Editing Wingtip vortices (section)

== Effects and mitigation ==

[[File:Air France Boeing 777-300ER planform view.jpg|thumb|Modern airliners often feature [[Aspect ratio (wing)|slender wings]] and [[wingtip device]]s]]

Wingtip vortices are associated with [[induced drag]], an unavoidable consequence of three-dimensional lift generation. The rotary motion of the air within the shed wingtip vortices (sometimes described as a "leakage") reduces the effective [[angle of attack]] of the air on the wing.

The [[lifting-line theory]] describes the shedding of trailing vortices as span-wise changes in lift distribution. For a given wing span and surface, minimal induced drag is obtained with an [[Elliptical wing|elliptical lift distribution]]. For a given lift distribution and [[wing planform]] area, induced drag is reduced with increasing [[Aspect ratio (wing)|aspect ratio]].

As a consequence, aircraft for which a high [[lift-to-drag ratio]] is desirable, such as [[Glider aircraft|gliders]] or long-range [[airliner]]s, typically have high aspect ratio wings. Such wings however have disadvantages with respect to structural constraints and maneuverability, as evidenced by [[Fighter aircraft|combat]] and [[Aerobatics|aerobatic]] planes which usually feature short, stubby wings despite the efficiency losses.

Another method of reducing induced drag is the use of [[Wingtip device|winglets]], as seen on most modern airliners. Winglets increase the effective aspect ratio of the wing, changing the pattern and magnitude of the [[vorticity]] in the vortex pattern. A reduction is achieved in the kinetic energy in the circular air flow, which reduces the amount of fuel expended to perform work upon the spinning air{{citation needed|date=May 2025}}.

After NASA became concerned about the increasing density of air traffic potentially causing vortex related accidents at airports, an experiment by NASA [[Ames Research Center]] wind tunnel testing with a 747 model found that the configuration of the flaps could be changed on existing aircraft to break the vortex into three smaller and less disturbing vortexes. This primarily involved changing the settings of the outboard flaps, and could theoretically be retrofitted to existing aircraft.<ref name="Corsiglia">{{cite report |last1=Corsiglia |first1=Victor R. |last2=Rossow |first2=Vernon J. |last3=Ciffone |first3=Donald L. |title=Experimental Study of the Effect of Span Loading on Aircraft Wakes |publisher=NASA Ames Research Center |date=1975 |url=https://ntrs.nasa.gov/api/citations/19750015407/downloads/19750015407.pdf}} </ref>