Aircraft wingtip vorticity redistribution apparatus
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United States of America Patent
Stats
-
Mar 31, 1992
Issued Date -
N/A
app pub date -
Dec 29, 1989
filing date -
Dec 29, 1989
priority date (Note) -
Expired
status (Latency Note)
Importance
Abstract
A rotor is mounted to an aircraft wing to recover induced drag associated with a wingtip vortex. When the rotor is placed in the vortex stream, the transverse component of relative wind encountered at selected increasing spanwise locations along the blade changes sign due to an increasing transverse component of blade velocity and decreasing transverse component of vortex velocity with increasing distance from the axis of rotation. In order to maximize induced drag recovery, the blade is twisted in a spanwise direction so that the inner portion of the blade drives the blade, while the radially outward portion acts as a propeller to resist rotation. The induced drag recovery is in the form of thrust generated by the rotor blade.
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