Mathematical modeling of ice body formation on the wing airfoil surface

Abstract

The main models and methods for investigating the process of icing of aerodynamic surfaces, the meteorological parameters of the icing, the cloud types, the types of the ice coating, and the systems of protection against icing are analyzed. A software is developed which makes it possible to model the icing on the leading edge of the wing airfoil. The motion of the carrying medium is described on the basis of the Navier-Stokes equations for a compressible gas, together with the Spalart-Allmaras turbulence model. A delayed model is applied to describe the motion of supercooled water droplets. The numerical modeling of the ice accretion process is based on the control volume method which consists in the solution of the differential equations of the mass, momentum, and energy conservation for any surface element using a model which allows for the surface moisture behavior on macro-and microlevels. With reference to the example of the NACA 0012 airfoil in two-dimensional viscous compressible twophase flow the main shapes of the ice bodies are reproduced with account for the ice accretion regime, the form of the moisture existence on the airfoil, the surface heating, and the effect of the variation in the airfoil geometry on the external flow and the aerodynamic characteristics.

An experimental study of freezing of supercooled water droplet on solid surface

“…To ensure safe aviation, a system of anti-icing measures is developed for each particular aircraft and it is certified with respect to flight under icing conditions. In solving these tasks, an important research tool, in addition to test flights and on-ground experiments in cooled high-speed wind tunnels (both having a number of disadvantages and restrictions), is offered by numerical simulations, which have become very effective due to rapid development of computational technologies.In most cases, well-known mathematical models describing the process of ice growth [1][2][3][4][5] are based on the Messinger hypothesis [6], according to which the spreading of liquid over the surface is described without taking into account its physical state, collision of supercooled water droplets with the ice-water interface, and their subsequent spraying. Results of mathematical modeling based on existing methods agree well only with the experimental data for rime ice (in which the incident supercooled droplets freeze almost immediately upon collision) and agree satisfactorily for some regimes with glaze ice formation.…”

“…In most cases, well-known mathematical models describing the process of ice growth [1][2][3][4][5] are based on the Messinger hypothesis [6], according to which the spreading of liquid over the surface is described without taking into account its physical state, collision of supercooled water droplets with the ice-water interface, and their subsequent spraying. Results of mathematical modeling based on existing methods agree well only with the experimental data for rime ice (in which the incident supercooled droplets freeze almost immediately upon collision) and agree satisfactorily for some regimes with glaze ice formation.…”

Investigation of Aircraft Icing Regimes

“…Для численного моделирования процессов образования льда на аэродинамических поверхностях разработано программно-методическое обеспечение, названное авторами FULLICE 2D [5,6,7,8,9,10,11,12,13,14]. Где для описания набегающего двухфазного потока применена модель взаимопроникающих сред.…”

Comparison Criteria for Ice Accretion On An Aerofoil Surface

“…The computational techniques are especially more cost effective as they reduce the time it takes to test a wide range of icing scenarios and operational conditions, and develop and estimate the efficiency of ice prevention system. Although numerical methods propose a spectrum of benefits, they still require experimental data for validation purposes [9,19].…”

“…Ice shape is then predicted by coupling the droplet collection efficiency data with the thermodynamic model. The predicted ice shape can then be used to study the aerodynamic penalties of iced object and assess heating requirement by either a de-icing system to remove this ice or an anti-icing system to prevent this ice from accreting on the object [9,[19][20][21][22].…”