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사정환(J.H. Sa),박수형(S.H. Park),김창주(C.-J. Kim),윤철용(C.Y. Yun),김승호(S.-H. Kim),김상호(S. Kim),유영훈(Y.H. Yu) 한국전산유체공학회 2009 한국전산유체공학회지 Vol.14 No.2
Numerical optimization of rotor blade airfoils is performed with a response surface method for helicopter rotor. For the baseline airfoils. OA 312, OA 309, and OA 407 airfoils are selected and optimized to improve aerodynamic performance. Aerodynamic coefficients required for the response surface method are obtained by using Navier-Stokes solver with k-w Shear Stress Transport turbulence model. An optimized airfoil has increased drag divergence Mach number. The present design optimization method can generate an optimized airfoil with multiple design constraints, whenever it is designed from different baseline airfoils at the same design condition.
사정환(J.H. Sa),박수형(S.H. Park),김창주(C.J. Kim),윤철용(C.Y. Yun),김승호(S.H. Kim),김상호(S.H. Kim),이재우(J.W. Lee) 한국전산유체공학회 2009 한국전산유체공학회 학술대회논문집 Vol.2009 No.4
Optimization with metamodel is one of numerical optimization methods. Response surface method is performed for making metamodel. The Hcks-Henne function is used for designing 2D shape of the airfoil and spring analogy is used to change the grid according to the change in shape of the airfoil. Aerodynamic coefficient required for response surface method are obtained by using Navier-Stokes solver with κ-ω shear stress transport turbulence model. For the baseline airfoils, OA 312, OA 309, and OA 407 airfoils select and optimize to improve aerodynamic performance.