Helicopter main-rotor/tail-rotor interaction
Yin, J. and Ahmed, S.R. (2000) Helicopter main-rotor/tail-rotor interaction. Journal of the American Helicopter Society, Vol. 45 (No. 4), pp. 293-302.
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Preliminary results from a study to model the interaction aerodynamics and aeroacoustics of the main and tail rotor of a helicopter in subsonic flow are presented. The configurations studied are: 1) two bladed main and tail rotors in hover, and 2) a four-bladed main rotor and two-bladed tail rotor in climbing flight. The unsteady pressure on the main and tail rotor surfaces is computed with an unsteady 3-D panel method with full-span free wake simulation of the simultaneously rotating rotor. The computed pressures serve as input to a Ffowcs Williams Hawkings-equation based acoustic code to evaluate the noise characteristics. For the hover configuration, the parameters varied were the distance between the rotor axes and the sense of rotation of the tail rotor. Presence of the main rotor has a significant effect on the noise directivity and noise level of the tail rotor. Noise contribution of the tail rotor dominates during the climb.
|Title:||Helicopter main-rotor/tail-rotor interaction|
|Journal or Publication Title:||Journal of the American Helicopter Society|
|In ISI Web of Science:||Yes|
|Page Range:||pp. 293-302|
|Keywords:||rotor interaction, rotor aeroacoustics, free wake, 3-D panel method, blade vortex interaction|
|HGF - Research field:||Aeronautics, Space and Transport|
|HGF - Program:||Aeronautics|
|HGF - Program Themes:||L RR - Rotorcraft Research|
|DLR - Research area:||Aeronautics|
|DLR - Program:||L RR - Rotorcraft Research|
|DLR - Research theme (Project):||L - The Quiet and Comfortable Rotorcraft|
|Location:||Köln-Porz , Braunschweig , Göttingen|
|Institutes and Institutions:||Institute of Aerodynamics and Flow Technology > Institut für Entwurfsaerodynamik|
|Deposited By:||elib DLR-Beauftragter|
|Deposited On:||16 Sep 2005|
|Last Modified:||14 Jan 2010 20:14|
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