Mathematical models of 3-D simulation of icing for aerodynamic surfaces of a promising airplane of local airlines using additive SLA technology

RFBR project number: 19-29-13016 мк

Project manager: Strijhak Sergei


The urgency of the tasks to ensure the safety and reliability of flights, as well as the protection of aircraft from disasters, including in the Northern regions of the Russian Federation, is increasing due to the emergence of new types of structures, advanced technologies and materials, including polymer composite materials, from which the main power elements and assemblies of such technical objects are made. One of the urgent problems in aviation is the problem of studying and modeling the process of ice formation. The need to combat icing affects not only classical objects such as aircraft and ships, but also unmanned aerial vehicles, power wires, runways. In particular, the problems of icing are extremely relevant in the Arctic zone of the Russian Federation. In the harsh conditions of the Arctic zone, the greatest danger of icing is for regional aviation. The increase in ice, ice plaque, snow on the wing and tail of a light convertible aircraft, a promising aircraft of local air lines, under certain conditions, is very fast and uneven, which leads to a decrease in the lift of the wing for 30% and an increase in drag for 40%.

The interdisciplinarity of the work is consideration of the phenomenon of ice formation using the laws of mechanics, physical models for deposition of ice crystals and the dynamics of the liquid film, models for polydisperse blend drops of a laboratory experiment in wind tunneles, the numerical simulation of additive technologies for making models for the experiment. The significance of this work is that the developed software package for modeling ice formation processes will be open source and can be used at aviation enterprises, design bureaus, and scientific organizations in the Russian Federation.

The scientific novelty of the work consists in refining the model for barrier ice taking into account the formation and dynamics of a liquid film moving on the surface of a solid, a new model for a polydesperse mixture of droplets and the development of a new simulation code. The result of project will be a software package for modeling the processes of ice formation, to carry out calculations, to design and use experimental models of the wing with various laws of ice buildup, manufactured using additive SLA-technology based on industrial 3D printers, with mechanical properties close to the properties of polymer composite materials, and to verify and control the compliance of the characteristics of the elements of the aircraft with modern Airworthiness standards.

Results of the work in 2020 year

Project participants developed a prototype of the iceFoam solver iceFoam based on the free OpenFOAM v1912 package for modeling the dynamics of liquid particles and ice formation on the body surface. So far, the solver is designed for particles with a characteristic size of about 40 microns, which corresponds to Appendix C of the AP-25 Aviation rules. Work is underway to expand the solver’s capabilities (in the direction of modeling various modes and types of ice build-up) based on the open packages Yade and OpenFOAM for the “Snow and Blizzard” Apendix.

Modeling of multiphase flows with continuous and dispersed phases is carried out using the Euler-Lagrangian approach, in which the continuous phase is considered in the Euler formulation, while droplet particles in the dispersed phase are tracked in the Lagrangian formulation. Currently, iceFoam includes a basic solver and two libraries: one library implements the thermodynamic model of a liquid film based on the theory of shallow water libsurfaceFilmModelsSWIM, the second library is designed for calculating droplet particles libIceFoamParticles. The calculation uses two meshes: one for modeling the external gas-drop flow, and the other, with a thickness of one cell, for calculating the ice accretion. The ice accretion leads to a change in the initial body shape. The boundary of the body moves in space along the normal. However, when recalculating the position of mesh nodes, you must ensure that the borders for two different meshes are moved simultaneously. One of the most effective ways to do this is to use the solution of the Laplace equation. The general structure of the iceFoam solver is shown in figure 1.

Figure 1. Structure of the iceFoam solver

Test simulation of ice freezing on the cylinder, NACA0012 and GLC-305 profiles were made using the RANS method and the Spalart-Allmares high-Reynolds turbulence model (Fig. 2).




Figure 2. Simulation results for: a) cylinder; b, c) wing profiles.

To calculate one example, we used from 8 to 32 computational cores on computing clusters of ISP RAS and SIC “Kurchatov Institute”. The acceleration of the developed solver was also estimated.

A mathematical model for the simulation of snowflakes

We use the Euler-Lagrangian approach – a conjugate method based on computational fluid dynamics and the discrete element method (DME).

In standard Euler-Lagrangian modeling of multiphase flows loaded with particles, the particles are considered as point masses. The flow at the particle level is not allowed, and analytical / empirical models of hydrodynamic forces are used to describe the interaction of liquid and particles.

The Discrete element method

The Discrete Element Method (DEM) is a Lagrangian method, in the sense that all particles in the computational domain are tracked by explicitly solving their trajectories. DEM is well suited for studying the behavior of a large number of particles at the microscopic level, for example, to describe the movement, deposition, agglomeration, or aggregation of a large number of adhesive particles, including those submerged in liquid or gas flows.

Depending on the software, this method makes it possible to track the elastic interactions of particles, their deformations, interaction with friction, cohesion and adhesion forces, and to study the influence of temperature and pressure, as well as mechanical effects when modeling complex systems. Including systems of complex geometry, moving or rotating systems.

When combined with a hydrodynamic solver, particle dynamics can be studied in a developed liquid or gas flow, taking into account the interaction of the medium with particles.

The basic principles of DEM are as follows. The simulation begins with placing all the particles in a specific position and giving them an initial velocity. Then the forces acting on each particle are calculated based on the initial data and the corresponding physical laws.

The equations in DEM are solved using explicit time schemes. In this regard, all the forces acting on the particle are added together to determine the resulting force. The change in the position and velocity of each particle during a certain time step is calculated from Newton’s laws using the integration method. After that, the new position is used to calculate the forces in the next time step, and this program cycle is repeated until the simulation ends.

The method of computational fluid dynamics

To describe the flow aerodynamics, a classical hydrodynamic approach is used using the finite volume method for solving the Navier-Stokes equations. This approach is the Eulerian. The flow in the problems under study is assumed to be incompressible.


To calculate this task, we combine two open source software codes: YADE and OpenFOAM.

The advantages of the YADE package are the following features:

  • the calculation of complex shape particles;
  • the calculation of complex models of particle interaction (taking into account cohesion, friction, elasticity, deformation, anisotropy, and other material properties);
  • the solver works in parallel mode using the MPI library.

Advantages of the OpenFOAM package:

  • good documentation;
  • C++ – based modular code structure;
  • wide distribution;
  • large number of developers and users;
  • extensive experience in implementing new models.

Development of the snowFoamYade solver

The snowFoamYade solver is based on the icoFoamYade solver, in which particles are represented as point masses that are affected by a hydrodynamic drag force. In the icoFoamYade solver, this force is represented by the Stokes drag force, which is not suitable for calculating the dynamics of snow crystals. Japanese scientist Ishizaka calculated the drag force for a snow crystal, which is a function of the Reynolds number over the particle diameter to the power of -0.28. in the snowfoamyade solver, the drag force is calculated using the Ishizaki formula.

Solution algorithm

The following sequence of actions is repeated in the DEM calculation:

  • exchange of information with the CFD calculation (determination of hydrodynamic forces acting on particles);
  • approximate collision detection;
  • detect exact collisions of bodies, update interactions as necessary;
  • calculation of interactions when forces are applied to bodies;
  • application of other external forces (for example, gravity and hydrodynamic forces);
  • changing the position of bodies based on forces, by integrating the equations of motion;
  • exchange of information (acceleration, velocity, mass and coordinates of particles) with CFD calculation.

The CFD calculation uses the following sequence of actions:

  • getting information from the DEM solution (acceleration, velocity, mass, and particle coordinates);
  • pressure, velocity, and density fields are corrected;
  • the law of conservation of the amount of traffic is being solved;
  • solution of the continuity equation for pressure field correction;
  • speed field correction;
  • correction of the pressure field based on the updated velocity field;
  • information exchange with DEM calculation (velocity field, pressure field).

Results and conclusions

In this work, the simulation of the flow of air around the cylinder in a rectangular cross-section pipe was carried out. It was calculated 8 seconds of the process, the results of the calculation were made following conclusions:

discrete element method is well suited to simulate the adhesion of ice crystals on the surface of the model body, the maximum thickness of the ice growth normal to the streamline body was 2 cm, the average thickness of the ice growth normal to the streamline body was 1 cm, the angle of the buildup of the snow cover amounted to 110 degrees (Fig. 3).

This approach is promising because it is possible to model the stress-strain state of the ice crust, the process of its destruction, and the interaction of complex particles.

Fig. 3 Calculation of the flow around the cylinder in snowYadeFoam at time t=8 seconds

List of publications 2020

1. Koshelev K.B., Melnikova V.G., Strijhak S.V. Development of iceFoam solver for modeling ice accretion. Proceedings of the Institute for System Programming of the RAS (Proceedings of ISP RAS). 2020;32(4):217-234. (in Russian)

2. Mel’nikova V.G., Koshelev K.B., Strizhak S.V. Modelirovanie obtekaniya profilya gazokapel’nym potokom i raschet tolshchiny zhidkoj plenki [Modeling of gas-drop flow around the profile and calculating the thickness of the liquid film]. Tezisy dokladov, predstavlennye na XXIV Mezhdunarodnuyu konferenciyu «Nelinejnye zadachi teorii gidrodinamicheskoj ustojchivosti i turbulentnost’» [Abstracts presented at the XXIV International conference “Nonlinear problems of the theory of hydrodynamic stability and turbulence”] (in Russian). 2020. p. 67.

3. K.B. Koshelev, V.G. Melnikova, S.V. Strijhak. Using a Thermodynamic Film Model Based on Shallow Water Theory and a Dynamic Mesh Model for the Icing of 2D/3D Bodies in the iceFoam Solver Simulation. //Int. Conf. on the Methods of Aerophys. Research (Novosibirsk, Russia, November 1-7, 2020): Abstracts. Pt. I. Novosibirsk: Parallel, 2020. P. 123-124.

List of conferences 2020

1. S.V. Strizhak, K.B. Koshelev, V.G. Melnikova. Development of the iceFoam solver for modeling ice accretion. International conference “Ivannikov readings”. Russia, Orel, 25-26.09.2020.

2. D.I. Romanova, S.V. Strizhak. Modeling the cylinder icing process using the CFD-DEM approach, using the YADE and OpenFOAM packages. International conference “Ivannikov readings”. Russia, Orel, 25-26.09. 2020.

3. D.I. Romanova, S.V. Strizhak. Modeling of the Icing Process for a Model Body, Taking into Account the Movement of Snow Crystals. Russian conference of young mechanical scientists (YSM-2020). Russia, Sochi, Burevestnik MSU, 3-13.09.2020.

4. K.B. Koshelev, S.V. Strizhak. Model Films Based on Shallow Water Theory for Modelling the Icing of the Airfoil and the Cylinder. XXXI scientific and technical conference on aerodynamics. Park – hotel “Yahonty”. 29-30.10.2020.

Results of the work in 2021 year

The iceFoam solver prototype for icing modeling based on the OpenFOAM v1912 open source package has been developed as the ICELIB library, which contains three new versions of the solver: iceFoam1, iceDyMFoam2, iceDyMFoam3. They are based on the Euler approach for the gas phase, the Lagrangian approach for modeling the motion of water droplets, and the shallow water model for describing a liquid film on the profile surface. Each version is designed for a specific type of task.

iceFoam1 is developed to estimate the icing area of a 3D wing, provided that the thickness of the ice layer is sufficiently small and the change in the profile surface during icing can be neglected. Two other versions are aimed at modeling icing with rime and glaze ice and take into account the effect of changing the profile geometry. The iceDyMFoam2 solver is better at simulating various types of ice but is limited by the number of processing cores for parallel computing, unlike iceDyMFoam3.

To verify the solvers, a series of icing calculations for various 2D airfoils (NACA 0012, GLC-305, General Aviation, Business Jet, Commercial Transport) and a 3D swept wing were performed. The deviation of the calculation results from the experimental data did not exceed 10%.

The calculation of the 3D swept wing with the profile GLC-305 was carried out in the area bounded by a parallelepiped of size 7 m × 3 m × 3 m. The computational adaptive unstructured grid contained about 1.3 × 106 nodes and had two subdomains: the near-wall subdomain of the film with a height of one computational cell (the characteristic cell size is about 4 mm) and the outer subdomain for modeling the gas-droplet flow. Figure 1 shows a grid with 5 levels of adaptation. The calculations were carried out for the “rime ice”: flow velocity V=90 m/s, angle of attack 6˚, air temperature T = 261.87 K, LWC = 0.51 g/m3, particle diameter d = 14.5μm, icing time t = 300 s. Time step 6 × 10-5 s. The calculation was performed by the iceDyMFoam3 version on the HPC4 computing cluster of the NRC Kurchatov Institute ( for 33 hours on 24 computing cores.

Fig. 1. Mesh with 4 levels of adaptation

a) top view

b) bottom view

Fig. 2. Velocity field and particle trajectories around a swept wing

Figure 2 shows the vertical component of water droplets velocity (top view). In terms of the maximum ice thickness (about 3 mm) and ice shape, the simulation results are close to the experimental data, which indicates the solver’s ability to simulate three-dimensional icing processes.

To simulate the dynamics droplets were considered as spheroids, as a result of which the lifting force, as well as the rotational moment of the force, were added to the consideration. A software package for calculating plane trajectories of spheroid particles in an external aerodynamic field has been developed.

A numerical simulation of the motion of supercooled water drops near the cylinder at a mixed flow velocity of 9 m/s, a temperature of 268 K, and the intensity of turbulent pulsations on the left boundary of 5% was carried out. The calculation of aerodynamic fields near the cylinder was performed using the k-omega SST turbulence model. Air viscosity was determined using the Sutherland formula. The simulation results show that the nonsphericity of particles leads to additional scattering, and the maximum value of the collision coefficient is observed for spherical particles, which is in good agreement with other models.

An algorithm for the influence of turbulent pulsations of a carrier flow on particle trajectories is considered and implemented using the Langevin equation under the assumption of their isotropy. It has been established by numerical simulation that turbulent fluctuations do not have a significant effect on the cumulative particle capture coefficient. A criterion is obtained for assessing the presence of fragmentation of droplets colliding with the surface when flowing around a body for given flow parameters.

Several numerical experiments were performed to simulate a mixed flow around a cylinder with the following parameters: droplet radius from 5 to 100 µm; cylinder radius 0.1 m, free flow velocity 100 m/s, atmospheric pressure; temperature -10 ˚C. The effect of droplet crushing on the cumulative difference in the distribution of mass and number concentrations of drops is established. Figure 3 shows the changes in the size of the droplets as they interact with the cylinder in the gas flow. The influence of the number of drops on the mass concentration distribution is insignificant.

Fig. 3. Visualization of the behavior of drops during their crushing for different values of N.

The research results presented in the paper can be used in calculations of icing and serve as a basis for the problem of counteracting this phenomenon.

List of publications 2021

  1. Koshelev K.B., Osipov A.V., Strijhak S.V. Osobennosti realizacii reshatelya iceFoam dlya resheniya zadachi modelirovaniya obledeneniya strelovidnogo kryla sverhzvukovogo samoleta. Proceedings of the XXII International Conference on Computational Mechanics and Modern Applied Software Systems (CMMASS’2021). Alushta, Crimea, 2021. P. 394-395. (in Russian).
  2. Strijhak S.V. Development of an efficient parallel computing algorithm for modeling swept wing icing using a solver iceFoam. Abstracts presented at: II International Conference “Mathematical Modelling” (AviaSpace-2021). Moscow, 2021. P. 79-81.
  3. Koshelev K.B., Osipov A.V., Strijhak S.V. Features of the implementation of an efficient parallel computation algorithm for modeling the icing of a swept wing with a GLC-305 airfoil. Trudy ISP RAN/Proc. ISP RAS, vol. 33, issue 5, 2021, pp. 249-258 (in Russian).
  4. Amelyushkin I.A., Kudrov M.A., Morozov A.O., Shcheglov A.S. Mathematical models and methods of numerical investigation of processes which accompany aircraft icing Trudy ISP RAN/Proc. ISP RAS, vol. 33, issue 5, 2021, pp. 237-248 (in Russian).–2021–33(5)–14.

List of conferences 2021

  1. Strijhak S.V. Разработка эффективного алгоритма параллельных вычислений для моделирования процесса обледенения стреловидного крыла с использованием решателя iceFoam. II International Conference “Mathematical Modelling” (AviaSpace-2021). Moscow, 2021. MAI, 21-22.06.2021.
  2. Koshelev K.B., Osipov A.V., Strijhak S.V. Features of the implementation of an efficient parallel computation algorithm for modeling the icing of a swept wing with a GLC-305 airfoil. International conference «Ivannikov Memorial Workshop 2021». Nizhny Novgorod. ISP RAS, 24-25.09.2021.
  3. Koshelev K.B., Osipov A.V., Strijhak S.V. Osobennosti realizacii reshatelya icefoam dlya resheniya zadachi modelirovaniya obledeneniya strelovidnogo kryla sverhzvukovogo samoleta. XXII International Conference on Computational Mechanics and Modern Applied Software Systems (CMMASS’2021). Alushta, Crimea, 2021. 4-13.09.2021.
  4. Amelyushkin I.A., Kudrov M.A. Vzaimodejstvie pereohlazhdennyh kapel’ s rel’efnym telom v potoke gaza. XXII International Conference on Computational Mechanics and Modern Applied Software Systems (CMMASS’2021). Alushta, Crimea, 2021. 4-13.09.2021.
  5. Korchagova V.N. Ispol’zovanie algoritmov dinamicheskogo perestraivaniya setki pri reshenii zadach gazovoj dinamiki razryvnym metodom Galerkina. All-Russian Aeroacoustic Forum. Gelendzhik. TsAFI, 20-25.09.2021.
  6. Koshelev K.B., Osipov A.V., Strijhak S.V. Application of the iceFoam solver to simulate swept wing icing with GLC-305 airfoil. The XXVII All-Russian conference, “High-Energy Processes in Condensed Matter” (HEPCM). Novosibrsk, ITAM SB RAS, 20-24 сентября 2021.
  7. Konstantin Koshelev, Andrey Osipov, Sergei Strijhak. The simulation of a gas-droplet flow around a swept wing of a supersonic jet aircraft in order to determine ice accretion using iceFoam solver. V International Conference on Aerospace System Science and Engineering ICASSE 2021, 14-16 July 2021, Virtual Event.

Results of the work in 2022–2023 years

New advanced supersonic passenger aircraft are currently being designed. In this regard, work is underway to design and test a demonstration aircraft. For example, this is a model aircraft within the framework of the World-Class Research Center project “Supersonic” (Russia) and the current project of the Lockheed Martin X-59 QueSST demonstrator aircraft (USA). This demonstrator aircraft lands and takes off at specific altitudes at subsonic speeds. While the demonstration aircraft is moving in clouds, there is a possibility of icing, which is a dangerous phenomenon, as it reduces the aerodynamic characteristics of the aircraft. The ice formed is of different types and forms: loose, transparent, barrier, mixed, horn-like, rough. Therefore, it is necessary to conduct scientific research to study this phenomenon. One possible approach is to model ice build-up using numerical models. A 3D digital model of the X-59 demonstration aircraft is publicly available. In this study, only the triangular wing of complex shape is considered (Fig.1).

Fig. 1. X-59 model on the left and X-59 wing model on the right.

Wing icing is modeled using the iceFoam solver developed within the OpenFOAM package. Two unstructured meshes are used to solve the problem: the first one in the outer region and the second one for the liquid film near the solid. The blockMesh and snappyHexMesh utilities within the OpenFOAM package are used to construct the gas phase mesh. Calculations were performed for the wing models of the X-59 demonstrator aircraft at a scale of 1:25 and 1:1 for the case of rime ice. For the different scale models, the Reynolds and Mach numbers were kept constant. At the same time, air water content and median diameter of water droplets were unchanged in dimensional form. Fig.2 shows the difference in the position of icing areas on the lower surface of the wing fragment for the different-scale models.

Fig. 2. Left – position of ice (highlighted in blue) on the bottom surface of the wing fragment for the 1:25 scale model, right – position of ice on the bottom surface of the wing fragment for the 1:1 scale model.

The preliminary conclusion is that even the coincidence of the Reynolds and Mach numbers for the carrier phase is not enough for different-scale icing models. It is necessary to conduct additional studies with different wing scales.

The task of studying the icing process is also relevant in connection with the operation of large ships and fishing vessels in the seas of the Arctic Ocean. In this study, icing of a fishing vessel is simulated at different Reynolds and Froude numbers. Using the interDyMFoam solver, the position of waves and water spray in space when the ship was moving was determined, taking into account sea waves. The iceFoam solver was used to simulate the process of icing of the ship’s surface. Calculations were performed for an average volume drop diameter of 1000 microns, wind speed of 10 m/s and ship speed of 5 m/s. Fig.3 shows the calculated data on the position of the water film and the ice accretion after 8 s.

Fig. 3. Left – position of water film (highlighted in red), right – position of ice accretion (highlighted in red).

In the framework of this project, studies of the interaction of droplets with a solid surface were carried out. An original criterion of the crushing mode of droplets colliding with the surface and depending on the parameters of the aerosol flow was formulated to assess the presence of crushing when flowing around the body at given parameters. The effect of droplet fragmentation on the integral difference in the distribution of mass and countable droplet concentrations is shown. The results of analytical and numerical studies presented in the paper can be used in calculations of icing and serve as a basis in problems of counteraction to this phenomenon. It is shown for the first time that the dependence of the increase due to crushing of the mass concentration of droplets on the initial size of the droplets (or the corresponding Weber number) is non-monotone when the body is streamlined by a gas-droplet flow.

The dependences of the concentration, velocity and size distribution of particles in the boundary layer of an air flow at a snow-covered surface on the main controlling parameters have been determined. A numerical algorithm has been developed, and the results have been verified and validated on the basis of available experimental data. Models of the dynamics of particles in the boundary layer near the surface of a streamlined body have been developed.

A physico-mathematical model and an original method for calculating the modes of interaction of ice crystals with the heated surface of the streamlined body have been developed (Fig. 4). The nodes of the computational mesh are deformed when the loads change during the time of the crystal impact on the surface of the heated body, heat flows and momentum transfer are calculated between the cells, while the cells are removed during the melting process based on the mass entrainment rate during the crystal impact on the surface of the streamlined body. The method is also applied to calculate the occurrence of stresses and ice fracture on the wing under the action of aerodynamic and mechanical loads. The developed method and the numerical algorithm for its implementation can be used in the calculation of icing for cases of long ice build-up time and to calculate the parameters of vibration and deformation anti-icing systems. In the present study, it was first applied to the problem of determining the parameters of heat exchange of a crystal during its collision with a solid, taking into account the viscosity of the solid and the transition of the kinetic energy of motion of solid layers and their deformation into thermal energy due to the viscosity of the solid.

Fig. 4. From left to right: scheme of the elementary act of particle impact on heated surface, scheme of gridless modeling of crystal impact on heated surface, calculation of change in velocity components of crystal impact on solid surface, scheme of calculation of stresses in ice on wing.

The research was supported financially by the Russian Foundation for Basic Research within the framework of the scientific project № 19-29-13016.

List of publications 2022-2023

  1. Стрижак, С.В. Развитие модели нейронной сети iceMPLNet для предсказания формы льда / С.В. Стрижак, К.Б. Кошелев, Д.И. Романова // Материалы XIV Международной конференции по прикладной математике и механике в аэрокосмической отрасли (AMMAI’2022) : Материалы конференции, Алушта, 04–13 сентября 2022 года. – Москва: Московский авиационный институт (национальный исследовательский университет), 2022. – С. 396-399.
  2. Стрижак, С.В. Алгоритм исключения “плохих” расчетных ячеек для моделирования процесса обледенения крыла самолета / С.В. Стрижак, К.Б. Кошелев, А. В. Осипов // Авиация и космонавтика: тезисы 21-ой международной конференции, Москва, 21–25 ноября 2022 года / Московский
    авиационный институт (национальный исследовательский университет). – Москва: Издательство “Перо”, 2022. – С. 425-427.
  3. Koshelev, K.B. Investigation of ice growth on a swept wing with considering the model of uniform roughness / K.B. Koshelev, A.V. Ivanov, S.V. Strijhak // ХХI International Conference on the Methods of Aerophysical Research (ICMAR 2022): Abstracts, Novosibirsk, 08–14
    августа 2022 года. Vol. Part I. – Novosibirsk: Федеральное государственное бюджетное учреждение «Сибирское отделение Российской академии наук», 2022. – P. 102-103. – DOI 10.53954/9785604788967_102.
  4. Кошелев, К.Б. Особенности построения сетки для моделирования процесса обледенения треугольного крыла сложной формы / К.Б. Кошелев, А.В. Осипов, С.В. Стрижак // Труды Института системного программирования РАН. – 2022. – Т. 34, № 5. – С. 215-226. – DOI 10.15514/ISPRAS-2022-34(5)-15.
  5. Konstantin Koshelev, Andrey Osipov, Sergei Strijhak, Nikita Tryaskin. Mathematical modeling of icing process of the outer surface of the hull for a marine vessel. Journal of Hydrodynamics, 2023,
  6. K. Koshelev, A. Osipov. S. Strijhak. Using the iceFoam solver to simulate ice accretion process on a swept wing with GLC-305 airfoil. February 2023, AIP Conference Proceedings 2504(1):030028 , DOI: 10.1063/5.0132710
  7. Амелюшкин И.А. Математические модели, численные алгоритмы, результаты исследования особенностей обледенения летательных аппаратов // XXVI Всероссийский семинар с международным участием по струйным, отрывным и нестационарным течениям: материалы докладов. Санкт-Петербург, 27 июня – 1 июля 2022 года / Сост.: М.В. Чернышов, А.С.Капралова. – СПб.: Балт. Гос. Техн. Ун-т, 2022. С. 26–27.
  8. Amelyushkin I.A. Models of interaction of snow particles and supercooled droplets with a solid body in nonhomogeneous flow, DOI: 10.53954/9785604788974_11 // Abstracts from International conference on the methods of aerophysical research, August 8–14, 2022 Novosibirsk, Russia, Part II, P. 11–12.
  9. Амелюшкин И.А., Кудров М.А., Морозов А.О. Модели сальтации снега, динамики кристаллов и переохлажденных капель в газовых потоках // Всероссийская конференция молодых ученых-механиков YSM-2022. Тезисы докладов (4 − 14 сентября 2022 г., Сочи, «Буревестник» МГУ). – М.: Издательство Московского университета, 2022. – C. 37. – (Электронное издание сетевого распространения), ISBN 978-5-19-011787-5 (e-book).
  10. Амелюшкин И.А. Особенности динамики частиц снега, льда и переохлажденных капель в пограничном слое у нагретой поверхности и в цилиндрическом канале // Модели и методы аэродинамики. Материалы Двадцать второй международной школы-семинар. – М.: ЦАГИ, 2022.
  11. Амелюшкин И.А., Кудров М.А., Морозов А.О. Модели процессов, сопровождающих обледенение летательных аппаратов и развитие противообледеннительных систем // Материалы ХХXIII научно-технической конференции по аэродинамике в пос. им. Володарского. – М.: Изд-во ЦАГИ. – 2022. С. 18–19.
  12. Амелюшкин И.А., Кудров М.А., Морозов А.О. Деформация, разрушение и плавление льда при соударении с нагретой поверхностью и при аэродинамическом воздействии // Труды 65-й Всероссийской научной конференции МФТИ» – 6–7 апреля 2023. МФТИ.
  13. Амелюшкин И. А. Особенности обтекания тела потоком, содержащим переохлажденные капли. Вестник МГОУ. 2022. 6-15 с. DOI: 10.18384/2310-7251-2022-1-6-15.

List of conferences 2022-2023

  1. Международная конференция по Прикладной математике и механике в аэрокосмической отрасли (AMMAI’2022), 4-13 сентября 2022 г., г. Алушта. Стрижак С.В. Устный доклад.
  2. International conference on the methods of Aerophysical Research, August 8–14, 2022 Novosibirsk, Russia. Кошелев К.Б. Устный доклад.
  3. International conference on the methods of Aerophysical Research, August 8–14, 2022 Novosibirsk, Russia. Амелюшкин И.А. Устный доклад.
  4. 21-я Международная конференция «АВИАЦИЯ И КОСМОНАВТИКА», 23.11.2022 г. Москва. Стрижак С.В. Устный доклад.
  5. XXVI Всероссийский семинар с международным участием по струйным, отрывным и нестационарным течениям: материалы докладов. Санкт-Петербург, 27 июня – 1 июля 2022 года. Амелюшкин И.А. Устный доклад.
  6. Всероссийская конференция молодых ученых-механиков YSM-2022. Тезисы докладов (4 − 14 сентября 2022 г., Сочи, «Буревестник» МГУ). Амелюшкин И.А. Устный доклад.
  7. Модели и методы аэродинамики. Материалы Двадцать второй международной школы-семинар. – М.: ЦАГИ, 2022. Амелюшкин И.А. Устный доклад.
  8. ISP RAS OPEN 2022, Москва. Кошелев К.Б. Устный доклад.
  9. The 6th Symposium on Computational Marine Hydrodynamics. 第六届CMHL船舶与海洋工程计算水动力学研讨会 (The 6th CMHL Symposium 2023). Shanghai, China. January 14, 2023, Online Virtual Meeting. Стрижак С.В. Пленарный доклад.
  10. 65 Всероссийская научная конференция МФТИ» – 6–7 апреля 2023. МФТИ. Амелюшкин И.А., Кудров М.А. Устный доклад.