time steps were applied to each blade section to obtain detailed ice shapes. The roughness effect on airfoil performance was included in com

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Yoon, Taekeun, and Kwanjung Yee. "Correction of Local Collection Efficiency Based on Roughness Element Concept for Glaze Ice Simulation." Journal of Mechanics 36, no. 5 (2020): 607–22. http://dx.doi.org/10.1017/jmech.2020.29.

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ABSTRACTIn glaze ice conditions, beads on the surface usually grow to form roughness elements through coalescence, finally resulting in enhancement of local collection efficiency. However, the effects of roughness elements due to freezing of beads are not reflected on the local collection efficiency in CFD icing simulations. This is problematic for predicting the resultant ice shape, which may lead to inaccurate aerodynamic performance and load distribution. The aim of this study is to propose a macroscopic icing model which can reflect bead microscopic phenomena using the Eulerian approach. T

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Shi, Weihan, Sicheng Shen, Guoan Hou, Juan Ding, Wenfeng Guo, and Yingwei Zhang. "Icing and Adhesive Characteristics of Iced Airfoils Under Rime Ice Conditions." Coatings 15, no. 5 (2025): 606. https://doi.org/10.3390/coatings15050606.

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Airfoils are widely used in the fields of aviation and wind power generation. Icing changes the profile of an airfoil and degrades its aerodynamic performance. Therefore, it is necessary to explore the icing of airfoils and the adhesive characteristics of the ice formed in order to explore their de-icing. In the present study, this is accomplished for the NACA0018 and S809 airfoils through measurement of the areas, thicknesses, and adhesive strength of the ice formed under different wind speeds. The iced area increased linearly with the icing time. The area on the S809 airfoil covered with ice

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Martini, Fahed, Hussein Ibrahim, Leidy Tatiana Contreras Montoya, Patrick Rizk, and Adrian Ilinca. "Turbulence Modeling of Iced Wind Turbine Airfoils." Energies 15, no. 22 (2022): 8325. http://dx.doi.org/10.3390/en15228325.

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Icing is a severe problem faced by wind turbines operating in cold climates. It is affected by various fluctuating parameters. Due to ice accretion, a significant drop in the aerodynamic performance of the blades’ airfoils leads to productivity loss in wind turbines. When ice accretes on airfoils, it leads to a geometry deformation that seriously increases turbulence, particularly on the airfoil suction side at high angles of attack. Modeling and simulation are indispensable tools to estimate the effect of icing on the operation of wind turbines and gain a better understanding of the phenomeno

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García, Paloma, Julio Mora, Miguel González del Val, Francisco Carreño, Francisco Javier García de Blas, and Alina Agüero. "Considering Thermal Diffusivity as a Design Factor in Multilayer Hybrid Ice Protection Systems." Coatings 12, no. 12 (2022): 1952. http://dx.doi.org/10.3390/coatings12121952.

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Icing is a major problem that affects the aeronautical sector, which is forced to use anti- and de-icing systems to ensure flight safety. The currently used systems are effective but exhibit high energy consumption. Resistive heating is used to prevent ice accretion or to release it once it has formed. To satisfy all the imposed airworthiness requirements, such as low aerodynamic impact, resistance to lightning strikes, no overheating, etc., multilayer systems are commonly configured with different layers fulfilling specific functions. For example, the Boeing 787 Dreamliner uses dry woven glas

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Yue, Ting, Xianlong Wang, Bo Wang, et al. "Design of Ice Tolerance Flight Envelope Protection Control System for UAV Based on LSTM Neural Network for Detecting Icing Severity." Drones 9, no. 1 (2025): 63. https://doi.org/10.3390/drones9010063.

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Icing on an unmanned aerial vehicle (UAV) can degrade aerodynamic performance, reduce flight capabilities, impair maneuverability and stability, and significantly impact flight safety. At present, most flight control methods for icing-affected aircraft adopt a conservative control strategy, in which small control inputs are used to keep the aircraft’s angle of attack and other state variables within a limited range. However, this approach restricts the flight performance of icing aircraft. To address this issue, this paper innovatively proposes a design method of an ice tolerance flight envelo

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Uranai, Sho, Koji Fukudome, Hiroya Mamori, Naoya Fukushima, and Makoto Yamamoto. "Numerical Simulation of the Anti-Icing Performance of Electric Heaters for Icing on the NACA 0012 Airfoil." Aerospace 7, no. 9 (2020): 123. http://dx.doi.org/10.3390/aerospace7090123.

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Ice accretion is a phenomenon whereby super-cooled water droplets impinge and accrete on wall surfaces. It is well known that the icing may cause severe accidents via the deformation of airfoil shape and the shedding of the growing adhered ice. To prevent ice accretion, electro-thermal heaters have recently been implemented as a de- and anti-icing device for aircraft wings. In this study, an icing simulation method for a two-dimensional airfoil with a heating surface was developed by modifying the extended Messinger model. The main modification is the computation of heat transfer from the airf

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48

Fevralskikh, A. V. "METHOD OF DESIGN AND GEOMETRICAL TRANSFORMATION OF HIGHSPEED AMPHIBIOUS VEHICLE AIRFOILS." Vestnik komp'iuternykh i informatsionnykh tekhnologii, no. 249 (March 2025): 41–49. https://doi.org/10.14489/vkit.2025.03.pp.041-049.

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The development of methods for determining the geometric parameters of the shape and design of the lifting surfaces of high-speed amphibious vessels using the positive influence of the ground effect is an inportant task on the way to creating new models of this type of transport – in particular, intended for operation in the North, in conditions of possible icing, which affects both the characteristics of lift and drag, and the characteristics of longitudinal static stability of cruising motion. At present, there are no clearly algorithmic methods for designing an aerodynamic profile of a scre

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Lozowski, E. P., A. M. Kobos, and L. G. Kachurin. "Influence of the Surface Liquid Film on Cylinder Icing Under Marine Conditions." Journal of Offshore Mechanics and Arctic Engineering 118, no. 2 (1996): 158–64. http://dx.doi.org/10.1115/1.2828826.

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A new steady-state icing model is presented Which explicitly takes into account the dynamics and thermodynamics of a liquid film on the ice accretion surface under high liquid fluxes. The film is generated by excess unfrozen impinging liquid, is set in motion by the aerodynamic shear stress, and is eventually shed. In order to keep the model simple, it is formulated for a rotating cylinder subjected to a continuous supercooled freshwater spray. The model is used to explore the physics of the liquid film, and confirms that the film is thin and laminar except possibly under extreme liquid fluxes

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50

Toba, D., K. Fukudome, H. Mamori, N. Fukushima, and M. Yamamoto. "Proposal of Novel Icing Simulation Using a Hybrid Grid- and Particle-Based Method." Journal of Mechanics 36, no. 5 (2020): 699–706. http://dx.doi.org/10.1017/jmech.2020.35.

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ABSTRACTIcing on aircraft can drastically reduce aerodynamic performance and lead to serious accidents. Therefore, prediction of the accreted ice shape and area and its effects on aerodynamic performance is crucial during the design phase of an aircraft. However, numerical simulations based on conventional grid-based methods such as the finite volume method cannot accurately reproduce the complex ice shapes, which involve horn growth, feather growth, air voids, and severe surface roughness. In the present study, instead of the grid-based method, a hybrid grid- and particle-based method was new

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