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

The Korean Society for Aeronautical and Space Sciences (한국항공우주학회)
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Aerodynamic Noise Analysis Using the Permeable Surface for UH-1H Rotor Blade in Hovering Flight Condition

UH-1H 로터 블레이드의 제자리 비행 시 투과면을 이용한 원방 소음 해석

  • Kim, Ki Ro (Department of Aerospace Information Engineering, Konkuk University) ;
  • Park, Min Jun (Department of Aerospace Engineering, Korea Advanced Institute of Science and Technology) ;
  • Park, Soo Hyung (Rotary-wing Aircraft Research & Development Division, Korea Aerospace Industries) ;
  • Lee, Duck Joo (Department of Aerospace Engineering, Korea Advanced Institute of Science and Technology) ;
  • Park, Nam Eun (Rotary-wing Aircraft Research & Development Division, Korea Aerospace Industries) ;
  • Im, Dong Kyun (Rotary-wing Aircraft Research & Development Division, Korea Aerospace Industries)
  • Received : 2017.11.29
  • Accepted : 2018.03.19
  • Published : 2018.05.01
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Abstract

The aerodynamic far-field noise was computed by an acoustic analogy code using the permeable surface for the UH-1H rotor blade in hover. The permeable surface surrounding the blade was constructed to include the thickness noise, the loading noise, and the flow noise generated from the shock waves and the tip vortices. The computation was performed with compressible three-dimensional Euler's equations and Navier-Stokes equations. The high speed impulsive noise was predicted and validated according to the permeable surface locations. It is confirmed that the noise source caused by shock waves generated on the blade surface is a dominant factor in the far-field noise prediction.

본 연구에서는 투과면을 이용하는 음향상사법으로 제자리 비행하는 UH-1H 로터 블레이드 주위의 원방 소음을 예측하였다. 두께 소음과 하중 소음, 그리고 충격파 및 끝단 후류 등에 의해 발생하는 유동 소음을 예측하기 위해 블레이드 표면을 포함하는 투과면을 구성하였다. 3차원 압축성 Euler 방정식 및 Navier-Stokes 방정식을 적용하여 공력 해석을 수행하고 비교하였다. 투과면의 위치에 따라 High Speed Impulsive 소음을 예측 및 검증하였다. 블레이드 끝단에서 발생하는 충격파에 의한 소음원이 지배적인 요소임을 확인하였으며, 충격파를 온전히 포함하도록 투과면을 구성하는 것이 중요함을 보였다.

Keywords

References

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