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로터-기체 상호작용 소음에 관한 수치 예측 연구NUMERICAL PREDICTION OF ROTOR-AIRFRAME INTERACTION NOISE

Other Titles
NUMERICAL PREDICTION OF ROTOR-AIRFRAME INTERACTION NOISE
Authors
김은민양진용이혁진강민제명노신이학진
Issue Date
Sep-2022
Publisher
한국전산유체공학회
Keywords
도심 항공 모빌리티(Urban Air Mobility); 전산유체역학(Computational Fluid Dynamics); 공력음향학(Aeroacoustics); 공력 소음(Aerodynamic Noise); 로터-기체 상호작용(Rotor-Airframe Interaction); 격자 볼츠만 법(Lattice Boltzmann Method)
Citation
한국전산유체공학회지, v.27, no.3, pp 79 - 88
Pages
10
Indexed
KCI
Journal Title
한국전산유체공학회지
Volume
27
Number
3
Start Page
79
End Page
88
URI
https://scholarworks.gnu.ac.kr/handle/sw.gnu/1952
DOI
10.6112/kscfe.2022.27.3.079
ISSN
1598-6071
Abstract
Strong-intensity tip vortex generated from the tip of the rotor blade causes strong aerodynamic interactions with the fuselage and structures. This interaction phenomenon directly affects the aerodynamic performance and noise characteristics of the rotor blades. In this study, the computational analysis of rotor-airframe configuration is performed to investigate the effects of rotor-airframe interaction on thrust, wake structure, flow field, and noise levels using the Lattice-Boltzmann Method (LBM). The isolated rotor operating in hovering conditions is used for the validation model. The thrust force and tonal noise associated with the 1st and 2nd Blade Passage Frequency (BPF) of the isolated rotor are compared against the measurements. The validation results showed good agreement with the experimental data. When a conical airframe is placed under the rotor blade, the thrust force tends to oscillate periodically. In addition, rotor wake development along the downstream direction is obstructed, and asymmetric wake structure can be observed, thus leading to a faster tip vortex breakdown and an increase in turbulence intensity. Finally, the overall sound pressure level (OASPL) of the rotor-airframe is higher than that of the isolated rotor at all microphone positions due to thrust fluctuation and a highly unsteady flow field caused by the strong interaction.
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Lee, Hak Jin
대학원 (기계항공우주공학부)
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