FURTHER DEVELOPMENT OF THE COMPUTATIONAL ICE ACCRETION PREDICTION METHOD

Abstract eng:
The paper deals with the further development of the computational wing airfoil ice accretion prediction code ICE, which was currently modified. Mentioned version enables computational rime ice and glaze ice accretion prediction on single and multi-element airfoils in acceptable time of solution. Mathematical model has been modified for variable wall temperature along the airfoil surface. The code was also improved for the better approximation of transition boundary layer location. There are shown results ice accretion prediction of the wing airfoil with a slotted flap and various cases of predicted ice shapes in dependence of air temperature. Presented icing simulation is an aid to the certification process of small transport aircraft.

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