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- W784863721 abstract "정지비행시의 헬리콥터 로터 모형의 블레이드의 피치각 변화가 소음방사에 미치는 영향을 수치해석을 통해 파악하였다. 공력 자료는 비정상 패널법과 경험후류 방법을 이용하여 구하였으며, <TEX>$0^{circ}$</TEX>에서 <TEX>$9^{circ}$</TEX>까지 등간격으로 <TEX>$1.5^{circ}$</TEX> 씩 피치각을 증가시키면서 블레이드 표면상의 공력 하중 분포를 얻어내었다. 수치해석을 통해 얻어낸 두께 소음은 피치각에 무관한 결과를 보였으나, 하중소음은 피치각이 <TEX>$1.5^{circ}$</TEX> 씩 증가할 때 마다 대략 3~4dBA정도로 소음의 세기가 증가하는 경향을 보였으며, 이정도의 증가분은 소음이 더 커졌음을 감지할 수 있는 충분한 크기라 할 수 있다. 또한 하중소음의 방향성 결과로부터 블레이드의 윗면 보다는 아랫면에서의 소음의 세기가 더 크게 나옴을 알 수 있었다. Noises from the helicopter rotor model are calculated numerically at various pitch angles. The aerodynamic data are calculated by using prescribed wake model and unsteady panel method. The distribution of aerodynamic loads on the blade surface are obtained from <TEX>$0^{circ}$</TEX> to <TEX>$9^{circ}$</TEX> pitch angles with equiangular increments of <TEX>$1.5^{circ}$</TEX>. Although thickness noise is not related to the change of pitch angles, loading noise level increases about 3~4dBA every <TEX>$1.5^{circ}$</TEX> increment of pitch angle. The additive noise level shows sufficient value to perceive the loudness. From the result of directivity pattern the sound level at the lower region of the blade disc plane is higher than that of the upper region." @default.
- W784863721 created "2016-06-24" @default.
- W784863721 date "2007-10-31" @default.
- W784863721 modified "2023-09-26" @default.
- W784863721 title "Thickness and Loading Noise from Helicopter Rotor at various Pitch Angles" @default.
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- W784863721 doi "https://doi.org/10.5139/jksas.2007.35.10.868" @default.
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