CAA modeling of helicopter main rotor in hover
1 Kazan National Research Technical University n.a. A. N. Tupolev (KNRTU-KAI), Kazan, Russia
2 University of Glasgow, Glasgow, UK
a Prof., department of aero-hydrodynamics, email@example.com
b Prof., department of aero-hydrodynamics, firstname.lastname@example.org
c PhD student, email@example.com
d Teacher, department of aero-hydrodynamics, firstname.lastname@example.org
e Prof., School of Engineering, George.Barakos@glasgow.ac.uk
Published online: 12 May 2017
In this work rotor aeroacoustics in hover is considered. Farfield observers are used and the nearfield flow parameters are obtained using the in house HMB and commercial Fluent CFD codes (identical hexa-grids are used for both solvers). Farfield noise at a remote observer position is calculated at post processing stage using FW–H solver implemented in Fluent and HMB. The main rotor of the UH-1H helicopter is considered as a test case for comparison to experimental data. The sound pressure level is estimated for different rotor blade collectives and observation angles.
© The Authors, published by EDP Sciences, 2017
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