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

a technology of aircraft wings and vortex, which is applied in the direction of airflow influencers, drag reduction, transportation and packaging, etc., can solve the problems of rapid and marked decrease in the circulation in each vortex, disintegration or destruction, and achieves the effect of avoiding degrading the performance of the moving body, avoiding increasing the drag, and being convenient to constru

Inactive Publication Date: 2005-01-13
AIRBUS OPERATIONS (SAS)
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

[0029] The device according to the invention is therefore easily constructed and inexpensive. Moreover, it is passive and very robust.
[0030] Additionally, at least one of the said perturbation means is advantageously retractable. For this purpose, the said perturbation means is preferably retractable into

Problems solved by technology

This exchange of fluid causes a rapid and marked decrease in the circulation in each vortex, a

Method used

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  • Apparatus for accelerating destruction of a vortex formed by a wing of an aircraft
  • Apparatus for accelerating destruction of a vortex formed by a wing of an aircraft
  • Apparatus for accelerating destruction of a vortex formed by a wing of an aircraft

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first embodiment

[0061] In a first embodiment shown in FIG. 2, the said perturbation means 11 has an unstreamlined element 13, whose “apparent” or “effective” diameter, which is transverse with respect to the flow, depends on the wavelength of the periodic perturbation to be generated.

[0062] Preferably, this unstreamlined element 13 is a cylinder, of circular section for example, as shown in FIG. 2. However, this cylinder can also have an elliptical section or any other section. The element can also be a flat plate with a high angle of incidence, inclined at 45.degree. for example.

[0063] The “effective” transverse dimension (or width) of the element 13 therefore determines the wavelength of the generated perturbation. This “effective” width depends on the degree of deviation of the stream lines by the element 13. It is not necessarily identical to the real dimension of the element 13. For example, a flat plate perpendicular to the flow deviates the stream lines much more than a cylinder having the ...

second embodiment

[0066] In a second embodiment shown schematically in FIG. 3, the said perturbation means 12 has a means 14 of an ordinary type for producing a jet of fluid 15, as indicated by the arrows 16. This jet of fluid 15 is emitted transversely with respect to the flow E in such a way as to generate the perturbation P according to the invention, as shown in a partial way. If the said jet of fluid 15 is emitted orthogonally to the flow E, its velocity must be at least equal to that of the aircraft 2 and its diameter must be of the same order of magnitude as the apparent diameter of an unstreamlined element 13 which could be used in its place.

[0067] Preferably, the said means 14 is positioned inside the existing structure 17 in the proximity of the said creation area 10A, 10B, for example inside the flap 6A, 6B or the wing 3A, 3B. If this is not the case, the said means 14 can also be retractable.

[0068] As indicated above, the perturbation means 11, 12 must be chosen in such a way as to produ...

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Abstract

An apparatus for accelerating a destruction of a vortex is formed at the rear of a wing of an aircraft by a merging of first and second co-rotating eddies. A perturbation device is disposed adjacent of an area of creation of the first co-rotating eddy. The device is configured to generate a periodic perturbation having a wavelength capable of exciting at least on instability mode of the first eddy.

Description

CROSS REFERENCE TO RELATED APPLICATION [0001] This application claims priority under 35 U.S.C. § 119 to French Patent Application 01 02804, filed on Mar. 1, 2001, and under 35 U.S.C. § 120 to U.S. patent application Ser. No. 10 / 080,407 filed on Feb. 25, 2002, the disclosures of which are incorporated by reference herein in their entirety.FIELD OF THE INVENTION [0002] The present invention relates to a process and device for accelerating the destruction of at least two vortices in the wake of a moving body. [0003] The present invention is applied more particularly, but not exclusively, to an aircraft, especially a transport aircraft. [0004] In this case, the two (or more) vortices to which the present invention is applied are generally created when the aircraft is taking off or landing, and at least one flap, particularly a wing flap, is deployed on each wing of the aircraft. These two vortices are contra-rotating and one of them is created in each of the two wakes of the said wings ...

Claims

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Application Information

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IPC IPC(8): B64C23/06
CPCY02T50/162B64C23/06Y02T50/10
Inventor CORJON, ALEXANDRELEWEKE, THOMASLAPORTE, FLORENT
Owner AIRBUS OPERATIONS (SAS)
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