Journal of the Korean Society for Aeronautical & Space Sciences (한국항공우주학회지)

The Korean Society for Aeronautical and Space Sciences (한국항공우주학회)
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Aerodynamic Design of Helicopter Rotor Airfoil in Forward Flight Using Response Surface Method

반응표면법을 이용한 전진비행하는 헬리콥터 로터 에어포일의 공력설계

  • 선효성 (서울대학교 기계항공공학부 대학원) ;
  • 이수갑 (서울대학교 기계항공공학부)
  • Published : 2004.09.01
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Abstract

This paper describes an efficient and robust optimization method for helicopter rotor airfoil design in forward flight. Navier-Stokes analysis was employed to compute the dynamic response of an airfoil, which simulates the unsteady rotor flow-field in forward flight. The optimization system consists of two categories; Response Surface Method to construct the response surface model based on D-optimal 3-level factorial design, and Genetic Algorithm to obtain the optimum solution of a defined objective function including penalty terms of constraints. The influence of design variables and their interactions on the aerodynamic performance was examined through the optimization process.

이 논문은 최적설계 기법의 적용을 통하여 전진비행하는 조건에서 헬리콥터 로터를 구성하는 에어포일의 공력성능을 향상시키는 것에 목적을 가지고 있다. 전진비행하는 로터의 유동장을 모사하는 에어포일의 동적반응에 의한 공력성능은 Navier-Stokes 방정식을 이용하여 계산되어진다. 최적설계 기법은 수리통계적인 방법에 기초하는 반응표면법과 적절한 목적함수와 제약조건의 조합을 통하여 최적점을 구해내는 유전 알고리즘으로 구성되어진다. 유동해석 방법과 설계기법의 통합을 바탕으로 공력성능이 향상된 에어포일의 형상을 구할 수 있었으며 통계학적인 방법에 기초하여 설계연구에 사용되어진 형상변수들이 공력성능에 영향을 미치는 정도를 파악할 수 있었다.

Keywords

References

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