CN111017192A - Mixed laminar flow wing suitable for double-fuselage layout verification machine - Google Patents
Mixed laminar flow wing suitable for double-fuselage layout verification machine Download PDFInfo
- Publication number
- CN111017192A CN111017192A CN201911346703.9A CN201911346703A CN111017192A CN 111017192 A CN111017192 A CN 111017192A CN 201911346703 A CN201911346703 A CN 201911346703A CN 111017192 A CN111017192 A CN 111017192A
- Authority
- CN
- China
- Prior art keywords
- air suction
- laminar flow
- double
- flow wing
- mixed
- 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.)
- Pending
Links
- 238000012795 verification Methods 0.000 title abstract description 8
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000029058 respiratory gaseous exchange Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
- B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
- B64C21/06—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for sucking
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a mixed laminar flow wing suitable for a double-fuselage layout verification machine, which is arranged between the double fuselage, wherein the center of a front edge wallboard of the mixed laminar flow wing is an air suction control area, air suction holes are uniformly arranged in the air suction control area, an air suction cavity is arranged below the air suction control area, the upper surface of the air suction cavity is communicated with the air suction holes, and the lower surface of the air suction cavity is connected with a mixed laminar flow air suction control device.
Description
Technical Field
The invention belongs to the technical field of aviation, and particularly relates to a mixed laminar flow wing suitable for a double-fuselage layout verification machine.
Background
The drag experienced by an aircraft during flight results largely from the frictional drag of the airflow against the aircraft surfaces. The laminar design of the aircraft wings is of great significance in improving the aircraft flight economy and reducing the cost. The air suction in the front edge area of the wing forms a forward pressure gradient, so that the mixed layer flow control of the wing is realized, the range of the laminar flow area on the surface of the wing is greatly improved, and the flight resistance is reduced.
Therefore, the wing section of the high-Reynolds-number mixed laminar flow wing is designed for the double-fuselage layout verification machine. The large-range laminar flow of the surface of the wing can be realized, and the flight resistance is reduced.
Disclosure of Invention
The purpose of the invention is as follows: the mixed laminar flow wing suitable for the double-fuselage layout verification machine is provided to realize the flow control of mixed layers on the surface of the wing, so that the frictional resistance is reduced, and the performance of the airplane is improved.
The technical scheme of the invention is as follows:
the mixed laminar flow wing is arranged between the two bodies, the center of a front edge wall plate of the mixed laminar flow wing is an air suction control area, air suction holes are uniformly arranged in the air suction control area, an air suction cavity is arranged below the air suction control area, the upper surface of the air suction cavity is communicated with the air suction holes, and the lower surface of the air suction cavity is connected with a mixed laminar flow air suction control device.
The average aerodynamic chord length of the mixed laminar flow wing is 1.44m, and the aspect ratio is 0.938.
The mixed laminar flow wing has 28 degrees of leading edge sweep angle and 17 degrees of trailing edge sweep angle.
The air suction control area is arranged in the range of the front 13 percent chord length of the mixed laminar flow wing leading edge wall plate in the middle span direction of 0.5 m.
The aperture of the air suction hole is 55-65 μm, and the hole distance is 12 times of the aperture.
The lower surface of the air suction cavity is connected with the mixed laminar flow air suction control device through a pipeline.
The air suction cavities are distributed along the spanwise direction according to the equal proportion of 0-12% of chord length, and the length of the spanwise direction is 500 mm.
The air suction cavity is divided into a front cavity and a rear cavity along the chord direction, and the length ratio of the front cavity to the rear cavity in the chord direction is 1: 2.
the invention has the beneficial effects that: the invention provides a mixed laminar flow wing suitable for a double-fuselage layout verification aircraft, which changes the head speed type of a wing section by forming negative pressure in an air suction cavity inside the wing section, enlarges the laminar flow area range of the wing section and reduces flight resistance.
Description of the drawings:
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic diagram of the present invention applied to a dual-body;
FIG. 3 is a schematic view of the arrangement of suction holes in the suction control area;
FIG. 4 is a top view of the distribution of the front and rear chambers of the suction chamber;
FIG. 5 is a sectional view of the front and rear chambers of the suction chamber;
FIG. 6 is a schematic view of the structure of the suction chamber;
the mixed laminar flow air suction control device comprises a double-body air suction control device, a mixed laminar flow wing air suction control device, an air suction control area air suction control device, an air suction hole.
The specific implementation mode is as follows:
the present invention is described in further detail below with reference to the attached drawings.
The utility model provides a mix laminar flow wing suitable for double fuselage layout verification machine, mix laminar flow wing 2 set up between double fuselage 1, mix laminar flow wing 2 leading edge wallboard centre is inspiration control area 3, inspiration control area 3 evenly arranged have the suction hole 4, the control area 3 of breathing in has arranged the air suction cavity down, the air suction cavity upper surface communicates with each other with the suction hole 4, the lower surface links to each other with mixing laminar flow inspiration controlling means 7. The aperture of the air suction holes 4 is 55-65 μm, and the hole distance is 12 times of the aperture. The airfoil surface opening is schematically illustrated in fig. 3, where the hole pitch a is 700 microns.
TABLE 1 geometrical parameters of the suction holes
The average aerodynamic chord length of the mixed laminar flow wing 2 is 1.44m, and the aspect ratio is 0.938.
The mixed laminar wing 2 has a leading edge sweep angle of 28 degrees and a trailing edge sweep angle of 17 degrees.
The air suction control area 3 is arranged in the middle span-wise 0.5m and front 13% chord length range of the front edge wall plate of the mixed laminar flow wing 2.
An equal-area air suction cavity is arranged below the air suction control area 3, the upper surface of the cavity is communicated with the air suction hole 4, and the lower surface of the cavity is connected with a mixed laminar flow air suction control device 7 through a pipeline. The air suction cavity is designed according to the following principle:
the cavity a ensures that all the air suction holes 4 are the same as a suction pipeline, and ensures that all the air suction holes 4 have more uniform suction speed as much as possible;
b, according to the characteristics of the pressure distribution of the front edge of the mixed laminar flow wing 2, the mixed laminar flow wing is divided into a front cavity and a rear cavity along the chord direction;
c, the cavity structure is located in the front area of the front beam as much as possible and does not interfere with the front beam;
the cavity keeps absolute sealing except the connection with the air suction hole 4 and the pipeline;
the cavity plan and cross-sectional views are shown in fig. 4, 5, 6. The cavity has a spanwise width of 500mm, and is distributed along the spanwise direction according to an equal proportion of 0-12% of chord length. The length ratio of the front cavity to the rear cavity in the chord direction is 1: 2.
during testing, the mixed laminar flow air suction control device 7 works to generate negative pressure in the air suction cavity to suck airflow in the boundary layer of the leading edge and change the speed type of the airflow, so that the flow stability of the surface of the wing is improved, laminar flow with a larger area is realized, the friction resistance is reduced, and the flight economy of the airplane is improved.
Claims (8)
1. The utility model provides a mix laminar flow wing suitable for machine is verified to double fuselage layout which characterized in that: the mixed laminar flow wing (2) is arranged between the two machine bodies (1), the air suction control area (3) is arranged in the center of the front edge wall plate of the mixed laminar flow wing (2), air suction holes (4) are uniformly arranged in the air suction control area (3), an air suction cavity is arranged below the air suction control area (4), the upper surface of the air suction cavity is communicated with the air suction holes (4), and the lower surface of the air suction cavity is connected with the mixed laminar flow air suction control device (7).
2. The hybrid laminar flow wing suitable for the double-fuselage layout verifier as claimed in claim 1, wherein: the average aerodynamic chord length of the mixed laminar flow wing (2) is 1.44m, and the aspect ratio is 0.938.
3. The hybrid laminar flow wing suitable for the double-fuselage layout verifier as claimed in claim 1, wherein: the mixed laminar flow wing (2) has a leading edge sweep angle of 28 degrees and a trailing edge sweep angle of 17 degrees.
4. The hybrid laminar flow wing suitable for the double-fuselage layout verifier as claimed in claim 1, wherein: the air suction control area (3) is arranged in the span-wise direction of the midpoint of a leading edge wall plate of the mixed laminar flow wing (2) to be 0.5m and within the front 13% chord length range.
5. The hybrid laminar flow wing suitable for the double-fuselage layout verifier as claimed in claim 1, wherein: the aperture of the air suction holes (4) is 55-65 μm, and the hole spacing is 12 times of the aperture.
6. The hybrid laminar flow wing suitable for the double-fuselage layout verifier as claimed in claim 1, wherein: the lower surface of the air suction cavity is connected with a mixed layer flow air suction control device (7) through a pipeline.
7. The hybrid laminar flow wing suitable for the double-fuselage layout verifier as claimed in claim 1, wherein: the air suction cavities are distributed along the spanwise direction according to the equal proportion of 0-12% of chord length, and the length of the spanwise direction is 500 mm.
8. The hybrid laminar flow wing suitable for the double-fuselage layout verifier as claimed in claim 1, wherein: the suction cavity body divide into preceding chamber (5), back cavity (6) along the chordwise, the chordwise length ratio of preceding back cavity is 1: 2.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911346703.9A CN111017192A (en) | 2019-12-24 | 2019-12-24 | Mixed laminar flow wing suitable for double-fuselage layout verification machine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911346703.9A CN111017192A (en) | 2019-12-24 | 2019-12-24 | Mixed laminar flow wing suitable for double-fuselage layout verification machine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111017192A true CN111017192A (en) | 2020-04-17 |
Family
ID=70212111
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911346703.9A Pending CN111017192A (en) | 2019-12-24 | 2019-12-24 | Mixed laminar flow wing suitable for double-fuselage layout verification machine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111017192A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112660416A (en) * | 2020-12-24 | 2021-04-16 | 中国航空工业集团公司西安飞机设计研究所 | Laminar flow control technology verification machine |
| CN115675917A (en) * | 2022-11-15 | 2023-02-03 | 中国空气动力研究与发展中心空天技术研究所 | Mix layer flow control on unmanned aerial vehicle and use getter device |
| CN117818871A (en) * | 2024-03-04 | 2024-04-05 | 中国空气动力研究与发展中心高速空气动力研究所 | Application method of passive mixed laminar flow nacelle |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101348170A (en) * | 2008-09-01 | 2009-01-21 | 北京航空航天大学 | Wing structure having lamellar flow flowing control and separation control |
| CN103144769A (en) * | 2013-03-05 | 2013-06-12 | 西北工业大学 | Pneumatic layout of vertical taking-off and landing aircraft with tilted duct |
| CN107264775A (en) * | 2017-06-16 | 2017-10-20 | 青岛华创风能有限公司 | Air cavity connects controller |
| CN207045693U (en) * | 2017-06-16 | 2018-02-27 | 青岛华创风能有限公司 | Air cavity connects controller |
| US20190092456A1 (en) * | 2017-09-28 | 2019-03-28 | Airbus Operations Limited | Ducts for laminar flow control systems |
| US20190118923A1 (en) * | 2017-10-20 | 2019-04-25 | Airbus Operations Limited | Apparatus for laminar flow control |
-
2019
- 2019-12-24 CN CN201911346703.9A patent/CN111017192A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101348170A (en) * | 2008-09-01 | 2009-01-21 | 北京航空航天大学 | Wing structure having lamellar flow flowing control and separation control |
| CN103144769A (en) * | 2013-03-05 | 2013-06-12 | 西北工业大学 | Pneumatic layout of vertical taking-off and landing aircraft with tilted duct |
| CN107264775A (en) * | 2017-06-16 | 2017-10-20 | 青岛华创风能有限公司 | Air cavity connects controller |
| CN207045693U (en) * | 2017-06-16 | 2018-02-27 | 青岛华创风能有限公司 | Air cavity connects controller |
| US20190092456A1 (en) * | 2017-09-28 | 2019-03-28 | Airbus Operations Limited | Ducts for laminar flow control systems |
| US20190118923A1 (en) * | 2017-10-20 | 2019-04-25 | Airbus Operations Limited | Apparatus for laminar flow control |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112660416A (en) * | 2020-12-24 | 2021-04-16 | 中国航空工业集团公司西安飞机设计研究所 | Laminar flow control technology verification machine |
| CN115675917A (en) * | 2022-11-15 | 2023-02-03 | 中国空气动力研究与发展中心空天技术研究所 | Mix layer flow control on unmanned aerial vehicle and use getter device |
| CN117818871A (en) * | 2024-03-04 | 2024-04-05 | 中国空气动力研究与发展中心高速空气动力研究所 | Application method of passive mixed laminar flow nacelle |
| CN117818871B (en) * | 2024-03-04 | 2024-05-17 | 中国空气动力研究与发展中心高速空气动力研究所 | Application method of passive mixed laminar flow nacelle |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US11987352B2 (en) | Fluid systems that include a co-flow jet | |
| CN111017192A (en) | Mixed laminar flow wing suitable for double-fuselage layout verification machine | |
| CN206318014U (en) | A kind of trailing edge and the flying wing with it | |
| CN104118557B (en) | Low-Reynolds-number airfoil section with multi-seam synergetic jet flow control and control method | |
| US10625847B2 (en) | Split winglet | |
| US20110260008A1 (en) | Fluid flow control device for an aerofoil | |
| CN105314096A (en) | No-control-surface aircraft with air fed by independent air source | |
| CN105035306A (en) | Jet-propelled flap lift augmentation joined wing system and aircraft thereof | |
| CN104210644A (en) | Efficient fluid dynamic and structural design and integration method to achieve extended hybrid laminar flow control | |
| CN111792022B (en) | Trailing edge airflow control method for inhibiting rotor blade-vortex interference noise | |
| US11858617B2 (en) | Propeller-driven helicopter or airplane | |
| CN106672205A (en) | Large-size variable sweep supersonic aircraft layout | |
| CN103419933A (en) | Vertical take-off and landing aircraft with front wings and rear wings on basis of novel high-lift devices | |
| EP4420976A1 (en) | Aircraft flap | |
| Boermans | Research on sailplane aerodynamics at Delft University of Technology | |
| CN201980037U (en) | Co-flow jet lift-enhancement type land-effect aerocar | |
| CN205186510U (en) | No rudder face aircraft of independent air supply air feed | |
| CN112124561B (en) | Aerodynamic drag reduction structure for wingtip winglet of aircraft and aircraft | |
| Hossain et al. | Enhancement of aerodynamic properties of an airfoil by co flow jet (CFJ) flow | |
| CN103419935A (en) | Vertical take-off and landing aircraft in saucer-shaped arrangement and based on novel high-lift device | |
| CN109823518A (en) | A kind of propeller blade shape | |
| CN101823554A (en) | Loading airplane | |
| CN107187579A (en) | A kind of flight force and moment control method suitable for many aerofoil aeroplane clothes office | |
| CN209241307U (en) | Without rudder face aircraft | |
| CN105775159A (en) | Design method for air-blowing ports with function of suppressing separated flow of wings |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20200417 |
|
| RJ01 | Rejection of invention patent application after publication |