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공력 및 소음 성능 향상을 위한 헬리콥터 블레이드 탭과 익단 형상 최적설계
홍윤표(Y.P. Hong),한동연(D.Y. Han),임동균(D.K. Im),이관중(K.J. Yee) 한국전산유체공학회 2018 한국전산유체공학회지 Vol.23 No.1
Design optimization of helicopter blade planform for better aerodynamic and aeroacoustic performances has been conducted in this study. Instead of redesigning the entire blade shape, the tip shape and the tab angle are carefully optimized for ease of manufacturability. To consider various conditions under which the helicopter actually operates, the aerodynamic analysis is performed by time-efficient hybrid CFD method. The efficient global optimization(EGO) algorithm based on expected improvement(EI) is used as optimization method. The blade planform is parameterized with 5 tip shape variables and 1 tab angle variable. Sensitivity analysis is also performed to check the effect of individual design variables on blade performance. As a result, thrust coefficient of the optimal blade is improved by 4.4% while the induced power for level flight is maintained with the improved noise performance.