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

The Korean Society for Aeronautical and Space Sciences (한국항공우주학회)
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Unsteady Aerodynamic Analysis for Helicopter Rotor in Hovering and Forward Flight Using Overlapped Grid

중첩 격자를 이용한 제자리 및 전진 비행하는 헬리콥터 로터의 비정상 공력해석

  • 임동균 (한국과학기술원 항공우주공학과 대학원) ;
  • 위성용 (한국과학기술원 항공우주공학과 대학원) ;
  • 김유진 (한국과학기술원 항공우주공학과 대학원) ;
  • 권장혁 (한국과학기술원 항공우주공학과) ;
  • 이덕주 (한국과학기술원 항공우주공학과) ;
  • 박수형 (건국대학교 항공우주정보시스템공학과) ;
  • 정기훈 (한국항공우주연구원) ;
  • 김승범 (한국항공우주연구원)
  • Published : 2009.03.01
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Abstract

In this paper, the helicopter aerodynamics is simulated in hovering and forward flight. Also, an overlapped grid technique is applied in this simulation to consider the blade motion and moving effects. The Caradonna & Tung's rotor blade was selected to analyze the unsteady aerodynamics in hovering and non-lift forward flight. Also, the AH-1G rotor blade was selected in forward flight. In forward flight case, the numerical trim was applied to determine the cyclic pitching angles using Newton-Raphson method, and the numerical results were in good agreement with experimental data, especially, the BVI effects were well simulated in advancing side in comparison other numerical results. The governing equation is a three dimensional unsteady Euler equation, and the Riemann invariants condition is used for inflow and outflow at the boundary.

본 연구에서는 헬리콥터 로터 블레이드의 움직임을 모사하기 위해 중첩 격자 기법을 적용하여 헬리콥터 로터의 전진 및 제자리 비행을 모사하였다. 제자리 및 무양력 전진 비행은 Caradonna & Tung의 로터 블레이드를 적용하였으며 전진 비행은 AH-1G 로터 블레이드를 적용하여 수치해석 하였다. 전진 비행 시 cyclic pitch각에 대해서 Newton-Raphson 수렴 방법으로 수치 트림을 수행하였으며 수치 트림에 의한 결과를 실험 및 다른 수치해석 결과와 비교하였을 때 실험값과 유사한 결과를 얻었다. 또한 수치 트림에 의한 결과는 로터 전진면에서 나타나는 BVI 현상을 잘 모사하였다. 지배 방정식은 3차원 비정상 오일러 방정식을 사용하였으며 원방 경계 조건으로 리만 불변치 경계조건을 적용하였다.

Keywords

References

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