전산유체역학을 활용한 착빙 익형 풍동시험의 공력 성능 보정 기법

초록

This paper proposes an correction method for predicting the aerodynamics of iced airfoil in icing wind tunnel test. Because of endplate effect, measuring the precise aerodynamics of a two-dimensional iced airfoil in wind tunnel is difficult. The proposed method synthesizes the aerodynamic characteristics of a iced wing with those of a clean wing in wind tunnel, to estimate the aerodynamics of iced airfoil. The method is validated by comparing its predictions with recent wind tunnel experiments. The results confirm that the simulated aerodynamics of the clean wing, including endplate effects, agree well with the experi- mental results before icing. And the synthesized aerodynamic changes due to icing show good agreement with the experimental results for the iced wing.

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