CN111439372B - Vortex generator for aircraft - Google Patents
Vortex generator for aircraft Download PDFInfo
- Publication number
- CN111439372B CN111439372B CN202010316903.6A CN202010316903A CN111439372B CN 111439372 B CN111439372 B CN 111439372B CN 202010316903 A CN202010316903 A CN 202010316903A CN 111439372 B CN111439372 B CN 111439372B
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- CN
- China
- Prior art keywords
- vortex generator
- guide vane
- flow deflector
- aircraft
- airplane
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
- B64C23/06—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
- B64C23/06—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices
- B64C23/065—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices at the wing tips
- B64C23/069—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices at the wing tips using one or more wing tip airfoil devices, e.g. winglets, splines, wing tip fences or raked wingtips
- B64C23/076—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices at the wing tips using one or more wing tip airfoil devices, e.g. winglets, splines, wing tip fences or raked wingtips the wing tip airfoil devices comprising one or more separate moveable members thereon affecting the vortices, e.g. flaps
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/10—Drag reduction
Abstract
The present invention relates to vortex generators for aircraft. The vortex generator for the airplane comprises a first flow deflector and a second flow deflector, wherein the second flow deflector is installed to be perpendicular to the first flow deflector, the second flow deflector is in the shape of an isosceles triangle, and the symmetrical center line of the isosceles triangle is located in the plane of the first flow deflector. The invention can achieve the following beneficial technical effects: the ability to control the separation of the gas streams is enhanced.
Description
Technical Field
The invention relates to the technical field of aviation, in particular to a vortex generator for an airplane.
Background
The aerodynamic characteristics of the airplane are important for the safety, economy, comfort and environmental protection of civil airplanes, and the vortex generators can improve the aerodynamic characteristics of the airplane, so that the design of the airplane vortex generators plays an important role in the design of the airplane.
In order to reduce the separation of the airflow on the wing of an airplane under a large attack angle, a vortex generator is usually installed on an engine nacelle of an engine-mounted wing-hung airplane to reduce the separation of the airflow on the upper surface of the wing of the airplane under the large attack angle. Meanwhile, a vortex generator can be arranged on the flap of the airplane to control the airflow separation on the flap.
However, conventional vortex generators have less than ideal control over airflow separation.
Disclosure of Invention
It is an object of the present invention to provide a vortex generator for an aircraft which addresses the problems of the prior art and which provides enhanced control of airflow separation.
The above object of the invention is achieved by a vortex generator for an aircraft comprising a first guide vane and a second guide vane mounted perpendicular to the first guide vane, the second guide vane being in the form of an isosceles triangle whose centre line of symmetry lies in the plane of the first guide vane.
According to the technical scheme, the vortex generator for the airplane can achieve the following beneficial technical effects: the ability to control the separation of the gas streams is enhanced.
Specifically, according to the simulation calculation result, compared with the conventional vortex generator (only one guide vane), the influence range of the vortex generator (comprising the first guide vane and the second guide vane) for the aircraft of the invention can be increased by about 30%, the control capability of the air flow separation is enhanced, and the favorable effect on the aerodynamic characteristics of the aircraft can be generated.
Preferably, the vertex angle of the isosceles triangle of the second guide vane ranges from 25 degrees to 45 degrees.
According to the technical scheme, the vortex generator for the airplane can achieve the following beneficial technical effects: the control capability of the air flow separation is further enhanced through the arrangement of the proper vertex angle of the second flow deflector.
Preferably, the second guide vane is installed at a height ranging from 20% to 80% of the height of the first guide vane.
According to the technical scheme, the vortex generator for the airplane can achieve the following beneficial technical effects: the control capability of the air flow separation is further enhanced by the proper installation height setting of the second guide vanes.
Preferably, an included angle between the second guide vane and the bottom edge of the first guide vane ranges from 0 degree to 15 degrees.
According to the technical scheme, the vortex generator for the airplane can achieve the following beneficial technical effects: and the control capability of the air flow separation is further enhanced through the proper included angle arrangement of the second guide vanes.
Preferably, the number of the second guide vanes is one.
According to the technical scheme, the vortex generator for the airplane can achieve the following beneficial technical effects: the control of the separation of the gas streams is enhanced by a simpler structural improvement.
Preferably, the number of the second guide vanes is two or three, and each second guide vane is installed to be parallel to the other second guide vanes.
According to the technical scheme, the vortex generator for the airplane can achieve the following beneficial technical effects: the control of the separation of the gas streams can be further enhanced by a slightly more complex structural modification.
Preferably, the thickness of the second guide vane ranges from 5mm to 10 mm.
According to the technical scheme, the vortex generator for the airplane can achieve the following beneficial technical effects: the control capability of the air flow separation is further enhanced by the appropriate thickness setting of the second guide vane.
Preferably, the first guide vane is in a swept-back trapezoid, and the angle range of the swept-back angle of the leading edge of the first guide vane is 45-65 degrees.
According to the technical scheme, the vortex generator for the airplane can achieve the following beneficial technical effects: the first guide vane can better generate vortex and improve the airflow separation on the upper surface of the wing.
Preferably, the ratio of the length of the bottom side of the first guide vane to the height of the first guide vane ranges from 2 to 8.
According to the technical scheme, the vortex generator for the airplane can achieve the following beneficial technical effects: the first guide vane can better generate vortex and improve the airflow separation on the upper surface of the wing.
Preferably, the vortex generator is mounted on the nacelle or on the flap of the aircraft.
According to the technical scheme, the vortex generator for the airplane can achieve the following beneficial technical effects: by suitable mounting of the vortex generators, the flow separation on the upper surface of the wing or on the flap can be improved.
Drawings
Fig. 1 is a schematic perspective view of a vortex generator for an aircraft according to an embodiment of the invention.
Fig. 2 is a schematic side view of a vortex generator for an aircraft according to an embodiment of the invention.
Fig. 3 is a schematic top view of a vortex generator for an aircraft according to an embodiment of the invention.
Fig. 4 is a schematic front view of a vortex generator for an aircraft according to an embodiment of the invention.
List of reference numerals
1. First flow deflector
2. Second flow deflector
Detailed Description
While specific embodiments of the invention will be described below, it should be noted that in the course of the detailed description of these embodiments, in order to provide a concise and concise description, all features of an actual implementation may not be described in detail. It should be appreciated that in the development of any such actual implementation, as in any engineering or design project, numerous implementation-specific decisions are made to achieve the developers' specific goals, such as compliance with system-related and business-related constraints, which may vary from one implementation to another. Moreover, it should be further appreciated that such a development effort might be complex and tedious, but would nevertheless be a routine undertaking of design, fabrication, and manufacture for those of ordinary skill having the benefit of this disclosure, and thus should not be construed as a complete understanding of this disclosure.
Unless otherwise defined, technical or scientific terms used in the claims and the specification should have the ordinary meaning as understood by those of ordinary skill in the art to which the invention belongs. The use of "first," "second," and similar terms in the description and claims of the present application do not denote any order, quantity, or importance, but rather the terms are used to distinguish one element from another. The terms "a" or "an," and the like, do not denote a limitation of quantity, but rather denote the presence of at least one. The word "comprise" or "comprises", and the like, means that the element or item listed before "comprises" or "comprising" covers the element or item listed after "comprising" or "comprises" and its equivalent, and does not exclude other elements or items. The terms "connected" or "coupled" and the like are not restricted to physical or mechanical connections, nor are they restricted to direct or indirect connections.
Fig. 1 is a schematic perspective view of a vortex generator for an aircraft according to an embodiment of the invention. Fig. 2 is a schematic side view of a vortex generator for an aircraft according to an embodiment of the invention. Fig. 3 is a schematic top view of a vortex generator for an aircraft according to an embodiment of the invention. Fig. 4 is a schematic front view of a vortex generator for an aircraft according to an embodiment of the invention.
As shown in fig. 1 to 4, according to an embodiment of the present invention, a vortex generator for an aircraft includes a first guide vane 1 and a second guide vane 2, the second guide vane 2 is installed perpendicular to the first guide vane 1, the second guide vane 2 is in the shape of an isosceles triangle, and a symmetrical center line of the isosceles triangle (i.e., a bisector of a vertex angle of a high or isosceles triangle on a base plate of the isosceles triangle) is located in a plane of the first guide vane 1.
According to the technical scheme, the vortex generator for the airplane can achieve the following beneficial technical effects: the ability to control the separation of the gas streams is enhanced.
Specifically, according to the simulation calculation result, compared with the conventional vortex generator (only one guide vane), the influence range of the vortex generator (comprising the first guide vane and the second guide vane) for the aircraft of the invention can be increased by about 30%, the control capability of the air flow separation is enhanced, and the favorable effect on the aerodynamic characteristics of the aircraft can be generated.
Preferably, as shown in fig. 1 to 4, the vertex angle of the isosceles triangle of the second guide vane 2 ranges from 25 degrees to 45 degrees.
According to the technical scheme, the vortex generator for the airplane can achieve the following beneficial technical effects: the control capability of the air flow separation is further enhanced through the arrangement of the proper vertex angle of the second flow deflector.
Preferably, as shown in fig. 1 to 4, the height of the isosceles triangle of the second guide vane 2 is in the range of 100mm to 700mm, and the width of the isosceles triangle is in the range of 200mm to 400 mm.
Preferably, as shown in fig. 1 to 4, the second guide vanes 2 are installed at a height ranging from 20% to 80% of the first guide vanes 1.
According to the technical scheme, the vortex generator for the airplane can achieve the following beneficial technical effects: the control capability of the air flow separation is further enhanced by the proper installation height setting of the second guide vanes.
Preferably, as shown in fig. 1 to 4, the included angle between the second guide vane 2 and the bottom edge of the first guide vane 1 ranges from 0 degree to 15 degrees.
According to the technical scheme, the vortex generator for the airplane can achieve the following beneficial technical effects: and the control capability of the air flow separation is further enhanced through the proper included angle arrangement of the second guide vanes.
Preferably, the number of second guide vanes 2 is one, as shown in fig. 1-4.
According to the technical scheme, the vortex generator for the airplane can achieve the following beneficial technical effects: the control of the separation of the gas streams is enhanced by a simpler structural improvement.
Preferably, the number of second guide vanes 2 is two or three, and each second guide vane 2 is installed to be parallel to the other second guide vanes 2.
According to the technical scheme, the vortex generator for the airplane can achieve the following beneficial technical effects: the control of the separation of the gas streams can be further enhanced by a slightly more complex structural modification.
Preferably, the thickness of the second guide vanes 2 ranges from 5mm to 10mm, as shown in fig. 1 to 4.
According to the technical scheme, the vortex generator for the airplane can achieve the following beneficial technical effects: the control capability of the air flow separation is further enhanced by the appropriate thickness setting of the second guide vane.
Of course, the above-described second vane thickness is only one preferred form of second vane thickness for use with vortex generators for aircraft in accordance with the present application, and those skilled in the art will appreciate based on the present disclosure that other suitable second vane thicknesses (e.g., 3mm, 12mm, etc.) may be used without departing from the scope of the present claims.
Preferably, as shown in fig. 1 to 4, the first guide vane 1 has a swept-back trapezoidal shape, and the angle of the swept-back angle of the leading edge is in the range of 45 degrees to 65 degrees.
According to the technical scheme, the vortex generator for the airplane can achieve the following beneficial technical effects: the first guide vane can better generate vortex and improve the airflow separation on the upper surface of the wing.
Preferably, the ratio of the length of the bottom side of the first guide vane 1 to the height is in the range of 2-8, as shown in fig. 1-4. That is, the length of the bottom side of the first guide vane 1 is 2 to 8 times as long as it is high.
According to the technical scheme, the vortex generator for the airplane can achieve the following beneficial technical effects: the first guide vane can better generate vortex and improve the airflow separation on the upper surface of the wing.
Preferably, as shown in fig. 1 to 4, the length of the bottom edge of the first guide vane 1 ranges from 600mm to 1200mm, and the height ranges from 150mm to 350 mm.
Preferably, the thickness of the first guide vane 2 ranges from 5mm to 10mm, as shown in fig. 1 to 4.
Of course, the first vane thickness described above is only one preferred form of first vane thickness for use with vortex generators for aircraft in the present application, and those skilled in the art will appreciate based on the present disclosure that other suitable first vane thicknesses (e.g., 3mm, 12mm, etc.) may be used without departing from the scope of the present claims.
Preferably, the vortex generator is mounted on the nacelle or on the flap of the aircraft.
According to the technical scheme, the vortex generator for the airplane can achieve the following beneficial technical effects: by suitable mounting of the vortex generators, the flow separation on the upper surface of the wing or on the flap can be improved.
Preferably, the vortex generators are mounted: the first guide vane 1 is substantially perpendicular to the surface on which it is mounted, for example the surface of a nacelle or the surface of a flap.
While particular embodiments of the present invention have been described above, it will be understood by those skilled in the art that they are not intended to limit the invention, and that various modifications may be made by those skilled in the art based on the above disclosure without departing from the scope of the invention.
Claims (9)
1. The vortex generator is characterized by comprising a first flow deflector and a second flow deflector, wherein the second flow deflector is installed to be perpendicular to the first flow deflector, the second flow deflector is in the shape of an isosceles triangle, the symmetric center line of the isosceles triangle is located in the plane of the first flow deflector, and the vertex angle range of the isosceles triangle of the second flow deflector is 25-45 degrees.
2. The vortex generator for an aircraft according to claim 1, wherein the second guide vane is mounted at a height in the range of 20% to 80% of the height of the first guide vane.
3. The vortex generator of claim 1, wherein an angle between the second baffle and a bottom edge of the first baffle ranges from 0 degrees to 15 degrees.
4. The vortex generator for an aircraft according to claim 1, wherein the number of second flow deflectors is one.
5. The vortex generator for an aircraft according to claim 1, wherein the number of second guide vanes is two or three, each second guide vane being mounted parallel to the other second guide vanes.
6. The vortex generator for an aircraft according to claim 1, wherein the second flow deflector has a thickness in the range of 5mm to 10 mm.
7. The vortex generator of claim 1 wherein the first baffle is swept-back trapezoidal having a leading edge sweep angle in the range of 45 degrees to 65 degrees.
8. The vortex generator for an aircraft according to claim 1, wherein a ratio of a base length to a height of the first baffle is in a range of 2-8.
9. The vortex generator for an aircraft according to claim 1, wherein the vortex generator is mounted on an engine nacelle or on a flap of the aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010316903.6A CN111439372B (en) | 2020-04-21 | 2020-04-21 | Vortex generator for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010316903.6A CN111439372B (en) | 2020-04-21 | 2020-04-21 | Vortex generator for aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111439372A CN111439372A (en) | 2020-07-24 |
| CN111439372B true CN111439372B (en) | 2021-10-08 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202010316903.6A Active CN111439372B (en) | 2020-04-21 | 2020-04-21 | Vortex generator for aircraft |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104108463A (en) * | 2013-04-19 | 2014-10-22 | 波音公司 | Winglet Attach Fitting And Method For Attaching A Split Winglet To A Wing |
| CN205022846U (en) * | 2015-05-07 | 2016-02-10 | 哈尔滨飞机工业集团有限责任公司 | A vortex generator for aircraft vertical fin |
| CN108953074A (en) * | 2018-08-14 | 2018-12-07 | 株洲时代新材料科技股份有限公司 | A kind of wind electricity blade vortex generator |
| CN110450942A (en) * | 2019-06-27 | 2019-11-15 | 南京航空航天大学 | It is a kind of for fuselage drag reduction and delay air-flow separate vortex generator |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2905930B1 (en) * | 2006-09-18 | 2009-05-15 | Airbus France Sa | TOURBILLON GENERATOR IN HOT GAS OUTPUT |
| US8528601B2 (en) * | 2009-03-30 | 2013-09-10 | The Regents Of The University Of Michigan | Passive boundary layer control elements |
-
2020
- 2020-04-21 CN CN202010316903.6A patent/CN111439372B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104108463A (en) * | 2013-04-19 | 2014-10-22 | 波音公司 | Winglet Attach Fitting And Method For Attaching A Split Winglet To A Wing |
| CN205022846U (en) * | 2015-05-07 | 2016-02-10 | 哈尔滨飞机工业集团有限责任公司 | A vortex generator for aircraft vertical fin |
| CN108953074A (en) * | 2018-08-14 | 2018-12-07 | 株洲时代新材料科技股份有限公司 | A kind of wind electricity blade vortex generator |
| CN110450942A (en) * | 2019-06-27 | 2019-11-15 | 南京航空航天大学 | It is a kind of for fuselage drag reduction and delay air-flow separate vortex generator |
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| Publication number | Publication date |
|---|---|
| CN111439372A (en) | 2020-07-24 |
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