EPJ Web Conf.
Volume 213, 2019EFM18 – Experimental Fluid Mechanics 2018
|Number of page(s)||5|
|Published online||28 June 2019|
Some Peculiarities of Helicopter Main Rotor Aeroacoustic for Far-Field Observer
Kazan National Research Technical University n.a. A. N. Tupolev (KNRTUKAI), Kazan, Russia
2 University of Glasgow, Glasgow, UK
* Corresponding author: email@example.com
Published online: 28 June 2019
Mathematical models for helicopter rotor acoustics are usually based on the Ffowcs Williams–Hawkings (FW–H) equation. The level of rotor noise is determined by geometry (thickness noise) of a flying vehicle and distributed blade loading (loading noise). Initially, the FW-H equation was obtained from Euler’s equations and does not depend on the viscosity of flow. In the present work the UH-1H helicopter is considered as a test case for numerical CFD simulation and comparison to experimental data.
© The Authors, published by EDP Sciences, 2019
This is an open access article distributed under the terms of the Creative Commons Attribution License 4.0 (http://creativecommons.org/licenses/by/4.0), which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
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