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: firstname.lastname@example.org
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.
Current usage metrics show cumulative count of Article Views (full-text article views including HTML views, PDF and ePub downloads, according to the available data) and Abstracts Views on Vision4Press platform.
Data correspond to usage on the plateform after 2015. The current usage metrics is available 48-96 hours after online publication and is updated daily on week days.
Initial download of the metrics may take a while.