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Implementation of a Method to Determine Aerodynamic Propeller-Wing Interaction Read chapter Read first chapter

2020 | OriginalPaper | Chapter

Progress in Helicopter Noise Prediction

Author : Manuel Keßler

Published in: New Results in Numerical and Experimental Fluid Mechanics XII

Publisher: Springer International Publishing

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Abstract

Noise emissions remain a challenge for the development of helicopters, even though recent models have introduced substantial technological improvements. In order to proceed further in efforts to lower sound levels, numerical simulations can help and support physical insight as well as predict the effectiveness of specific mitigation measures. Advanced simulation frameworks have been pushed recently to provide results of sufficient quality and accuracy to base development decisions upon, notwithstanding the extremely challenging flow physics around a complex moving geometry, coupled to structure dynamics at the blade and generating acoustics by a multitude of different phenomena.
The applied rotorcraft prediction tool chain is now capable of separating various noise generation mechanisms, reproducing characteristic sound emission distinctions of diverse flight tests. Often the simulation is within the experimental variance of individual flights, although in other cases larger discrepancies remain, depending on the dominating acoustic process. However, even then the computation can give insight and help to further diminish noise emissions at an early stage of the development process, instead of expensive last-minute retrofits.

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previous chapter Emulation of Sound Pressure Level Spectra Based on Numerical Data
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Metadata
Title
Progress in Helicopter Noise Prediction
Author
Manuel Keßler
Copyright Year
2020
Book
New Results in Numerical and Experimental Fluid Mechanics XII

Print ISBN: 978-3-030-25252-6

Electronic ISBN: 978-3-030-25253-3

Copyright Year: 2020

DOI
https://doi.org/10.1007/978-3-030-25253-3_71

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