Aerodynamics and Aeroacoustics of Helicopter Main-Rotor/Tail-Rotor Interaction
Ahmed, S.R. and Yin, J. (1999) Aerodynamics and Aeroacoustics of Helicopter Main-Rotor/Tail-Rotor Interaction. 5th AIAA/CEAS Aeroacoustics Conference, Bellevue (usa), 10.-12.05.1999.
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Preliminary results from an ongoing effort to model the interaction aerodynamics and aeroacoustics of main- and tail rotor of a helicopter in subsonic flow are presented. The configurations studied are a) a two-blade main- and tail rotor in hover, and b) a four-blade main- and a two-blade tail rotor in climb flight. The numerical approach consists of computing the unsteady pressure on the main- and tail rotor blade surface with a 3-D unsteady free wake panel method and using this as input to a Ffowcs Williams Hawkings equation based aeroacoustic code to evaluate the noise characteristics. Parameters varied for the hover configuration are the lateral spacing between the main- and tail rotor axis and the sense of tail rotor rotation. Main rotor interaction effects a significant change in the noise directivity pattern and noise level of the tail rotor. Tail rotor contribution to the total noise dominates during the climb flight.
|Document Type:||Conference or Workshop Item (Paper)|
|Title:||Aerodynamics and Aeroacoustics of Helicopter Main-Rotor/Tail-Rotor Interaction|
|Keywords:||Main-Rotor/Tail-Rotor Interaction, Aerodynamics, Aeroacoustics|
|Event Title:||5th AIAA/CEAS Aeroacoustics Conference, Bellevue (usa), 10.-12.05.1999|
|HGF - Research field:||Aeronautics, Space and Transport|
|HGF - Program:||Aeronautics|
|HGF - Program Themes:||L - no assignement|
|DLR - Research area:||Aeronautics|
|DLR - Program:||L DT - Drehflüglertechnologien|
|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 20:02|
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