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초록
A noise prediction code for helicopter rotors was developed using a nonlinear vortex lattice method (NVLM) and the Ffowcs Williams-Hawkings acoustic analogy with impermeable boundary conditions. Aerodynamic loading was evaluated by coupling NVLM with a vortex particle method to compute loading and thickness noise. The code was validated using Caradonna-Tung and HART-II rotor data under hover and forward flight conditions, respectively. While pitch angle had minimal influence on thickness noise, overall noise levels increased with pitch. The predicted aerodynamic forces and acoustic pressures showed good agreement with measurements, demonstrating the capability of code for designing low-noise rotor blades.
키워드
헬리콥터 소음; 저소음 블레이드; 와류법; 음향상사법; Helicopter Noise; Low-noise Rotor Blade; Vortex Method; Acoustic Analogy
- 제목
- 헬리콥터 주로터 소음 저감 설계를 위한 와류법과 FW-H 음향상사법 기반의 공력 소음 예측 코드 개발
- 제목 (타언어)
- Development of Aerodynamic Noise Prediction Code based on Vortex Method and FW-H Acoustic Analogy for Designing Low-noise Rotor Blade of Helicopter
- 저자
- 김시진; 이사랑; 손상민; 김기로; 박남은; 명노신; 이학진
- 발행일
- 2025-04
- 저널명
- 한국소음진동공학회논문집
- 권
- 35
- 호
- 2
- 페이지
- 218 ~ 228