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Methods to predict rotor trailing-edge noise using computational fluid dynamicsa).

Jordon Won1, Nikos Trembois1, Seongkyu Lee1

  • 1Mechanical and Aerospace Engineering, University of California, Davis, California 95616, USA.

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|August 29, 2025
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Summary
This summary is machine-generated.

Predicting rotor turbulent boundary layer noise is crucial. Deriving boundary-layer parameters from sectional forces offers the most reliable computational fluid dynamics (CFD) predictions, validated by experimental data.

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Area of Science:

  • Aerospace Engineering
  • Acoustics
  • Computational Fluid Dynamics

Background:

  • Rotorcraft noise, particularly turbulent boundary layer trailing-edge noise, is a significant concern in aerospace applications.
  • Accurate prediction of this noise requires reliable inputs for empirical models, such as boundary-layer parameters.
  • Computational fluid dynamics (CFD) is a powerful tool for simulating aerodynamic phenomena, but its direct application for noise prediction requires careful parameter extraction.

Purpose of the Study:

  • To investigate and compare three distinct methods for obtaining boundary-layer parameters essential for predicting rotor turbulent boundary layer trailing-edge noise.
  • To evaluate the efficacy of computational fluid dynamics (CFD) coupled with Amiet's trailing-edge noise model for noise prediction.
  • To identify the most reliable and efficient approach for deriving boundary-layer parameters from CFD data.

Main Methods:

  • Three approaches were developed to extract boundary-layer parameters: direct extraction from 3D CFD solutions, derivation from sectional forces, and determination from pressure coefficient distributions.
  • These parameters were used as inputs for an empirical wall pressure spectrum model.
  • Amiet's trailing-edge noise model was employed in conjunction with CFD simulations.

Main Results:

  • The method deriving boundary-layer parameters from sectional normal and chordwise forces proved to be the most reliable and efficient.
  • Predictions using this method showed good agreement with experimental data across various operating conditions for two rotor configurations.
  • Trailing-edge noise showed low sensitivity to changes in effective angle of attack but significant sensitivity to airfoil selection, blade geometry, and rotation speed.

Conclusions:

  • Deriving boundary-layer parameters from sectional forces is a robust method for predicting rotor trailing-edge noise using CFD.
  • The study highlights the critical influence of rotor design parameters (airfoil, blade geometry, speed) on noise levels.
  • CFD coupled with empirical models provides a viable framework for understanding and mitigating rotor noise.