CN208882103U - A kind of aircraft drag reduction vortex generator - Google Patents
A kind of aircraft drag reduction vortex generator Download PDFInfo
- Publication number
- CN208882103U CN208882103U CN201821090534.8U CN201821090534U CN208882103U CN 208882103 U CN208882103 U CN 208882103U CN 201821090534 U CN201821090534 U CN 201821090534U CN 208882103 U CN208882103 U CN 208882103U
- Authority
- CN
- China
- Prior art keywords
- vortex generator
- aircraft
- drag reduction
- vortex
- generator
- Prior art date
- 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.)
- Active
Links
Classifications
-
- 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
Landscapes
- Wind Motors (AREA)
Abstract
The utility model discloses a kind of drag reduction vortex generators, belong to overall Design of Aerodynamic Configuration field, are related to aircraft drag reduction vortex generator.A secondary vortex generator is devised at left and right sides of aircraft endpiece horizontal tail inferoanterior fuselage, it is aerofoil profile feature that it, which is opened up to section, downward projection is trapezoidal, installing the vortex generator additional can reduce the cruise drag of aircraft, reduce aircraft utilization cost, while influence of the stringent control vortex generator to aircraft other aspects aerodynamic characteristic.
Description
Technical field:
The utility model is related to aircraft drag reduction vortex generator shape, belongs to aircraft totality Design of Aerodynamic Configuration neck
Domain.
Background technique:
A kind of vortex generator.Certain type machine since afterbody upper uplifting angle influences, under cruising condition fuselage trailing vortex intensity compared with
Greatly, the pressure drag of generation is that one of the important sources of full machine aerodynamic drag change by using the designing technique of vortex generator
The flow field characteristic for becoming fuselage surface helps to weaken trailing vortex intensity, reduces pressure drag.CFD is calculated and wind tunnel test shows this
Vortex generator can reduce about 8 resistance points of resistance, effectively reduce the use cost of aircraft, at the same to other aerodynamic characteristics and
Handling quality is substantially without influence.
Summary of the invention:
(1) goal of the invention: the utility model proposes a kind of aircraft drag reduction vortex hair under the premise of meeting flying quality
Raw device.
The technical solution of the utility model is to design and install additional at left and right sides of aircraft endpiece horizontal tail inferoanterior fuselage
A pair of of vortex generator reduces aircraft utilization cost to reduce the cruise drag of aircraft.
(2) technical solution
In order to solve the above-mentioned technical problem, the utility model is achieved through the following technical solutions: a kind of aircraft drag reduction
Vortex generator, the generator bow projection profile be it is trapezoidal, open up to cross-sectional profile be aerofoil profile feature, with vortex generator root
String leading edge point is coordinate origin O, is positive, is positive in Y-axis, Z axis meets the right-hand rule, in vortex generator batten after X axis
Multiple coordinate points are chosen on curve, measurement unit mm:
| X | Y | Z | X | Y | Z | X | Y | Z |
| 319.34 | 3.85 | 0 | 319.34 | 3.07 | 150 | 319.34 | 2.28 | 300 |
| 297.44 | 9.21 | 0 | 300.57 | 7.66 | 150 | 303.70 | 6.12 | 300 |
| 275.42 | 14.03 | 0 | 281.69 | 11.79 | 150 | 287.97 | 9.56 | 300 |
| 253.28 | 18.31 | 0 | 262.72 | 15.46 | 150 | 272.16 | 12.61 | 300 |
| 231.05 | 22.08 | 0 | 243.67 | 18.69 | 150 | 256.28 | 15.30 | 300 |
| 208.74 | 25.35 | 0 | 224.54 | 21.50 | 150 | 240.34 | 17.64 | 300 |
| 186.36 | 28.05 | 0 | 205.36 | 23.81 | 150 | 224.35 | 19.57 | 300 |
| 163.91 | 30.14 | 0 | 186.12 | 25.60 | 150 | 208.32 | 21.06 | 300 |
| 141.41 | 31.57 | 0 | 166.83 | 26.82 | 150 | 192.25 | 22.08 | 300 |
| 118.87 | 32.11 | 0 | 147.51 | 27.29 | 150 | 176.15 | 22.47 | 300 |
| 96.34 | 31.46 | 0 | 128.20 | 26.74 | 150 | 160.05 | 22.01 | 300 |
| 73.89 | 29.39 | 0 | 108.96 | 24.96 | 150 | 144.02 | 20.53 | 300 |
| 51.66 | 25.66 | 0 | 89.90 | 21.77 | 150 | 128.14 | 17.87 | 300 |
| 29.89 | 19.84 | 0 | 71.24 | 16.77 | 150 | 112.59 | 13.71 | 300 |
| 9.29 | 10.78 | 0 | 53.59 | 9.01 | 150 | 97.88 | 7.24 | 300 |
| 0.00 | 0.00 | 0 | 45.62 | -0.23 | 150 | 91.24 | -0.47 | 300 |
| 4.46 | -5.97 | 0 | 49.44 | -5.35 | 150 | 94.42 | -4.73 | 300 |
| 26.42 | -10.36 | 0 | 68.26 | -9.11 | 150 | 110.11 | -7.87 | 300 |
| 48.95 | -10.80 | 0 | 87.58 | -9.49 | 150 | 126.21 | -8.18 | 300 |
| 71.49 | -10.12 | 0 | 106.90 | -8.91 | 150 | 142.30 | -7.70 | 300 |
| 94.01 | -9.01 | 0 | 126.20 | -7.95 | 150 | 158.39 | -6.90 | 300 |
| 116.53 | -7.96 | 0 | 145.51 | -7.06 | 150 | 174.48 | -6.15 | 300 |
| 139.05 | -6.94 | 0 | 164.81 | -6.18 | 150 | 190.57 | -5.43 | 300 |
| 161.58 | -6.05 | 0 | 184.12 | -5.42 | 150 | 206.66 | -4.79 | 300 |
| 184.11 | -5.16 | 0 | 203.43 | -4.65 | 150 | 222.75 | -4.15 | 300 |
| 206.64 | -4.26 | 0 | 222.74 | -3.89 | 150 | 238.84 | -3.51 | 300 |
| 229.17 | -3.47 | 0 | 242.06 | -3.21 | 150 | 254.94 | -2.94 | 300 |
| 251.71 | -2.81 | 0 | 261.37 | -2.64 | 150 | 271.04 | -2.47 | 300 |
| X | Y | Z | X | Y | Z | X | Y | Z |
| 274.25 | -2.29 | 0 | 280.69 | -2.20 | 150 | 287.14 | -2.10 | 300 |
| 296.80 | -1.91 | 0 | 300.02 | -1.87 | 150 | 303.24 | -1.83 | 300 |
| 319.34 | -1.63 | 0 | 319.34 | -1.63 | 150 | 319.34 | -1.63 | 300 |
Each coordinate points of identical Z-direction coordinate are sequentially connected generation spline curve respectively, formed vortex generator Z to
The closing of the curved surface of generation is by cross-sectional profile control line using each section front and rear edges point line as the controlling curve of curved surface Z-direction
The shape of vortex generator.
The vortex generator is composite material manufacture, and inside is filled with foam core, outside alkali-free glass molding with cloth.
3) beneficial effect
The beneficial effects of the utility model are: the vortex generator of the utility model, weakens trailing vortex intensity, reduce pressure difference resistance
Power.CFD and results of wind tunnel show: relative to vortex generator state is not added, which makes aircraft in cruise shape
About 8 resistance points of state drag reduction, can effectively reduce use cost.Simultaneously to other aerodynamic characteristics and handling quality substantially without
It influences.
Detailed description of the invention
The attached drawing of the utility model has 4, and Detailed description of the invention is as follows:
Fig. 1 is a kind of side view of drag reduction vortex generator；
Fig. 2 is a kind of front view of drag reduction vortex generator；
Fig. 3 is a kind of top view of drag reduction vortex generator；
Fig. 4 is a kind of scheme of installation of drag reduction vortex generator.
Wherein 1 is drag reduction vortex generator, and 2 be horizontal tail, and 3 be vertical fin.
Specific embodiment
A kind of drag reduction vortex generator, bowing, it is trapezoidal to be projected as, and opening up to section is aerofoil profile feature, establishes with vortex generator
Root string leading edge point is the coordinate system of coordinate origin O, is positive, is positive in Y-axis, Z axis meets the right-hand rule, is being vortexed after X axis
Multiple coordinate points are chosen in generator spline curve, measurement unit mm:
Each coordinate points of identical Z-direction coordinate are sequentially connected generation spline curve respectively, formed vortex generator Z to
The closing of the curved surface of generation is by cross-sectional profile control line using each section front and rear edges point line as the controlling curve of curved surface Z-direction
The shape of vortex generator.The vortex generator is composite material manufacture, and inside is filled with foam core, outside alkali-free glass
Molding with cloth.
Claims (2)
1. a kind of aircraft drag reduction vortex generator, it is characterised in that: the generator bow projection profile be it is trapezoidal, open up to section
Shape is that aerofoil profile feature is positive after X axis, is positive in Y-axis using vortex generator root string leading edge point as coordinate origin O, Z axis
Meet the right-hand rule, multiple coordinate points chosen in vortex generator spline curve, measurement unit mm:
Each coordinate points of identical Z-direction coordinate are sequentially connected generation spline curve respectively, are formed outside the section of vortex generator Z-direction
The curved surface closing of generation is vortex hair using each section front and rear edges point line as the controlling curve of curved surface Z-direction by shape control line
Raw device.
2. vortex generator according to claim 1, it is characterised in that: the vortex generator is composite material manufacture,
Inside is filled with foam core, outside alkali-free glass molding with cloth.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821090534.8U CN208882103U (en) | 2018-07-11 | 2018-07-11 | A kind of aircraft drag reduction vortex generator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821090534.8U CN208882103U (en) | 2018-07-11 | 2018-07-11 | A kind of aircraft drag reduction vortex generator |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208882103U true CN208882103U (en) | 2019-05-21 |
Family
ID=66506455
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821090534.8U Active CN208882103U (en) | 2018-07-11 | 2018-07-11 | A kind of aircraft drag reduction vortex generator |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208882103U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN110733626A (en) * | 2019-10-10 | 2020-01-31 | 中航通飞研究院有限公司 | flow deflector for improving rolling stability of airplane and method thereof |
| CN110920870A (en) * | 2019-11-18 | 2020-03-27 | 北京航空航天大学 | A method for suppressing rocking motion of pointed side edge fuselage layouts by leading edge flaps |
| RU199016U1 (en) * | 2020-03-31 | 2020-08-07 | Евгений Алексеевич Прокопенко | Subsonic aircraft with a thick wing profile with a drag reduction device |
-
2018
- 2018-07-11 CN CN201821090534.8U patent/CN208882103U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN110733626A (en) * | 2019-10-10 | 2020-01-31 | 中航通飞研究院有限公司 | flow deflector for improving rolling stability of airplane and method thereof |
| CN110733626B (en) * | 2019-10-10 | 2023-10-27 | 中航通飞华南飞机工业有限公司 | Guide vane and method for improving rolling stability of airplane |
| CN110920870A (en) * | 2019-11-18 | 2020-03-27 | 北京航空航天大学 | A method for suppressing rocking motion of pointed side edge fuselage layouts by leading edge flaps |
| RU199016U1 (en) * | 2020-03-31 | 2020-08-07 | Евгений Алексеевич Прокопенко | Subsonic aircraft with a thick wing profile with a drag reduction device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN208882103U (en) | A kind of aircraft drag reduction vortex generator | |
| US7300021B2 (en) | Aerospace vehicle fairing systems and associated methods | |
| CN101596934B (en) | Wingtip eddy diffusion device | |
| CN107140180B (en) | Hypersonic rider double-vane aerodynamic arrangement | |
| CN106650095B (en) | Correction method of unmanned aerial vehicle control matrix based on wind tunnel test data and CFD calculation | |
| CN204489176U (en) | The drag rudder of a kind of anury Flying-wing aircraft | |
| CN101885381A (en) | dimpled wing | |
| CN111516871A (en) | Supersonic stealth unmanned aerial vehicle with pneumatic stealth integrated design | |
| CN104118556A (en) | Special spoon-shaped wing section with ultra-low Reynolds number, high lift-drag ratio and low speed | |
| CN103303461B (en) | A kind of aircraft antenna fairing | |
| CN204937477U (en) | The aerofoil profile of a kind of low-resistance, low pitching moment | |
| CN104724281B (en) | A kind of combination leading edge Waverider method for designing and combination leading edge Waverider | |
| CN202953169U (en) | Novel spoon-shaped blended winglet for civil airplane | |
| CN111017185B (en) | Laminar flow technology verification machine | |
| CN103612746B (en) | Fairing structure of suspension in wing suspension layout aircraft | |
| CN104309813B (en) | Design method for shape of helicopter tail beam | |
| CN103407574B (en) | Novel efficient notch airfoil shape of parafoil unmanned plane and optimum design method thereof | |
| US20240124121A1 (en) | Aviation turbofan engine and fan duct nozzle | |
| CN208216978U (en) | A kind of aircraft horizontal tail root vortex generator | |
| CN209008845U (en) | A kind of high aspect ratio wing of high lift-rising | |
| CN204341388U (en) | A kind of passenger plane connecting wing configuration | |
| CN104494843B (en) | A kind of aircraft slotted flap design method | |
| CN109895996A (en) | A kind of high-lift wing of light-duty sport plane | |
| CN110539882A (en) | Method and device for optimizing flow at junction of leading edge bending flap and leading edge slat | |
| CN203158227U (en) | Improved airplane |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address |
Address after: 723213 Liulin Town, Chenggu County, Hanzhong City, Shaanxi Province Patentee after: Shaanxi Aircraft Industry Co.,Ltd. Address before: 723213 cuijiashan Town, Hanzhong City, Shaanxi Province Patentee before: Shaanxi Aircraft INDUSTRY(GROUP) Co.,Ltd. |
|
| CP03 | Change of name, title or address |