Dynamic Intake 장착 헬기 공기흡입구의 결빙 증식 전산 예측

다국어 초록 (Multilingual Abstract)

A significant change in engine performance and propulsive characteristics can occur by ice accretion on the surface of helicopter engine intake. In order to analyze those icing effects, a physics-based icing simulation using the CFD methods can be used prior to the exact but very expensive icing wind tunnel or in-flight tests. In this study, the impact of ice accretions on the dynamic intake type helicopter is examined in detail. An analysis is carried out for a forward flight after neglecting the effect of down-wash in the rotor for the sake of simplicity. As a result, the location of major iced areas such as the engine intake and the amount of ice accretion are identified.