article · Defense Technical Information Center (DTIC) · 2007
Fluidic Control of Virtual Aerosurfaces
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Abstract
This experimental research has focused on modifying the global aerodynamic characteristics of lifting surfaces at cruise (low) angles of attack when the baseline flow is fully attached. Using hybrid actuators, trapped vorticity concentrations at the leading and trailing edges affect aerodynamic forces and moment without control surfaces. Hybrid actuators employ miniature obstructions with integrated synthetic jet actuators. Actuation on the pressure surface near the leading edge results in a substantial (up to 50%) reduction in pressure drag and total drag (29%) with virtually no loss in lift, leading to a higher lift to drag ratio. When the actuation is applied near the trailing edge, the effects are bi-directional changes in pitching moments, which can be continuously varied by controlling the actuation amplitude. Moreover, the same performance can be achieved at substantially reduced actuation power by exploiting transitory aerodynamic effects through pulse modulation. PIV studies of the flow in the vicinity of the actuators, in the boundary layer and the wake, were used in this investigation.
Cite this paper
Glezer, A. (2007). Fluidic Control of Virtual Aerosurfaces. Defense Technical Information Center (DTIC).
Glezer, Ari. “Fluidic Control of Virtual Aerosurfaces.” Defense Technical Information Center (DTIC), 2007.
Glezer, Ari. 2007. “Fluidic Control of Virtual Aerosurfaces.” Defense Technical Information Center (DTIC).
Glezer, A. (2007) ‘Fluidic Control of Virtual Aerosurfaces’, Defense Technical Information Center (DTIC).
@article{glezer2007fluidic,
title = {{Fluidic Control of Virtual Aerosurfaces}},
author = {Glezer, Ari},
journal = {Defense Technical Information Center (DTIC)},
year = {2007}
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