Heat and mass transfer in the case of an anti-icing system modelisation

Morency, François; Tezok, F.; Paraschivoiu, Ion

doi:10.2514/6.1999-623

Cited by 11 publications

(5 citation statements)

References 5 publications

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“…All these three codes used the potential flow panel method to calculate the flowfield. Morency et al 11 applied the integral boundary layer method and the finite difference method for the analysis of the heat transfer coefficient for anti-icing case in CANICE and found that the heat transfer coefficients from finite difference method were closer to the experimental ones. Habashi 7 used a three-dimensional (3D) computation fluid dynamic (CFD) conjugate heat transfer method for the anti/de-icing thermal analysis in FENSAP-ICE to couple the thermal conduction and the convective heat transfer.…”

Section: Introductionmentioning

confidence: 97%

Numerical simulation of an airfoil electrothermal anti-icing system

Lin

et al. 2012

Proceedings of the Institution of Mechanical Engineers, Part G:

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The mathematical models and a numerical code for numerical simulation of a thermal anti-icing system are presented in this article. Mass conservation is applied to the runback water flow. An energy balance is imposed on the airfoil skin including the water flow. The heat transfer coefficient distributions are obtained using the boundary layer integral method. The external flowfield and the local water collection efficiency data are predicted using an Eulerian method, based on a computation fluid dynamic code and its user-defined functions. Given the input of the electrical power density distribution, the numerical code is able to calculate airfoil equilibrium surface temperature, mass flux of runback water, runback ice mass flux, and range if happens. A user interface is developed to integrate the computation fluid dynamic code to achieve a method for the analysis of a thermal anti-icing system. All the numerical results are compared with both experimental data and other numerical results presented in the literature.

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Section: Introductionmentioning

confidence: 97%

Numerical simulation of an airfoil electrothermal anti-icing system

Lin

et al. 2012

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…(The values defining the correlation have been withheld for commercial reasons.) Simulation codes for ice accretion in both two-dimensional (13)(14)(15)(16)(17)(18)(19) and three-dimensional (26) versions (CANICE) have been developed at the Ecole Polytecnique, Montreal. The development of CANICE has been geared towards the specific needs of Bombardier.…”

Section: Heat Transfer Correlation For Piccolo Systems Basedmentioning

confidence: 99%

“…The heat flux q from this region is then evaluated with the help of the internal hot-air temperature T I and the local wall temperature T w A limitation of this method is that the internal heat flux q or the convection coefficient h anti and temperature T i are based on empirical relations (6) for a hot-air jet impinging on a flat plate. This has been a commonly accepted practice in studies related to anti-icing system modelling (13)(14)(15)(16)(17)(18)(19)(20)(21)(22)(23)(24)(25) . It must be pointed out that this local distribution of internal heat flux q i or the convection coefficient h anti is based purely on the local distribution on a flat plate and, therefore, does not account for the curvature of the internal wall region of an aerofoil leading-edge or the wing slat.…”

Section: Simulation Of Ice Accretionmentioning

confidence: 99%

Key aerodynamic technologies for aircraft engine nacelles

et al. 2006

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“…Few works applied the momentum and thermal boundary layer integral models to anti-ice simulation satisfactorily. Morency et al [1999b] developed the numerical code CANICE A that evaluates the heat transfer coefficient considering laminar flow over isothermal surface [Smith and Spalding, 1958], turbulent flow over smooth and non-isothermal surface [Ambrok, 1957] and abrupt laminar-turbulent transition. Same authors developed other version of the code, CANICE B, and use the experimental data of heat transfer coefficient .…”

Section: Introductionmentioning

confidence: 99%

Integral Analyses of the Convective Heat Transfer Around Ice Protected Airfoils With Non-Isothermal Surfaces

Silva

Silvares

Zerbini

2008

International Symposium on Advances in Computational Heat Transfer

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The heated airfoil operating under icing conditions has some important characteristics that differentiates the problem from the case of adiabatic airfoil subjected to ice growth. In presence of thermal ice protection, the hypothesis of flow over isothermal surfaces, which is assumed by most classic icing codes, may not represent the operation satisfactorily. The present paper implemented successfully two modeling strategies that considers streamwise surface temperature variations in thermal boundary-layer evaluation by integral procedure: 1) solution of the approximated enthalpy thickness integral equation assuming flow over a non-isothermal surface; 2) application of superposition principle to thermal boundary-layer solutions to represent the effects of flow over a surface with non-uniform temperature distribution. The numerical results were compared with isothermal model results as well as the experimental results of flat plate in a wind tunnel and two NACA aifoils, the 0012 and the 65 2-0016, operating in icing tunnel under clear air and icing conditions. The streamwise surface temperature gradient, water evaporation rate variation and the presence of laminar-turbulent transition, when occurring within the protected area, are effects that are represented adequately by the mathematical models.

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Heat and mass transfer in the case of an anti-icing system modelisation

Cited by 11 publications

References 5 publications

Numerical simulation of an airfoil electrothermal anti-icing system

Numerical simulation of an airfoil electrothermal anti-icing system

Key aerodynamic technologies for aircraft engine nacelles

Integral Analyses of the Convective Heat Transfer Around Ice Protected Airfoils With Non-Isothermal Surfaces

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