Method for accelerating destruction of a vortex formed by a wing of an aircraft

Abstract

A method of accelerating a destruction of a vortex formed at a rear of a wing of an aircraft by merging first and second co-rotating eddies. A periodic perturbation is generated adjacent an area of creation the first eddy. The periodic perturbation has a wavelength capable of exciting at least one instability mode of the first eddy.

1 . A method of accelerating a destruction of a vortex formed at a rear of a wing of an aircraft by a merging of first and second co-rotating eddies, the method comprising: 
 generating a periodic perturbation adjacent an area of creation the first eddy, the periodic perturbation having a wavelength capable of exciting at least one instability mode of the first eddy.    
     
     
         2 . The method according to  claim 1 , wherein the periodic perturbation is generated adjacent a flap of the wing.  
     
     
         3 . The method according to  claim 2 , further comprising: 
 extending a perturbation device from the area adjacent the flap of the wing; and    retracting the perturbation device into one of the wing and the flap.    
     
     
         4 . The method according to  claim 2 , further comprising: 
 extending an unstreamed element from the area adjacent the flap of the wing; and    retracting the unstreamed element into one of the wing and the flap.    
     
     
         5 . The method according to  claim 4 , wherein the unstreamed element has one of a circular and an elliptical cross section.  
     
     
         6 . The method according to  claim 2 , further comprising: 
 emitting a jet of fluid from the area adjacent the flap of the wing.    
     
     
         7 . A method of accelerating a destruction of a vortex formed at a rear of a wing of an aircraft by a merging of first and second co-rotating eddies, the method comprising: 
 emitting a jet of fluid transverse to a direction of travel of the aircraft, the jet of fluid causing a periodic perturbation having a wavelength capable of exciting at least one instability mode of the first eddy.    
     
     
         8 . The method according to  claim 7 , wherein the jet of fluid is emitted at a velocity at least equal to a velocity of the aircraft.  
     
     
         9 . The method according to  claim 8 , wherein the jet of fluid is emitted from one of the wing and a flap of the aircraft.  
     
     
         10 . A method of accelerating a destruction of first and second contra-rotating vortices formed at a rear of first and second wings of an aircraft, the first contra-rotating vortex formed by a merging of first and second co-rotating eddies, and the second contra-rotating vortex formed by a merging of third and fourth co-rotating eddies, the method comprising: 
 generating a first periodic perturbation adjacent an area of creation the first eddy, the first periodic perturbation having a first wavelength capable of exciting at least one instability mode of the first eddy; and    generating a second periodic perturbation adjacent an area of creation of the third eddy, the second periodic perturbation having a second wavelength capable of exciting at least one instability mode of the second eddy.    
     
     
         11 . The method according to  claim 10 , wherein the first and second periodic perturbations are generated such that diameters of the first and second vortices are greater than a predetermined proportion of a distance between the first and second vortices.  
     
     
         12 . The method according to  claim 11 , wherein the first and second periodic perturbations are generated such that the diameters of the first and second vortices are greater than about 30% of the distance between the first and second vortices.  
     
     
         13 . The method according to  claim 12 , wherein the first and second periodic perturbations are generated adjacent first and second flap of the first and second wings.  
     
     
         14 . The method according to  claim 13 , further comprising: 
 extending first and second perturbation devices from the areas adjacent the first and second flap of the first and second wings; and    retracting the first and second perturbation devices.    
     
     
         15 . The method according to  claim 13 , further comprising: 
 extending first and second unstreamed elements from the areas adjacent the first and second flap of the first and second wings; and    retracting the first and second unstreamed elements.    
     
     
         16 . The method according to  claim 15 , wherein the unstreamed element has one of a circular and an elliptical cross section.  
     
     
         17 . The method according to  claim 13 , further comprising: 
 emitting first and second jets of fluid from the areas adjacent the first and second flaps of the first and second wings.