The ice accretion on wings and horizontal stabilizers may cause aerodynamic performance degradation, weight increase, flight control difficulties and, in critical cases, may lead to operational safety margins reduction. When aicraft flies through supercooled water droplets clouds, which are in meta-stable equilibrium, ice will form in all surfaces that are subjected to impingement and not protected. Usually, antice protection systems are designed, developed and certified with support of a numerical tool. The present work will develop and implement a mathematical model for prediction of heat and mass transfer in two-phase flow around airfoils equiped with thermal antice system operating in steady state. Under icing conditions, it is necessary to heat and control the temperature of the airfoil surface at leading edge region to prevent ice formation. The heating system balances the cooling effects caused by coupled convection heat and mass transfer imposed by the air flow loaded with supercooled water droplets and the runback water flow around airfoil. The present work will implement new models to: 1)estimate airfoil surface wetness factor by adopting a liquid water film flow model as well as a rivulet formation and flow model ; 2) evaluate laminar and turbulent boundary layer with pressure gradient and laminar-turbulent transition over non-isothermal and permeable airfoil surface by implementing integral and finite difference methods; 3) predict the onset position and lenght of laminar-turbulent transition region by using classic empirical correlations, linear stability analysis and more recent methods.
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