Prediction of helicopter rotor noise in hover
1 Kazan National Research Technical University n.a. A. N. Tupolev (KNRTU-KAI), Kazan, Russia
2 University of Liverpool, Liverpool, UK
1a Prof., department of aero-hydrodynamics, firstname.lastname@example.org
2 Prof., department of aero-hydrodynamics, email@example.com
3 PhD student, firstname.lastname@example.org
4 PhD student, email@example.com
5 Prof., department of Engineering, G.Barakos@liverpool.ac.uk
Published online: 6 May 2015
Two mathematical models are used in this work to estimate the acoustics of a hovering main rotor. The first model is based on the Ffowcs Williams-Howkings equations using the formulation of Farassat. An analytical approach is followed for this model, to determine the thickness and load noise contributions of the rotor blade in hover. The second approach allows using URANS and RANS CFD solutions and based on numerical solution of the Ffowcs Williams-Howkings equations. The employed test cases correspond to a model rotor available at the KNRTUKAI aerodynamics laboratory. The laboratory is equipped with a system of acoustic measurements, and comparisons between predictions and measurements are to be attempted as part of this work.
© Owned by the authors, published by EDP Sciences, 2015
This is an Open Access article distributed under the terms of the Creative Commons Attribution License 4.0, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.