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AERODYNAMIC DESIGN OPTIMIZATION OF ROTOR BLADE OA AIRFOILS  

Sa, J.H. (건국대학교 대학원 항공우주정보시스템공학과)
Park, S.H. (건국대학교 대학원 항공우주정보시스템공학과)
Kim, C.J. (건국대학교 대학원 항공우주정보시스템공학과)
Yun, C.Y. (한국항공우주연구원)
Kim, S.H. (한국항공우주연구원)
Kim, S. (건국대학교 대학원 항공우주정보시스템공학과)
Yu, Y.H. (건국대학교 대학원 항공우주정보시스템공학과)
Publication Information
Journal of computational fluids engineering / v.14, no.2, 2009 , pp. 25-31 More about this Journal
Abstract
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-$\omega$ 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.
Keywords
CFD; Airfoil Flow; Design Optimization; Response Surface Method;
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