CN100400375C - Aerofoil with blunt tail edge - Google Patents
Aerofoil with blunt tail edge Download PDFInfo
- Publication number
- CN100400375C CN100400375C CNB2006100464779A CN200610046477A CN100400375C CN 100400375 C CN100400375 C CN 100400375C CN B2006100464779 A CNB2006100464779 A CN B2006100464779A CN 200610046477 A CN200610046477 A CN 200610046477A CN 100400375 C CN100400375 C CN 100400375C
- Authority
- CN
- China
- Prior art keywords
- edge
- wing profile
- tail edge
- aerofoil profile
- aerofoil
- 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.)
- Expired - Fee Related
Links
Images
Abstract
The present invention relates to a wing profile with a blunt tail edge. The present invention keeps the shape of the suction surface of a traditional wing profile with a pointed tail edge, and enlarges the thickness of the tail edge of the wing profile to 0.5-3.0 % of the chord length of the wing profile. A point on the pressure surface of the traditional wing profile with a pointed tail edge is smoothly connected with the blunt tail edge to form a new pressure surface of the wing profile with a blunt tail edge. Under the same conditions, the aerodynamic characteristic of the wing profile is obviously enhanced. The present invention has the advantages that the lift coefficient and the lift/drag ratio of the wing profile are obviously enhanced; the stalling angle of the wing profile is considerably deferred; because the wing profile with a blunt tail edge of the present invention enlarges the tail edge regions and the wing profile thickness of modification parts, the strength and the rigidity of wings or paddles are enhanced. The present invention has the advantages of simple implement and low cost.
Description
Technical field:
The present invention relates to a kind of aerofoil with blunt tail edge, exactly belong to Airfoil Design, manufacturing and application.
Background technology:
Present aerofoil profile, for example NACA series, brother's Dettingen (
) series etc. all is fine stern edge aerofoil profile, they all have goodish aeroperformance, especially for subsonic velocity or low speed aerofoil profile.This situation has been broken in the appearance of Ge Ni (Gurney) wing flap, and it has produced significant effects to airfoil performance, has obtained some good results under certain condition.So-called gurney flap is promptly opened up to the tablet that installs a suitable height vertical with its string of a musical instrument additional along wing or blade at the aerofoil profile trailing edge.Studies show that: gurney flap has changed the distribution of pressure on aerofoil profile suction surface and the acting face effectively, increase effective camber of aerofoil profile, thereby increased the circular rector of fluid winding flow aerofoil profile, obviously improved the lift coefficient of aerofoil profile, and highly suitably the time, can make its liter (power) resistance (power) than improving a lot.But, gurney flap with aerofoil profile be connected and structural strength on also can bring new problem.In fact, gurney flap has obviously hindered the air current flow on the acting face, and therefore when lift increased, its resistance also had sizable increase.In order to remedy this defective of gurney flap, the present invention is transformed into fine stern edge aerofoil profile the aerofoil with blunt tail edge of certain trailing edge thickness, subsonic velocity or low speed aerofoil profile aeroperformance are greatly improved, and to stride, supersonic profile also can apply and improve its performance.Have U.S. Pat 4858852 to propose a kind of " Divergent trailing-edge airfoil " before this, still the trailing edge of this aerofoil profile can only be dispersed, and only is applicable to transonic Airfoil.
Summary of the invention:
The objective of the invention is to adopt the method for the simplest and easy enforcement to improve traditional fine stern edge airfoil aerodynamic performances, and needn't carry out complexity and expensive Airfoil Design process.Suction surface to traditional aerofoil profile remains unchanged, to keep the good aeroperformance of original aerofoil profile, and the acting face trailing edge that will treat improved fine stern edge aerofoil profile (being the aerofoil profile prototype) adds " gurney flap " of suitable height (0.5%-3.0% aerofoil profile chord length), (60%-99% aerofoil profile chord length) beginning is connected with the free edge of wing flap with smooth curve from certain chord length position with acting face again, thereby constitute new aerofoil with blunt tail edge, the trailing edge angle of this aerofoil profile can be that bear or positive, (75 ° to+60 °) promptly disperse or the convergence.
Advantage of the present invention is: the lift coefficient and the 1ift-drag ratio of aerofoil profile obviously improve, and the stalling incidence of aerofoil profile is postponed greatly; Because aerofoil with blunt tail edge of the present invention has strengthened the trailing edge zone and revised the profile thickness at position, thereby the intensity and the rigidity of wing or blade have been increased; Implement simply, cost is low.
Description of drawings
Fig. 1 is that traditional fine stern edge aerofoil profile and aerofoil with blunt tail edge of the present invention compare scheme drawing.
Fig. 2 is the local enlarged diagram of Fig. 1.
Fig. 3 is the lift coefficient comparison curve of traditional fine stern edge aerofoil profile and aerofoil with blunt tail edge of the present invention.
Fig. 4 is aerofoil with blunt tail edge of the present invention improves percentum with respect to the 1ift-drag ratio of traditional fine stern edge aerofoil profile a curve.
The specific embodiment
With reference to Fig. 1, traditional fine stern edge aerofoil profile is made up of leading edge 21, trailing edge 22, suction surface 20 and acting face 24, and shown in the dotted line among Fig. 1,23 is its string of a musical instrument, and the length of the string of a musical instrument is the chord length of aerofoil profile; And the suction surface 30 of aerofoil profile of the present invention is identical with the suction surface 20 of traditional fine stern edge aerofoil profile, and form by leading edge 21, blunt trailing edge 32, suction surface 30 and acting face 34, shown in the solid line among Fig. 1,23 still is its string of a musical instrument, the E point is the common ground of the acting face 34 of traditional fine stern edge aerofoil profile acting face 24 and aerofoil profile of the present invention, the E point can change between the 60%-99% chord length apart from the chordwise distance of leading edge 21, and at E point place, the slope of left and right sides acting face is identical.
With reference to Fig. 2, be the local enlarged diagram of the afterbody of the traditional fine stern edge aerofoil profile of Fig. 1 and aerofoil profile of the present invention.The E point is the common ground of the acting face 34 of traditional fine stern edge aerofoil profile 24 and aerofoil profile of the present invention, before the E point, the acting face 24 of fine stern edge aerofoil profile is common with the acting face 34 of aerofoil profile of the present invention, the E point can change between the 60%-99% chord length apart from the chordwise distance of leading edge 21, at E point place, the slope of left and right sides acting face is identical; 32 is the blunt trailing edge of aerofoil with blunt tail edge of the present invention, and its thickness can be 0.5%-3.0% aerofoil profile chord length; 33 is the trailing edge angle of aerofoil with blunt tail edge of the present invention, (promptly at the trailing edge place, the angle between the tangent line of the tangent line of aerofoil profile suction surface 30 and acting face 34) this trailing edge angle can be that bear or positive, from-75 ° to+60 °, promptly can disperse, also can restrain.
With reference to Fig. 3,, be Re=6.7 * 10 at Reynolds number for the thickness at trailing edge 32 is that 2% aerofoil profile chord length, E point are positioned at when aerofoil profile leading edge 21 is 90% chord length
5Under the condition, the lift coefficient of traditional fine stern edge aerofoil profile and aerofoil profile of the present invention is with the comparison curve of change in angle of attack, and the lift efficiency of visible aerofoil with blunt tail edge of the present invention is greatly improved, and its stalling incidence has also been postponed greatly.
With reference to Fig. 4, for the thickness at trailing edge 32 is that 2% chord length, E point are positioned at when aerofoil profile leading edge 21 is 90% chord length, and be 2 ° at the angle of attack, Reynolds number is Re=6.7 * 10
5Under the condition, the liter of traditional fine stern edge aerofoil profile and aerofoil profile of the present invention (power) resistance (power) is than the curve that improves percentum, and the aerodynamic characteristics of visible aerofoil with blunt tail edge of the present invention is greatly improved.
Although the present invention is with regard to subsonic velocity or low speed aerofoil profile and propose, its design philosophy is equally applicable to stride, supersonic aerofoil profile.
Claims (2)
1. aerofoil with blunt tail edge, form by leading edge (21), suction surface (30), acting face (34) and blunt trailing edge (32), it is before identical with traditional fine stern edge aerofoil profile acting face (24) that described acting face (34) is gone up the E point, suction surface (30) is identical with the suction surface (20) of traditional fine stern edge aerofoil profile, it is characterized in that: the trailing edge of described aerofoil profile is that certain thickness blunt trailing edge (32) is arranged, its trailing edge thickness is between the aerofoil profile chord length of 0.5%-3.0%, and restrain at the trailing edge angle (33) of aerofoil with blunt tail edge.
2. aerofoil with blunt tail edge according to claim 1 is characterized in that: begin to connect with smooth curve to blunt trailing edge (32) from the E point, the E point can change between the aerofoil profile chord length of 60%-99% apart from the chordwise distance of leading edge (21); At E point place, the slope of left and right sides acting face is identical.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2006100464779A CN100400375C (en) | 2006-04-29 | 2006-04-29 | Aerofoil with blunt tail edge |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2006100464779A CN100400375C (en) | 2006-04-29 | 2006-04-29 | Aerofoil with blunt tail edge |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1843844A CN1843844A (en) | 2006-10-11 |
| CN100400375C true CN100400375C (en) | 2008-07-09 |
Family
ID=37062818
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB2006100464779A Expired - Fee Related CN100400375C (en) | 2006-04-29 | 2006-04-29 | Aerofoil with blunt tail edge |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN100400375C (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102052266B (en) * | 2010-12-29 | 2013-11-06 | 南京航空航天大学 | After-load blunt trailing edge wing profile designed based on sharp trailing edge wing profile |
| CN105752315B (en) * | 2016-04-20 | 2017-03-29 | 西北工业大学 | Take into account the new ideas aerofoil profile transonic speed with hypersonic aeroperformance |
| CN107640312A (en) * | 2017-08-11 | 2018-01-30 | 南京航空航天大学 | Reduce the trailing edge devices of wave resistance in a kind of transonic speed laminar flow airfoil design |
| FR3077803B1 (en) * | 2018-02-15 | 2020-07-31 | Airbus Helicopters | METHOD OF IMPROVING A BLADE IN ORDER TO INCREASE ITS NEGATIVE INCIDENCE OF STALL |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4519746A (en) * | 1981-07-24 | 1985-05-28 | United Technologies Corporation | Airfoil blade |
| US4858852A (en) * | 1987-06-01 | 1989-08-22 | Mcdonnell Douglas Corporation | Divergent trailing-edge airfoil |
| US6592072B1 (en) * | 2002-06-20 | 2003-07-15 | The Boeing Company | Spanwise tailoring of divergent trailing edge wings |
| US6607164B2 (en) * | 2001-10-22 | 2003-08-19 | Toyota Motor Sales, U.S.A., Inc. | Wing airfoil |
-
2006
- 2006-04-29 CN CNB2006100464779A patent/CN100400375C/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4519746A (en) * | 1981-07-24 | 1985-05-28 | United Technologies Corporation | Airfoil blade |
| US4858852A (en) * | 1987-06-01 | 1989-08-22 | Mcdonnell Douglas Corporation | Divergent trailing-edge airfoil |
| US6607164B2 (en) * | 2001-10-22 | 2003-08-19 | Toyota Motor Sales, U.S.A., Inc. | Wing airfoil |
| US6592072B1 (en) * | 2002-06-20 | 2003-07-15 | The Boeing Company | Spanwise tailoring of divergent trailing edge wings |
Also Published As
| Publication number | Publication date |
|---|---|
| CN1843844A (en) | 2006-10-11 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101405504B (en) | Wind turbine rotor blade | |
| CN102414440B (en) | Wind turbine providing increased power output | |
| US20150217851A1 (en) | Wing configuration | |
| CN101813070B (en) | Vane airfoil profile of low power wind driven generator | |
| CN104118556B (en) | Special spoon-shaped wing section with ultra-low Reynolds number, high lift-drag ratio and low speed | |
| CN202642093U (en) | Propeller and aircraft with propeller | |
| CN207826548U (en) | A kind of high-efficient low-noise rotor | |
| US20150361951A1 (en) | Pressure side stall strip for wind turbine blade | |
| CN109229364B (en) | Class ellipse aerofoil profile applied to high-speed helicopter rotor reversed flow region | |
| US8936435B2 (en) | System and method for root loss reduction in wind turbine blades | |
| CN108163192A (en) | A kind of high-efficient low-noise rotor | |
| CN111120401A (en) | Multi-wing centrifugal ventilator blade design method based on NACA wing profile | |
| CN100400375C (en) | Aerofoil with blunt tail edge | |
| CN115320827B (en) | High-lift-drag-ratio airfoil profile with high subsonic speed and low Reynolds number flow | |
| CN208593491U (en) | A kind of blade leading edge boring device reducing paddle vortex interaction effect | |
| CN107878728A (en) | Wing structure and aircraft | |
| CN202953169U (en) | Novel spoon-shaped blended winglet for civil airplane | |
| CN109989876B (en) | Blade and wind generating set comprising same | |
| CN2900356Y (en) | Blunt tail edge wing | |
| CN104097763B (en) | A kind of special-shaped Airfoil | |
| Manerikar et al. | Horizontal axis wind turbines passive flow control methods: a review | |
| CN207064139U (en) | Wind generator set blade | |
| CN214499309U (en) | Airfoil profile applicable to wind driven generator blade under low Reynolds number working condition | |
| CN114021265A (en) | Airplane wing section based on logarithmic spiral | |
| CN104696158B (en) | A kind of vertical axis aerogenerator group lift-type vane airfoil profile |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20080709 Termination date: 20110429 |