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Accession Number
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ADA564094
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Title
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Aero-Effected Flight Control Using Distributed Active Bleed.
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Publication Date
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Jan 2012
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Media Count
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38p
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Personal Author
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A. Glezer A. Leonard
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Abstract
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A novel, scalable approach to aero-effected flight control of lifting surfaces using distributed active bleed was investigated experimentally and theoretically. Aerodynamic control is achieved by large-area surface bleed of air that is driven by the pressure differences in flight and is regulated by low-power surface-integrated louver actuators. The joint numerical-experimental investigation focused on the flow mechanisms of the interaction between the bleed and the cross flow and aerodynamic effects of unsteady bleed on a 2-D wing model. Particular emphasis was placed on the generation and regulation of vorticity concentrations that alter the wing s apparent aerodynamic shape and thereby its aerodynamic performance over a range of (static) angles of attack, and under time-periodic pitch oscillations. Wind tunnel investigations of the mechanisms of the time-dependent interactions between the bleed and cross flows used a 2-D Clark-Y model integrated with addressable arrays of piezoelectric louvers for regulating leading and trailing edge bleed. The resulting time- dependent forces and moment were measured over a wide range of angles of attack from pre- to post-stall using load cells, and the induced changes in surface vorticity concentrations were measured using PIV.
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Keywords
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Active control
Aerodynamic bleed
Aerodynamic forces
Bleed systems
Flight control systems
Flow fields
Lift
Lift and pitch control
Louvers
Pitch(Motion)
Vortex based reduced order model
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Source Agency
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Non Paid ADAS
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NTIS Subject Category
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51E - Avionics
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Corporate Author
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Georgia Inst. of Tech., Atlanta. School of Mechanical Engineering.
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Document Type
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Technical report
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Title Note
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Final technical rept. 31 Aug 2008-30 Sep 2011.
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NTIS Issue Number
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1302
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Contract Number
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FA9550-08-1-0398
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