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<p>This study investigated the aerodynamic interference, performance, and noise characteristics of the XH-59A counter-rotating coaxial rotor. A structural dynamic model, validated through comparisons with established reference data, was employed to account for blade motion. Detailed analyses of the aerodynamic phenomena associated with specific design parameters were conducted under four distinct flight conditions. The results demonstrated that rotor torque increased with higher advance ratios, particularly at increased forward flight speeds or reduced rotor speeds. This increase was closely correlated with a reduction in the lift-to-drag ratio. Aerodynamic interferences, including root–vortex, hub–wake interactions, self-blade–vortex interactions (self-BVI), and blade-crossing effects, generated instantaneous blade loading fluctuations that directly influenced high-frequency aerodynamic noise. The simulation results indicated directional variations in noise levels across the hemispherical domain depending on the azimuthal position, which were attributed to localized interference mechanisms.</p>

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Coupled CFD–CSD Analysis of Aerodynamic and Aeroacoustics Behavior of a Lift-Offset Coaxial Rotor in Forward Flights

  • 期刊论文

  • 发表日期：

    2025年9月29日

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  • Jaewon Lee,
  • You Sang Lim,
  • Yong Su Jung

摘要

This study investigated the aerodynamic interference, performance, and noise characteristics of the XH-59A counter-rotating coaxial rotor. A structural dynamic model, validated through comparisons with established reference data, was employed to account for blade motion. Detailed analyses of the aerodynamic phenomena associated with specific design parameters were conducted under four distinct flight conditions. The results demonstrated that rotor torque increased with higher advance ratios, particularly at increased forward flight speeds or reduced rotor speeds. This increase was closely correlated with a reduction in the lift-to-drag ratio. Aerodynamic interferences, including root–vortex, hub–wake interactions, self-blade–vortex interactions (self-BVI), and blade-crossing effects, generated instantaneous blade loading fluctuations that directly influenced high-frequency aerodynamic noise. The simulation results indicated directional variations in noise levels across the hemispherical domain depending on the azimuthal position, which were attributed to localized interference mechanisms.