Volume 37 Issue 3
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DING C W, ZHOU G C, CHEN B, et al. Experimental study on aerodynamic noise characteristics of helicopter ducted tail rotor[J]. Journal of Experiments in Fluid Mechanics, 2023, 37(3): 107-112. DOI: 10.11729/syltlx20210186
Citation: DING C W, ZHOU G C, CHEN B, et al. Experimental study on aerodynamic noise characteristics of helicopter ducted tail rotor[J]. Journal of Experiments in Fluid Mechanics, 2023, 37(3): 107-112. DOI: 10.11729/syltlx20210186
shu

Experimental study on aerodynamic noise characteristics of helicopter ducted tail rotor

  • 1.

    AVIC Aerodynamics Research Institute, Harbin　150001, China

  • 2.

    Heilongjiang Provincial Laboratory of Aerodynamic Noise and Control , Harbin　150001, China

  • 3.

    Aviation Key Laboratory of Aerodynamics for Low Speed and High Reynolds Number, Harbin　150001, China

  • 4.

    China Helicopter Research and Development Institute, Jingdezhen　333000, China

More Information
  • Received Date: December 14, 2021
  • Revised Date: January 16, 2022
  • Accepted Date: January 28, 2022
    Graphical Abstract
    • Abstract
  • Using the FL–52 aero-acoustic wind tunnel test system of the Aerodynamics Research Institute, the experimental study on the ducted tail rotor noise characteristics is carried out. The influence of the jet shear layer on the test data is corrected, and the noise spectrum and far-field directivity of the culvert tail rotor in hover and forward flight are obtained. The variation laws of the noise with the Mach number of the tail rotor tip are analyzed, and the results show that the aerodynamic noise of the ducted tail rotor conforms to the load noise characteristics. The effects of the blade distribution along the hub on the spectral characteristics of the aerodynamic noise are compared. The shielding noise reduction effect of the duct on the noise propagation under typical working conditions is obtained in hover, the noise in the rotating plane is 2 dB lower than that in other positions in forward flight, the noise reduction in the rotating plane is 5 – 8 dB.
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    • References (15)
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