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권형일(H.I. Kwon),이슬기(S.G. Yi),최성임(S.I. Choi),김근배(K.B. Kim) 한국전산유체공학회 2012 한국전산유체공학회 학술대회논문집 Vol.2012 No.11
In this study, we present that multi-stage design framework for aerodynamic design optimization of rotary wing such as propeller and helicopter rotor blades. Strategy of the proposed framework is to enhance aerodynamic performance using both planform and sectional design optimization iteratively. In first stage of planform design, we used genetic algorithm and blade element momentum theory(BEMT) based on two dimensional aerodynamic database to find optimal planform variables in short time. After initial design, local flow conditions of blade sections are calculated. Next stage, sectional design optimization is conducted using two dimensional Navier-Stokes analysis and gradient based optimization algorithm. Mien optimal shapes are determined, planform design is performed again. Through the iterative design process, not only optimal flow condition but also optimal shape could be acquired. To validate the framework, design optimization for propeller which operated in electric vehicle system were performed As a results, about 8% of efficiency enhancement has acquired.