Patent
Method for reducing the induced drag of a lift-generating wing and a device for carrying it out
TLDR
In this article, the vortex flow is disturbed in a deliberate manner in that additional bodies are arranged on the wing in the region where the vortices are created, and the rotation direction of which vortice is in each case in the opposite direction to that of the free vortex located at the same position along the span.Abstract:
In the case of a method for reducing the induced drag of a lift-generating wing (aerofoil) which causes free angles on the wing, the vortex flow is disturbed in a deliberate manner in that additional bodies are arranged on the wing in the region where the vortices are created. At the same time, artificial vortices are produced at discrete points on the wing with the aid of the additional bodies, the rotation direction of which vortices is in each case in the opposite direction to that of the free vortex located at the same position along the span. Their vortex intensities are in this case controlled such that they are at least approximately the same as that of the free vortex at the same point along the span. A device is used for carrying out the method, in the case of which device vortex generators in the form of flow apparatuses having an air throughput are arranged on the wing, which flow apparatuses in each case have a spin-generating, adjustable air-guidance system in their interior.read more
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Patent
Cylindrical wing tip with helical slot
TL;DR: In this paper, the shape of a spiral and/or helical slot cylindrical cavity is proposed for reducing induced drag, tip vortex and increase lift-drag ratio.
Patent
Aircraft with means for a premature breakdown of the wing vortex pair
Roland Stuff,Heinrich Vollmers +1 more
TL;DR: In this article, a premature breakdown of a wing vortex pair +/−Γ M behind an aircraft in flight is described, in which the wing vortices of the wing pair are lost behind the aircraft.
Patent
Air foil providing vortex attenuation
TL;DR: In this article, an airfoil providing vortex attenuation includes an outboard area (28), a foil extension portion (30) having a high pressure surface (32), and an orifice portion with an opening (42).
Patent
Wingtip vortex propeller
TL;DR: In this article, a wingtip pusher propeller is positioned aft of the wingtip 18 to rotate in the crossflow of the vortex to increase the energy efficiency of aircraft.
Patent
Aircraft air eddies also generate a break eddy between the wing tip and fuselage in an opposite twist to the main air eddy from the wings to merge them together to break down the main eddy behind the aircraft
Roland Stuff,Heinrich Vollmers +1 more
TL;DR: In this article, the main eddy is degraded over a flight length of at least 20 wingspans behind the aircraft and at least one break eddy (15) is merged with the degraded main eddies to trigger the instabilities within the main e eddy and break it up completely.
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Patent
Vortex generator for airfoil structures
TL;DR: A vortex generator for the ends of airfoil structures that directs air on the high pressure side of the structure into a vortex generator chamber and discharges the swirling air at the trailing edge is described in this article.
Patent
Vortex reducing wing tip
TL;DR: In this paper, an airfoil tip is constructed to droop downward and extend aft of the trailing edge of the air foil structure and to include air foil configuration both chordwise and spanwise with camber in both the chord wise and span wise directions and further including a vortex opposing twist in the chordwise direction.
Patent
Nozzle and auxiliary inlet arrangement for gas turbine engine
TL;DR: In this paper, a combined nozzle and auxiliary inlet arrangement is provided for a gas turbine engine of the variable pitch fan type wherein the fan nozzle area may be increased during the reverse pitch mode of operation to accommodate an increased reverse airflow through the fan.
Patent
Vortex arrestor and visualization system
TL;DR: In this article, a nozzle mounted adjacent the tip of an aircraft wing projects rearwardly from its trailing edge into a region most susceptible to abatement of a vortex wake that otherwise develops during flight.