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Helicopter Fuselage Active Flow Control in the Presence of a RotorThis work extends previous investigations of active flow control for helicopter fuselage drag and download reduction to include the effects of the rotor. The development of the new wind tunnel model equipped with fluidic oscillators is explained in terms of the previous test results. Large drag reductions greater than 20% in some cases were measured during powered testing without increasing, and in some cases decreasing download in forward flight. As confirmed by Particle Image Velocimetry (PIV), the optimum actuator configuration that provided a decrease in both drag and download appeared to create a virtual (fluidic) boat-tail fairing instead of attaching flow to the ramp surface. This idea of a fluidic fairing shifts the focus of 3D separation control behind bluff bodies from controlling/reattaching surface boundary layers to interacting with the wake flow.
Document ID
20140008727
Document Type
Conference Paper
Authors
Martin, Preston B (Army Research Development and Engineering Command NASA Langley, VA, United States)
Overmeyer, Austin D. (Army Research Development and Engineering Command NASA Langley, VA, United States)
Tanner, Philip E. (Army Research Development and Engineering Command NASA Langley, VA, United States)
Wilson, Jacob S. (Army Research Development and Engineering Command NASA Langley, VA, United States)
Jenkins, Luther N. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
July 7, 2014
Publication Date
May 20, 2014
Subject Category
Aircraft Design, Testing and Performance
Report/Patent Number
NF1676L-18577
Meeting Information
American Helicopter Society Annual Forum(Montreal, Quebec, Canada)
Funding Number(s)
WBS: WBS 031102.02.07.18.91S2.14
Distribution Limits
Public
Copyright
Other