Resources Contact Us Home
Vorticity cancellation at trailing edge for induced drag elimination

Image Number 4 for United States Patent #7134631.

Wing tip vortices are evident from airliner vapor trails, and helicopter blade slap. Elliptically loaded high aspect ratio tapered wings have minimum induced drag but cannot eliminate it. Different methods are disclosed herein, for upper and lower surface boundary layers to cancel their opposing vorticity upon shedding from the trailing edge, thereby eliminating wake vorticty, induced drag and associated noise. This requires wing-rotor-propeller or fan blades with a platform designed for uniform bound circulation and with boundary layer control near the tip. In addition this requires special techniques to counter span-wise pressure gradients, such as tip circulation control blowing or an upwind small propeller or wind turbine on each tip. These techniques can eliminate wake vorticity with its induced drag, noise, flying on the backside of the power curve and the option for asymmetric loading by pneumatic means to eliminate need for cyclic pitch control or conventional ailerons.

  Recently Added Patents
Method and device for accessing the documentation of an aircraft according to alarms generated therein
Voltage regulator structure that is operationally stable for both low and high capacitive loads
Approaching object detection system
2-aryl-4-quinazolinones and their pharmaceutical compositions
Gas flow indicator
Pose-variant face recognition using multiscale local descriptors
  Randomly Featured Patents
Collar for mounting around the neck of an animal
Gear and gear drive unit
Multiple-resolution scanning device
Cyclic compound and PPAR agonist
Electrical connector
Stream sharing for event data within an enterprise network
Desmosine derivatives and reagent for preparing artificial antigens
Data transfer and control among multiple computer devices in a gaming environment
Piston ring tension measurement apparatus
Emergency flag apparatus and associated method