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Investigation of a Virtual Blade Method for Aerodynamic and Acoustic Prediction of Helicopter Rotors

Investigation of a Virtual Blade Method for Aerodynamic and Acoustic Prediction of Helicopter Rotors A virtual blade method (VBM) combining the unsteady momentum source model with the computational fluid dynamics solver is applied in this work. The momentum source term is employed to replace the effect of the rotor blade on the air in the unsteady Reynolds-averaged Navier–Stokes equations, and the unsteady characteristics of the rotor flow field are accurately captured without body-fitted grids. The rotor aeroacoustic computation model is then combined with the Ffowcs Williams and Hawkings (FW–H) equation. Taking the Caradonna–Tung rotor, GIT rotor fuselage model, and AH-1/OLS rotor model as examples, the aeroacoustic computation effectiveness for blade tip vortex capturing in hover and rotor/fuselage aerodynamic interactions is validated by available experimental data. The results show that the VBM can accurately simulate the rotor wake, unsteady load, and aerodynamic noise at a low computational cost. Compared with the body-fitted grid method, the flow field computation time of the VBM is reduced by 3/4, and the amount of data for VBM/FW–H acoustic postprocessing is reduced by more than 90%. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png International Journal of Aeronautical and Space Sciences Springer Journals

Investigation of a Virtual Blade Method for Aerodynamic and Acoustic Prediction of Helicopter Rotors

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References (28)

Publisher
Springer Journals
Copyright
Copyright © The Author(s), under exclusive licence to The Korean Society for Aeronautical & Space Sciences 2022. Springer Nature or its licensor (e.g. a society or other partner) holds exclusive rights to this article under a publishing agreement with the author(s) or other rightsholder(s); author self-archiving of the accepted manuscript version of this article is solely governed by the terms of such publishing agreement and applicable law.
ISSN
2093-274X
eISSN
2093-2480
DOI
10.1007/s42405-022-00554-4
Publisher site
See Article on Publisher Site

Abstract

A virtual blade method (VBM) combining the unsteady momentum source model with the computational fluid dynamics solver is applied in this work. The momentum source term is employed to replace the effect of the rotor blade on the air in the unsteady Reynolds-averaged Navier–Stokes equations, and the unsteady characteristics of the rotor flow field are accurately captured without body-fitted grids. The rotor aeroacoustic computation model is then combined with the Ffowcs Williams and Hawkings (FW–H) equation. Taking the Caradonna–Tung rotor, GIT rotor fuselage model, and AH-1/OLS rotor model as examples, the aeroacoustic computation effectiveness for blade tip vortex capturing in hover and rotor/fuselage aerodynamic interactions is validated by available experimental data. The results show that the VBM can accurately simulate the rotor wake, unsteady load, and aerodynamic noise at a low computational cost. Compared with the body-fitted grid method, the flow field computation time of the VBM is reduced by 3/4, and the amount of data for VBM/FW–H acoustic postprocessing is reduced by more than 90%.

Journal

International Journal of Aeronautical and Space Sciences – Springer Journals

Published: Apr 1, 2023

Keywords: Virtual blade method; Vortex; Aerocoustic; CFD; Helicopter rotor

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