CN102271997A - Use of positive pressure inside a flexible wing for blowing off some of the incoming flow through a shaped slit to the upper surface thereof - Google Patents
Use of positive pressure inside a flexible wing for blowing off some of the incoming flow through a shaped slit to the upper surface thereof Download PDFInfo
- Publication number
- CN102271997A CN102271997A CN2009801268560A CN200980126856A CN102271997A CN 102271997 A CN102271997 A CN 102271997A CN 2009801268560 A CN2009801268560 A CN 2009801268560A CN 200980126856 A CN200980126856 A CN 200980126856A CN 102271997 A CN102271997 A CN 102271997A
- Authority
- CN
- China
- Prior art keywords
- wing
- blowing
- positive pressure
- pressure inside
- incoming flow
- 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
- 238000007664 blowing Methods 0.000 title abstract 2
- 230000008676 import Effects 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 238000000034 method Methods 0.000 abstract 1
- 230000006698 induction Effects 0.000 description 6
- 230000000694 effects Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- UJCHIZDEQZMODR-BYPYZUCNSA-N (2r)-2-acetamido-3-sulfanylpropanamide Chemical compound CC(=O)N[C@@H](CS)C(N)=O UJCHIZDEQZMODR-BYPYZUCNSA-N 0.000 description 1
- 101100272852 Clostridium botulinum (strain Langeland / NCTC 10281 / Type F) F gene Proteins 0.000 description 1
- 241001669680 Dormitator maculatus Species 0.000 description 1
- 206010044565 Tremor Diseases 0.000 description 1
- 238000007405 data analysis Methods 0.000 description 1
- 230000000994 depressogenic effect Effects 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000011229 interlayer Substances 0.000 description 1
- 239000010410 layer Substances 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
Images
Classifications
-
- 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
- B64C21/04—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for blowing
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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
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Toys (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention relates to aviation, in particular to heavier-than-air vehicles with a flexible wing and is directed at improving the aerodynamic characteristics of a hollow wing provided with an air intake. The technical result is achieved by using a positive pressure inside of a hollow wing for blowing off some of the incoming flow through a convergent channel to the upper surface of said wing in order to form an additional depression zone thereon. The invention can be implemented without substantially modifying the process of the flexible wing production.
Description
Technical field
The present invention relates to communications and transportation and aviation field, specifically, relate to overweight the aerocraft of air.
Background technology
The structure of at present known aircraft wing is determined by the additonal pressure that the aircraft wing internal cavities forms.Additonal pressure is to form like this: windstream slows down at the air inlet position near the body leading edge, and makes Yan bar system bear pressure.This wing generally comprises the slot that is provided with induction opening, and induction opening is used to reduce the 1ift-drag ratio of wing side.In addition, the hollow structure of wing has strengthened the difficulty of coordinating between wing and the bont, and adjusts the Yan bar system that goes up, and the operation of the profile drag during with increase aircraft Normal Take-Off And Landing will cause aerofoil surface the crack to occur.
In theory, 1ift-drag ratio and lift-rising performance in the time of can strengthening the aircraft Normal Take-Off And Landing to the ingenious control of the boundary layer of aircraft wing and profile drag, thereby reduced the aircraft that has aircraft wing susceptibility for weather condition, increase the speed adjustable range of operation simultaneously, reduced needed lifting surface area.
Such trial was arranged in the past,, controlled the upper edge interlayer of hollow wing promptly by the slot of aerofoil surface.Yet this trial does not only improve the lift-rising performance of wing significantly, and makes its design heavy and complicated more.
Summary of the invention
Technical matters to be solved by this invention is to strengthen the pneumatic property of the mid airway flight device wing that has induction opening.
In order to solve the problems of the technologies described above, technical scheme of the present invention is like this:
A kind of leading edge has the hollow wing of admission port, comprise upper and lower wallboard and rib, be provided with the air pocket that imports the wing cavity above the described wing, described air pocket is imported into wainscot, and forming convergent channel at least one, described convergent channel has the air gate by wing wainscot slot.
As if the convergent channel in the wing cavity has become inferior leading edge, and the air-flow of from then on flowing through has produced unnecessary gravitation, has improved the 1ift-drag ratio of wing thus.In addition, the unnecessary pressure of hollow wing in-to-in part is transformed into the more weak jet-stream wind that the wing wainscot flows through, and this just makes the wing wainscot produce the depression area one time, and this depressed area makes the wing wainscot produce burbling, has increased the angle of attack.
Need not redesign on a large scale the aircraft wing manufacturing technology, just can realize technical scheme of the present invention.
Description of drawings
Fig. 1 is the shape of original wing and top distribution of pressure scheme drawing thereof.
Fig. 2 is wing shapes and the distribution of pressure scheme drawing that has induction opening.
Fig. 3 is wing shapes and the distribution of pressure scheme drawing that has the air pocket of figuration slot.
Fig. 4 has the wing shapes of air pocket of figuration slot and top pressure scheme drawing thereof.
The specific embodiment
The present invention is further illustrated below in conjunction with drawings and Examples.
As shown in Figure 3, a kind of leading edge of the present invention has the hollow wing of admission port, comprise upper and lower wallboard and rib, be provided with the air pocket 1 and the air pocket 2 that import the wing cavity above the described wing, these air pockets form convergent channel at least one, and described convergent channel has the air gate by wing wainscot slot.Rib is divided into front side rib and rear side rib two parts, and every part supports corresponding air pocket respectively, as shown in Figure 4, has increased the radian of wing and the groove crack effect of trembling under air pocket and this two-part synergy effect.
In general, a plurality of grooves that formed by air pocket are arranged on the wing, use hollow wing internal over pressure, with the air inlet wing wainscot that leads, form the secondary depression district in this case by convergent channel.
In order to assess final effect, be necessary to consider to adopt the wing figure of original NACA 4415, and reynolds number Re=2196294, the angle of attack is the distribution of pressure situation on the wing under the 10 degree situations.
The shape of original wing and top distribution of pressure thereof are as shown in Figure 1;
Have the wing shapes of induction opening and distribution of pressure as shown in Figure 2;
Have the wing shapes of air pocket of figuration slot and distribution of pressure as shown in Figure 3;
When the latter half of wing turns to, when being 20 degree angles, have the wing shapes of air pocket of figuration slot and top distribution of pressure situation thereof, as shown in Figure 4 with first half;
Fig. 1,2,3 and 4 pressure gradient equate.
The data analysis of pneumatic property (utilization fluid mechanics software 2.3 versions) shows the following main performance of wing with concrete form:
| The scheme drawing sequence number | Cx | Cy |
| 1 | 0.087371 | 1.151827 |
| 2 | 0.09917 | 1.052378 |
| 3 | 0.08921 | 1.201745 |
| 4 | 0.257864 | 1.908809 |
As our finding, induction opening has weakened the wing performance, and the convergent channel that has a slot has remedied this shortcoming.In addition, when the latter half of wing was crooked, lift will increase considerably significantly.
The enhancing of profile drag is gone up Yan bar (also claiming " bracing cable ") by row after drawing high fast and is formed, and middle ranking is on curve, as shown in Figure 4.
If the structure member that increases wing latter half camber is not provided, to compare with conventional wing, newly-designed difference is that the upper strata spar is divided into former and later two parts, and spar links to each other with rib routinely.
Claims (1)
1. a leading edge has the hollow wing of admission port, comprise upper and lower wallboard and rib, it is characterized in that, be provided with the air pocket that imports the wing cavity above the described wing, described air pocket is imported into wainscot, and forming convergent channel at least one, described convergent channel has the air gate by wing wainscot slot.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2008128067/11A RU2389644C2 (en) | 2008-07-11 | 2008-07-11 | Hollow soft wing with air intake at tip and shaped slot on upper surface |
| RU2008128067 | 2008-07-11 | ||
| PCT/RU2009/000335 WO2010005341A2 (en) | 2008-07-11 | 2009-07-03 | Use of positive pressure inside a flexible wing for blowing off some of the incoming flow through a shaped slit to the upper surface thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102271997A true CN102271997A (en) | 2011-12-07 |
Family
ID=41507614
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009801268560A Pending CN102271997A (en) | 2008-07-11 | 2009-07-03 | Use of positive pressure inside a flexible wing for blowing off some of the incoming flow through a shaped slit to the upper surface thereof |
Country Status (5)
| Country | Link |
|---|---|
| CN (1) | CN102271997A (en) |
| IL (1) | IL210329A0 (en) |
| RU (1) | RU2389644C2 (en) |
| UA (1) | UA98558C2 (en) |
| WO (1) | WO2010005341A2 (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2444462C1 (en) * | 2010-06-28 | 2012-03-10 | Юрий Витальевич Швед | Soft two-skin wing with spreading stiffener |
| RU2508228C1 (en) * | 2012-12-11 | 2014-02-27 | Алексей Николаевич Пеков | Method of aircraft airfoil boundary layer control and device for realising it |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4191349A (en) * | 1978-03-24 | 1980-03-04 | Cabinet Lavoix | Parachute having an improved multi-cell canopy |
| FR2633248B1 (en) * | 1988-06-28 | 1990-10-12 | Degraces Jacques | WATERPROOF WELL DEVICE FOR PARACHUT WINGS |
| CN1950254A (en) * | 2004-05-13 | 2007-04-18 | 空中客车德国有限公司 | Aircraft component, in particular a wing |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU1782869C (en) * | 1989-05-29 | 1992-12-23 | Нижегородское авиационное производственное объединение им.С.Орджоникидзе | Paraglider |
-
2008
- 2008-07-11 RU RU2008128067/11A patent/RU2389644C2/en not_active IP Right Cessation
-
2009
- 2009-07-03 UA UAA201015567A patent/UA98558C2/en unknown
- 2009-07-03 CN CN2009801268560A patent/CN102271997A/en active Pending
- 2009-07-03 WO PCT/RU2009/000335 patent/WO2010005341A2/en active Application Filing
-
2010
- 2010-12-28 IL IL210329A patent/IL210329A0/en unknown
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4191349A (en) * | 1978-03-24 | 1980-03-04 | Cabinet Lavoix | Parachute having an improved multi-cell canopy |
| FR2633248B1 (en) * | 1988-06-28 | 1990-10-12 | Degraces Jacques | WATERPROOF WELL DEVICE FOR PARACHUT WINGS |
| CN1950254A (en) * | 2004-05-13 | 2007-04-18 | 空中客车德国有限公司 | Aircraft component, in particular a wing |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2010005341A3 (en) | 2010-03-04 |
| WO2010005341A2 (en) | 2010-01-14 |
| RU2389644C2 (en) | 2010-05-20 |
| UA98558C2 (en) | 2012-05-25 |
| IL210329A0 (en) | 2011-03-31 |
| RU2008128067A (en) | 2010-01-20 |
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