# US 9,038,950 B2 · Arrangement of aerodynamic auxiliary surfaces for an aircraft

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- Number: US 9,038,950 B2
- Document ID: US9038950B2
- Status: Granted
- Kind: B2
- Application number: 13/588,276
- Filed: 2012-08-17
- Published: 2013-01-03
- Granted: 2015-05-26
- Earliest claimed: 2010-02-19
- Assignees: Airbus Operations GmbH
- Applicants: Peter Kreuzer; Sven Schaber; Iris Goldhahn
- Inventors: Peter Kreuzer; Sven Schaber; Iris Goldhahn
- Web page: https://patentgrep.com/patent/US9038950B2

## CPC

- B64C 23/06: by generating vortices
- B64C 21/10: using other surface properties, e.g. roughness
- Y02T 50/10: Drag reduction
- B64C: AEROPLANES; HELICOPTERS
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## Abstract

An arrangement of aerodynamic auxiliary surfaces is configured for being arranged on the underside of an aircraft and furthermore includes a longitudinal axis and at least one aerodynamic auxiliary surface, wherein the aerodynamic auxiliary surface is laterally offset referred to the longitudinal axis, and wherein the aerodynamic auxiliary surface is configured for generating vortices when it is subjected to an oncoming air flow. This makes it possible to compensate vortices caused by the shape of the aircraft such that the directional stability of the aircraft can be improved and the aerodynamic drag may be reduced.

## Claims

### Claim 1

An aircraft comprising:
a fuselage comprising a fuselage upsweep at a rear of the aircraft;
at least one outwardly directed landing gear fairing in form of a sponson on the fuselage; and
at least one arrangement positioned on an underside of the at least one landing gear fairing upstream of the fuselage upsweep, the arrangement having a longitudinal axis and comprising:
a plurality of vortex generators arranged between a first edge and a second edge of the underside, said vortex generators being laterally offset relative to the longitudinal axis, and wherein said plurality of vortex generators is configured for generating vortices when said plurality of vortex generators is subjected to an oncoming air flow.

### Claim 2 (depends on 1)

The aircraft of claim 1, wherein a first side of each of said plurality of vortex generators directed downstream is spaced apart from the longitudinal axis of the arrangement by a different distance than a second side directed upstream.

### Claim 3 (depends on 1)

The aircraft of claim 1, wherein the plurality of vortex generators is arranged in a symmetric arrangement relative to the longitudinal axis of the arrangement.

### Claim 4 (depends on 1)

The aircraft of claim 1, wherein said plurality of vortex generators are configured such that a first side of the vortex generators directed downstream extends farther into the air flow around the arrangement than a second side directed upstream.

### Claim 5 (depends on 1)

The aircraft of claim 1, comprising a plurality of pairs of vortex generators arranged between a first edge and a second edge of the underside, the vortex generators of each of the plurality of the pairs being arranged symmetric to one another and positioned in groups on opposite sides of the arrangement.

### Claim 6 (depends on 1)

The aircraft of claim 1, wherein each of said plurality of vortex generators has a shape selected from a group of shapes, with the group consisting of:
triangular shape;
lunulate shape;
rectangle;
square; and
segment of a circle.

### Claim 7 (depends on 1)

The aircraft of claim 1, wherein at least one of said plurality of vortex generators is flat and has a plane shape.

### Claim 8 (depends on 1)

The aircraft of claim 1, wherein at least one of said plurality of vortex generators is twisted.

### Claim 9 (depends on 1)

The aircraft of claim 1, wherein at least one of said plurality of vortex generators has a symmetrical profile.

### Claim 10 (depends on 1)

The aircraft of claim 1, wherein at least one of said plurality of vortex generators is manufactured of a material selected from a group of materials, with the group consisting of:
metallic material;
composite fiber material;
fiber
metal laminates;
elastomer; and
thermosetting plastic.

### Claim 11 (depends on 1)

The aircraft of claim 1, wherein vortices generated by said at least one vortex generators positively influence main vortices occurring on the aircraft.

### Claim 12 (depends on 1)

The aircraft of claim 1, wherein each of the plurality of vortex generators is arranged obliquely relative to the longitudinal axis of the arrangement.

### Claim 13 (depends on 1)

The aircraft of claim 1, wherein each of the plurality of vortex generators is arranged parallel to an adjacent one of the plurality of vortex generators.

### Claim 14 (depends on 1)

The aircraft of claim 1, wherein each of the plurality of vortex generators is arranged obliquely relative to an adjacent one of the plurality of vortex generators.

### Claim 15 (depends on 1)

The aircraft of claim 1, wherein an angle of at least one of the plurality of vortex generators relative to the longitudinal axis is adjustable.