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Numerical Investigation Into the Unsteady Aerodynamics of a Ducted Helicopter Tail Rotor Under Side-Wind Conditions

[+] Author Affiliations
Marc Kainz, Florian Danner, Hans-Peter Kau

Technische Universität München, Garching, Germany

Frédéric Le Chuiton

Eurocopter Deutschland GmbH, Munich, Germany

Paper No. GT2010-22142, pp. 87-98; 12 pages
doi:10.1115/GT2010-22142
From:
  • ASME Turbo Expo 2010: Power for Land, Sea, and Air
  • Volume 7: Turbomachinery, Parts A, B, and C
  • Glasgow, UK, June 14–18, 2010
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4402-1 | eISBN: 978-0-7918-3872-3
  • Copyright © 2010 by ASME

abstract

A numerical study into the unsteady aerodynamics of a ducted helicopter tail rotor is presented. Computations were carried out for ideal hover flight conditions and under the influence of side-wind. The results are validated against existing experimental performance data. The investigated numerical model incorporates the full annulus turbomachinery components as well as the entire tail boom including non-axis-symmetric casing contour, drive shaft fairing, fin and stabilisers. The rotor is characterised by an uneven azimuth-wise blade distribution, while the stator vanes complemented by the drive shaft fairing are distributed evenly. For the computational fluid dynamics analysis the fully turbulent three-dimensional Favre-averaged Navier-Stokes equations were solved on a Chimera grid system with 24.7 million cells. Besides thrust and shaft power characteristics, the varying blade loading due to the azimuth-wise position and the side-wind effect is analysed.

Copyright © 2010 by ASME
Topics: Aerodynamics , Rotors , Wind

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