TY - GEN
T1 - UNSTEADY FLOW SIMULATION AROUND MAIN LANDING GEAR USING HIERARCHICAL CARTESIAN GRID METHOD WITH IMMERSED BOUNDARY METHOD
AU - Imamura, Taro
AU - Tamaki, Yoshiharu
N1 - Funding Information:
The LEG geometry was kindly provided by Aeronautical Technology Directorate of Japan Aerospace Exploration Agency. Author would like to express his gratitude for their contribution. This research was conducted using the Fujitsu PRIMERGY CX2550M5/CX2560M5(Oakbridge-CX) in the Information Technology Center, The University of Tokyo.
Publisher Copyright:
© 2021 32nd Congress of the International Council of the Aeronautical Sciences, ICAS 2021. All rights reserved.
PY - 2021
Y1 - 2021
N2 - Among the airframe noise from an aircraft, landing gear noise is one of the dominant noise sources during the approach phase. A hierarchical Cartesian-grid-based flow solver for unsteady flow simulation is used to investigate the noise generated from a realistic landing gear configuration. Flow simulations around multiple configurations by putting on/off the landing gear components are performed. The overall flow field around the complex geometry is investigated in detail based on the time-averaged flow field. Also, the far-field noise is estimated based on Curle's equation assuming that acoustic sources are compact. Relation between the landing gear components and the power spectral density distribution is investigated to understand the dominant noise source of the landing gear.
AB - Among the airframe noise from an aircraft, landing gear noise is one of the dominant noise sources during the approach phase. A hierarchical Cartesian-grid-based flow solver for unsteady flow simulation is used to investigate the noise generated from a realistic landing gear configuration. Flow simulations around multiple configurations by putting on/off the landing gear components are performed. The overall flow field around the complex geometry is investigated in detail based on the time-averaged flow field. Also, the far-field noise is estimated based on Curle's equation assuming that acoustic sources are compact. Relation between the landing gear components and the power spectral density distribution is investigated to understand the dominant noise source of the landing gear.
KW - Airframe noise
KW - Computational aeroacoustics
KW - Landing gear
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M3 - Conference contribution
AN - SCOPUS:85124492028
T3 - 32nd Congress of the International Council of the Aeronautical Sciences, ICAS 2021
BT - 32nd Congress of the International Council of the Aeronautical Sciences, ICAS 2021
PB - International Council of the Aeronautical Sciences
T2 - 32nd Congress of the International Council of the Aeronautical Sciences, ICAS 2021
Y2 - 6 September 2021 through 10 September 2021
ER -