CN104386240A - Total-lifting wing of airplane - Google Patents
Total-lifting wing of airplane Download PDFInfo
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- CN104386240A CN104386240A CN201410642438.XA CN201410642438A CN104386240A CN 104386240 A CN104386240 A CN 104386240A CN 201410642438 A CN201410642438 A CN 201410642438A CN 104386240 A CN104386240 A CN 104386240A
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- wing
- top airfoil
- lower aerofoil
- wing surface
- total
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Abstract
The invention relates to a total-lifting wing of an airplane. The total-lifting wing comprises an upper wing surface and a lower wing surface, wherein the upper wing surface and the lower wing surface are formed by curved surfaces which go down from the front edge to the rear edge. The total-lifting wing of the airplane has a simple structure, the upper wing surface can generate vertical airflows and enable the vertical airflows to flow downwards under the action of the airflows, the pressure intensity of the wing surface is reduced, and ascending lifting force is generated on the curved surface; the lower wing surface can enable the forward airflows to be reflected in a behind-below direction, and the curved surface has reverse ascending lifting force, thus, the upper wing surface and the lower wing surface can form consistent ascending lifting force, the sum of the ascending lifting forces of the two wing surfaces is more than that of the single wing surface, and the wing efficacy can be improved.
Description
Technical field
The invention belongs to aircraft manufacturing technical field, particularly a kind of aircraft total lift wing.
Background technology
Wing is one of important composition parts of aircraft, and its main effect produces lift, to support that aircraft flies aloft.At present, various aircraft produces the principle of lift, is under zero degrees elevation, there is provided lift by current difference principle, and survey according to existing wind-tunnel, the leading portion of wing top airfoil contains positive pressure district, do not provide whole negative pressure district in this part, thus there is raising force and down-force and to cancel each other situation.Wing is in top airfoil part, and the current difference in utilization between lower aerofoil, produces difference of pressure, produce to raising force, between the vertex that the part of raising force mainly concentrates on top airfoil to airfoil trailing edge.Such aerofoil surface structure makes lower aerofoil not have lift to produce, and usefulness reduces.
Summary of the invention
The object of the present invention is to provide a kind of aircraft total lift wing that can improve wing usefulness, to solve the problem.
In order to achieve the above object, technical scheme of the present invention is achieved in that
A kind of aircraft total lift wing, comprises top airfoil and lower aerofoil, and described top airfoil and lower aerofoil are formed by the curved surface declined from leading edge to trailing edge.
The main plane of top airfoil is decline curved surface, and curved surface is that monotonically decreasing function is formed, and namely from the left side to the right, curved surface height in the vertical direction successively declines, general without flex point.
The main plane of lower aerofoil is decline curved surface, and curved surface is that monotonically decreasing function is formed, and namely from the left side to the right, curved surface height in the vertical direction successively declines, general without flex point.
The lower aerofoil high order end transition face crossing with top airfoil high order end is traditionally arranged to be left convex surface.
Lower aerofoil is traditionally arranged to be convex outward with top airfoil at transition face crossing bottom.
Compared with prior art, the advantage of the embodiment of the present invention is: structure of the present invention is simple, and top airfoil is under airflow function, and the Vertical dimension air-flow of formation flows downward, and aerofoil pressure declines, thus at this curved surface generation lift upwards; Front air-flow reflects to the back lower place by lower aerofoil, makes this curved surface obtain reverse lift upwards.So just make top airfoil and lower aerofoil form consistent with raising force, the two is greater than to raising force sum the lift that one side produces, thus improves the usefulness of wing.
Accompanying drawing explanation
Fig. 1 is aircraft wing angle of attack schematic cross-section when being zero degree;
Fig. 2 is that Fig. 1 cuts Airfoil Sections schematic diagram after CK line left-half;
Fig. 3 is section structure schematic diagram of the present invention.
In Fig. 1 ~ Fig. 3,1, top airfoil; 2, lower aerofoil; 201, left convex surface; 202, convex outward;
In figure, direction shown in arrow is air flow line.
Detailed description of the invention
Carry out clear, complete description below with reference to accompanying drawing to the technical scheme of various embodiments of the present invention, obviously, described embodiment is only a part of embodiment of the present invention, instead of whole embodiments.Based on the embodiment in the present invention, other embodiments all that those of ordinary skill in the art obtain under the prerequisite not making creative work, all belong to the scope that the present invention protects.
Embodiment
Suppose that the aircraft wing angle of attack is zero degree, as shown in Figure 1, wing vertex C, crosses C point and makes plumb bob vertical friendship horizon MN in K wing principal section figure.By the new wing profile figure that a left side of CK half is formed, after cutting, remaining right half part, forms the cross section of new aerofoil surface, as shown in Figure 2.Top airfoil lift formula is:
F＝1/2ρCSv
2
In formula:
F is the lift that top airfoil is subject to;
ρ is density of air;
C is coefficient;
S is area;
V is speed.
Or
F=K × (under P on-P) × S F is the raising force that top airfoil is subject to;
K is coefficient;
Under P: be the pressure of lower aerofoil;
P is upper: be the pressure of top airfoil;
S: be top airfoil area.
Then on the vertical line of C point, E place, below work one straight line a little, with the left side of wing tail water flat spot N, horizon intersects at D, cut ED line lower left side, the left convex surface of C and E is connected upper lower aerofoil, then D and N convex outward is connected upper lower aerofoil, finally by constant for the height of figure each point Vertical dimension, only in level to being horizontally extended for MN equably.Just obtain a kind of wing new as shown in Figure 3:
A kind of aircraft total lift wing, comprises top airfoil 1 and lower aerofoil 2, and top airfoil 1 and lower aerofoil 2 are formed by the curved surface declined from leading edge to trailing edge.
The lift formula in vertical direction of ED line:
F＝K×M×V×sinα
In formula:
F is lift;
K is coefficient;
M is air quality;
V is air velocity;
α is straight line and level inclination.
When line style is different, lift needs to revise.
Thus airfoil lift is made up of two formula sums, produces lift than single top airfoil, have more lower aerofoil.
In the present invention, when top airfoil is certain, the angle angle of lower aerofoil and horizontal surface is larger, and the raising force of generation is larger.
Preferably, lower aerofoil 2 and top airfoil 1, crossing bottom, adopt suitable convex outward, and air-flow, under the reflectivity effect of lower aerofoil 2, adds K value, and the raising force that lower aerofoil 2 is produced increases.
Preferably, lower aerofoil 2 is crossing in elongated surfaces bottom with top airfoil 1 in elongated surfaces bottom, is namely having certain thickness bottom between top airfoil 1 and lower aerofoil, is adding the intensity of wing.
Preferably, lower aerofoil 2 is arcwall face, and the center of circle of arcwall face is positioned at outside wing, adds the reflectivity of air-flow, too increases the angle between lower aerofoil and horizontal surface simultaneously.
Preferably, lower aerofoil 2 is crossing in elongated surfaces topmost with top airfoil 1 in elongated surfaces topmost, namely has certain thickness topmost between top airfoil 1 and lower aerofoil, adds the intensity of wing.
Preferably, lower aerofoil 2 is set to left convex surface 201 with the phase cross surface of top airfoil 1 topmost, and now while the intensity that can increase wing-body, flow velocity reduces minimum.
Structure of the present invention is simple, and top airfoil 1 is under airflow function, and the Vertical dimension air-flow of formation flows downward, and aerofoil pressure declines, thus at this curved surface generation lift upwards; Front air-flow reflects to the back lower place by lower aerofoil 2, makes this curved surface obtain reverse lift upwards.So just make top airfoil and lower aerofoil form consistent with raising force, the two is greater than to raising force sum the lift that one side produces, thus improves the usefulness of wing.
The above, it is only preferred embodiment of the present invention, not any pro forma restriction is done to the present invention, any those skilled in the art, do not departing within the scope of technical solution of the present invention, make a little change when the technology contents of above-mentioned announcement can be utilized or be modified to the Equivalent embodiments of equivalent variations, in every case be the content not departing from technical solution of the present invention, the any simple modification done above embodiment according to technical spirit of the present invention, equivalent variations and modification, all still belong in the scope of technical solution of the present invention.
Claims (5)
1. an aircraft total lift wing, comprises top airfoil (1) and lower aerofoil (2), it is characterized in that, described top airfoil (1) and lower aerofoil (2) are formed by the curved surface declined from leading edge to trailing edge.
2. aircraft total lift wing according to claim 1, is characterized in that, described top airfoil (1) is that the decline curved surface from leading edge to trailing edge is formed.
3. aircraft total lift wing according to claim 1, is characterized in that, described lower aerofoil (2) is that the decline curved surface from leading edge to trailing edge is formed.
4. aircraft total lift wing according to claim 1, is characterized in that, described top airfoil (1) and lower aerofoil (2), crossing topmost, intersect and can intersect with fillet surface.
5. aircraft total lift wing according to claim 1, is characterized in that, described top airfoil (1) and lower aerofoil (2), crossing bottom, intersect and can intersect with fillet surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410642438.XA CN104386240A (en) | 2014-11-14 | 2014-11-14 | Total-lifting wing of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410642438.XA CN104386240A (en) | 2014-11-14 | 2014-11-14 | Total-lifting wing of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104386240A true CN104386240A (en) | 2015-03-04 |
Family
ID=52604228
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410642438.XA Pending CN104386240A (en) | 2014-11-14 | 2014-11-14 | Total-lifting wing of airplane |
Country Status (1)
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| CN (1) | CN104386240A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3640780A1 (en) * | 1986-11-28 | 1988-10-20 | Blauer Miklos Zoltan Dipl Masc | Ideal aerofoil section for the wings (vanes) of fluid-dynamic installations |
| KR20000001523A (en) * | 1998-06-12 | 2000-01-15 | 데이비드 에스 에이치 황 | Wing structure and manufacturing method thereof |
| EP1468908A1 (en) * | 2003-04-16 | 2004-10-20 | Manuel Munoz Saiz | Aerodynamic profile |
| US20070246611A1 (en) * | 2006-04-19 | 2007-10-25 | Anadish Kumar Pal | Triboelectric treatment of wing and blade surfaces to reduce wake and BVI/HSS noise |
| CN101481014A (en) * | 2009-02-14 | 2009-07-15 | 刘华友 | Airfoil |
| CN204264443U (en) * | 2014-11-14 | 2015-04-15 | 鄢光明 | Aircraft total lift wing |
-
2014
- 2014-11-14 CN CN201410642438.XA patent/CN104386240A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3640780A1 (en) * | 1986-11-28 | 1988-10-20 | Blauer Miklos Zoltan Dipl Masc | Ideal aerofoil section for the wings (vanes) of fluid-dynamic installations |
| KR20000001523A (en) * | 1998-06-12 | 2000-01-15 | 데이비드 에스 에이치 황 | Wing structure and manufacturing method thereof |
| EP1468908A1 (en) * | 2003-04-16 | 2004-10-20 | Manuel Munoz Saiz | Aerodynamic profile |
| US20070246611A1 (en) * | 2006-04-19 | 2007-10-25 | Anadish Kumar Pal | Triboelectric treatment of wing and blade surfaces to reduce wake and BVI/HSS noise |
| CN101481014A (en) * | 2009-02-14 | 2009-07-15 | 刘华友 | Airfoil |
| CN204264443U (en) * | 2014-11-14 | 2015-04-15 | 鄢光明 | Aircraft total lift wing |
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| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20150304 |
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| RJ01 | Rejection of invention patent application after publication |