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Forced Diffusion of Trailing Vorticity from a Hovering RotorA small turbulence generating device was Attached near the tip of a hovering rotor blade In order to alter the structure of the trailing vortex. Stereo particle image velocimetry (PIV) images were used to quantify the wake behind the rotor blade during the first revolution. An analysis of the 3D-velocity field includes a method for accounting for vortex wander. The results show that a major change in the size and intensity of the trailing vortex can be achieved.
Document ID
20010119438
Acquisition Source
Ames Research Center
Document Type
Conference Paper
Authors
McAlister, Kenneth W. (NASA Ames Research Center Moffett Field, CA United States)
Tung, Chee (NASA Ames Research Center Moffett Field, CA United States)
Heineck, James T. (NASA Ames Research Center Moffett Field, CA United States)
Aiken, Edwin W.
Date Acquired
August 20, 2013
Publication Date
January 1, 2001
Subject Category
Aerodynamics
Meeting Information
Meeting: American Helicopter Society 57th Annual Forum and Technology Display
Location: Washington, DC
Country: United States
Start Date: May 9, 2001
End Date: May 11, 2001
Sponsors: American Helicopter Society, Inc.
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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