CN104816827B - Anti- low induced drag lifting airscrew under a kind of wing tip sweepback - Google Patents
Anti- low induced drag lifting airscrew under a kind of wing tip sweepback Download PDFInfo
- Publication number
- CN104816827B CN104816827B CN201510151522.6A CN201510151522A CN104816827B CN 104816827 B CN104816827 B CN 104816827B CN 201510151522 A CN201510151522 A CN 201510151522A CN 104816827 B CN104816827 B CN 104816827B
- Authority
- CN
- China
- Prior art keywords
- winglet
- rotor
- chord length
- wing
- length
- 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
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
- Toys (AREA)
Abstract
Anti- low induced drag lifting airscrew under a kind of wing tip sweepback, it is characterised in that：Be wing tip away from one end of center of rotation in rotor, increase a winglet, the tangential length of root of winglet is less than the tangential length in main wing tip, and the winglet tip string of a musical instrument less than main wing Plane of rotation be under winglet instead, and inwardly reverse certain angle, the leading-edge sweep of winglet；The present invention proposes low induced drag lifting airscrew anti-under a kind of wing tip sweepback, and it is a kind of brand-new lifting airscrew, wherein main innovative point is wing tip aerodynamic arrangement form.The rotor has significantly low hovering induced drag characteristic, and the hovering efficiency to improving helicopter is very helpful.
Description
Technical field
The present invention is rotor craft rotor pneumatic design, belongs to field of flight vehicle design, in particular to a kind of
Anti- low induced drag lifting airscrew under wing tip sweepback, it is a kind of lifting airscrew for having special wing tip aerodynamic arrangement.
Background technology
Rotor craft, with helicopter and gyroplane as representative, with can VTOL, flexible, speed and efficiency
Higher advantage.This characteristic causes helicopter to be particularly suitable for performing patrol, prison in crowded urban district and field with a varied topography
Depending on etc. task.
The pneumatic design core of rotor craft is rotor.Rotor is as own load is generally large and has periodically fortune
Dynamic the characteristics of, efficiency are low typically compared with Fixed Wing AirVehicle, and this situation is especially apparent in hovering flight.Therefore, rotor sets
Meter is always to improve the hovering efficiency of helicopter as an important design object.
The hovering efficiency of helicopter is improved, a simplest mode is exactly to improve the rotor solidity of helicopter.This side
Case can be realized by increasing rotor chord length or increase rotor blade number.However, this method for high-speed helicopter and
Low-speed helicopter has limitation.For high-speed helicopter, excessive rotor solidity causes rotor wetted area to increase, and rotor disappears
Consumption power rise, flight efficiency decline；For low-speed helicopter, excessive rotor solidity declines rotor rotating speed, to external world
Air-flow sinuous flow disturbance sensitivity increases, and the stationarity of flight declines.Therefore to improve straight by appropriate rotor configuration design
The hovering efficiency of the machine of liter, the design of wherein wing tip is critically important ingredient.
The content of the invention
1. technical problem to be solved
Generally, rotor hovering resistance torque is big, and hovering efficiency is low.This problem cannot be by the simple of rotor
Zoom increases the solution of rotor blade number.In order to solve this problem, the present invention proposes anti-under a kind of wing tip sweepback
Low induced drag lifting airscrew, it is a kind of brand-new lifting airscrew, wherein main innovative point is the pneumatic cloth of wing tip
Office's form (hereinafter referred to as wing tip).The rotor has significantly low hovering induced drag characteristic, the hovering effect to improving helicopter
Rate is very helpful.
2. the technical scheme for adopting
Anti- low induced drag lifting airscrew under a kind of wing tip sweepback, which is main to be characterised by：
1) increase a winglet away from one end (i.e. wing tip) of center of rotation in rotor, the tangential length of root of winglet is little
In the tangential length in main wing tip, and the winglet tip string of a musical instrument is less than main wing Plane of rotation (anti-i.e. under winglet), and inwardly reverses certain
Angle.The leading-edge sweep of winglet.
The shape of winglet and position can be described by following parameter：Little wing root chord length clr, little wingtip chord length clt, small span
Long b, winglet leading edge sweep X, winglet inverted diherdral θ, winglet torsion angleIn the present invention, little wing root chord length clr is about main wing
Wing tip chord length C30.7 to 0.5 times, the ratio about 1.5 to 1 of winglet length b and little wing root chord length clr, winglet leading-edge sweep
Between 40 ° to 60 °, winglet inverted diherdral is more than 20 ° to angle X, and winglet torsion angle is -3 ° to -5 °.All geometric parameters of winglet
In, angle is unrelated with the physical dimension of rotor, and all sizes are proportional to the tip chord length of rotor.
2) part (the basic wing) in rotor in addition to winglet, using double trapezoid plane figure form.The distribution form
Chord change rule is：With blade rotary shaft (propeller hub) as basic point, open up into 0%～40% length, by C1Linear change is to C2；
Open up into 40% to 100% length, by C2Linear change is to C3.Wherein, C2>C1, C2>C3, C1With C3Without particular kind of relationship.Each
The contraction coefficient of trapezoidal wing panel is not more than 2.
3) Changing Pattern of basic wing blade torsion angle γ is：With blade rotary shaft (propeller hub) as basic point, open up to 0%～
In 40% length, by γ1Linear change is to γ2；Open up into 40% to 100% length, by γ2Linear change is to γ3.Wherein, γ1
There is negative twist in root for negative value, i.e. blade to turn；γ2、γ3It is on the occasion of and γ2>γ3.General γ2No more than 5 °, often take 3 °；
γ1Not less than -3 °, -2 ° are often taken.Rotor cross sectional shape (aerofoil profile) selection strategy is to use thicker low camber aerofoil profile in root,
Open up to 40% position and use the moderate aerofoil profile of camber and thickness, taper is thin symmetrical airfoil.Aerofoil profile needs to select according to specific needs
Select.
3. beneficial effect
It is an advantage of the current invention that using the rotor blade of the design, compared with the rotor blade of rectangular planar shape, resistance
Force square can decline up to 12%, and lift only loses 3%, it is believed that no significantly sacrificing.
Description of the drawings
Fig. 1 is the isometric drawing of the present invention；
Fig. 2 is the top view of the present invention；
Fig. 3 is the front view of winglet part of the present invention；
Fig. 4 is the top view of winglet part of the present invention；
Fig. 5 is the direction view of winglet part of the present invention.
In figure, symbol description is as follows：
B, the basic wing；L, winglet；γ1, rotary-wing root section torsion angle；γ2, 40% position torsion angle of rotor；γ3, rotor taper
Torsion angle；C1, rotary-wing root section chord length；C2,40% position chord length of rotor；C3, rotor taper chord length；Φ, winglet torsion angle；It is θ, little
Wing inverted diherdral；B, winglet length；X, winglet leading edge sweep；Clr, little wing root chord length；
Clt, little wingtip chord length.
Specific embodiment
Below in conjunction with accompanying drawing and embodiment, the present invention is described in further detail.See Fig. 1-Fig. 5,
1. in the present invention, the root chord length (C1) of the basic wing is 56mm, and 40% to open up to chord length (C2) be 104mm, tip chord length (C3)
70mm, length 1175mm, rotary-wing root section torsion angle (γ1) for -2 °, 40% opens up to torsion angle (γ2) for 3 °, taper torsion angle
(γ3) for 1 °
2. in the present invention, the root aerofoil profile of the basic wing is NACA 67A236, and it is NACA to open up to 40% to 80% position aerofoil profile
25013, the aerofoil profile outside 80% position is NACA 0008.
3. the winglet in the present invention is located at rotor tip location, as shown in fig. 1；Geometric parameter such as Fig. 4 of description winglet
With shown in Fig. 5.In this example, the length of little wing root chord length clr is main rotor tip chord length (C3) 0.57 times, be 40mm；Winglet
Tip chord length clt is 0.6 times of little wing root chord length, is 24mm；Winglet length b is 1.25 times of little wing root chord length clr, is 50mm.
Winglet angle of sweep X is 44 °, and winglet inverted diherdral θ is 30 °, winglet torsion angleFor -3 °.
Claims (1)
1. low induced drag lifting airscrew anti-under a kind of wing tip sweepback, it is characterised in that：In rotor away from center of rotation
One end is wing tip, increases a winglet, and the tangential length of root of winglet is less than the tangential length in basic wing tip portion, and winglet tip string
Line less than basic wing Plane of rotation be under winglet instead, and inwardly reverse certain angle, the leading-edge sweep of winglet；
The shape of winglet and position are described by following parameter：Little wing root chord length clr, little wingtip chord length clt, winglet length b, winglet
Leading edge sweep X, winglet inverted diherdral θ, winglet torsion angleWherein, thriving point chord length C based on little wing root chord length clr3's
0.7 to 0.5 times, the ratio of winglet length b and little wing root chord length clr is 1.5 to 1, winglet leading edge sweep X 40 ° to 60 ° it
Between, winglet inverted diherdral is more than 20 °, and winglet torsion angle is -3 ° to -5 °；In all parameters of winglet, angle parameter is several with rotor
What size is unrelated, and other parameters are proportional to the tip chord length of rotor；
Part in rotor in addition to winglet is the basic wing, using double trapezoid plane figure form；The chord length of the distribution form becomes
Law is：With blade rotary shaft be propeller hub as basic point, open up into 0%～40% length, by rotary-wing root section chord length C1It is linear to become
Change to 40% position chord length C of rotor2；Open up into 40% to 100% length, by 40% position chord length C of rotor2Linear change is to rotation
Wingtip portion chord length C3, wherein, 40% position chord length C of rotor2More than rotary-wing root section chord length C1, 40% position chord length C of rotor2It is more than
Rotor taper chord length C3, rotary-wing root section chord length C1With rotor taper chord length C3Without particular kind of relationship, the contraction coefficient of each trapezoidal wing panel
No more than 2；
The Changing Pattern of basic wing blade torsion angle γ is：With blade rotary shaft be propeller hub as basic point, open up to 0%～40% length
It is interior, by rotary-wing root section torsion angle γ1Linear change is to 40% position torsion angle γ of rotor2；Open up into 40% to 100% length, by
40% position torsion angle γ of rotor2Linear change is to rotor taper torsion angle γ3；Wherein, rotary-wing root section torsion angle γ1For negative value,
I.e. there is negative twist in root and turn in blade；40% position torsion angle γ of rotor2With rotor taper torsion angle γ3It is on the occasion of and rotor
40% position torsion angle γ2More than rotor taper torsion angle γ3；40% position torsion angle γ of rotor2No more than 5 °；Rotary-wing root section
Torsion angle γ1Not less than -3 °；Rotor cross sectional shape selection strategy is to use thicker low camber aerofoil profile in root, open up to 40%
Using the moderate aerofoil profile of camber and thickness, taper is thin symmetrical airfoil for position.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510151522.6A CN104816827B (en) | 2015-04-01 | 2015-04-01 | Anti- low induced drag lifting airscrew under a kind of wing tip sweepback |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510151522.6A CN104816827B (en) | 2015-04-01 | 2015-04-01 | Anti- low induced drag lifting airscrew under a kind of wing tip sweepback |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104816827A CN104816827A (en) | 2015-08-05 |
| CN104816827B true CN104816827B (en) | 2017-04-05 |
Family
ID=53727359
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510151522.6A Active CN104816827B (en) | 2015-04-01 | 2015-04-01 | Anti- low induced drag lifting airscrew under a kind of wing tip sweepback |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104816827B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105711833B (en) * | 2016-03-08 | 2018-04-10 | 哈尔滨飞机工业集团有限责任公司 | Helicopter main blade |
| CN108163192B (en) * | 2017-12-29 | 2024-05-24 | 重庆驼航科技有限公司 | High-efficient low noise rotor |
| CN208291466U (en) * | 2018-05-25 | 2018-12-28 | 深圳市大疆创新科技有限公司 | Propeller, Power Component and aircraft |
| EP3730403B1 (en) * | 2019-04-26 | 2022-05-04 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | A helicopter with a stabilizer wing |
| CN110525644A (en) * | 2019-07-12 | 2019-12-03 | 天津曙光天成科技有限公司 | Lifting airscrew blade tip structure, the production method of rotor and blade tip |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2689852B1 (en) * | 1992-04-09 | 1994-06-17 | Eurocopter France | BLADE FOR AIRCRAFT TURNING WING, AT THE ARROW END. |
| FR2772715B1 (en) * | 1997-12-22 | 2000-02-11 | Eurocopter France | BLADE FOR A TURNING AIRCRAFT |
| US20050281676A1 (en) * | 2004-06-16 | 2005-12-22 | Egolf Thomas A | Multi-hedral rotary wing |
| US7762785B2 (en) * | 2007-12-10 | 2010-07-27 | Sikorsky Aircraft Corporation | Main rotor blade with integral tip section |
| CN104326082A (en) * | 2014-10-20 | 2015-02-04 | 清华大学 | Helicopter and blade thereof |
| CN204507266U (en) * | 2015-04-01 | 2015-07-29 | 天峋创新（北京）科技有限公司 | Low induced drag lifting airscrew anti-under a kind of wing tip sweepback |
-
2015
- 2015-04-01 CN CN201510151522.6A patent/CN104816827B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN104816827A (en) | 2015-08-05 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104816827B (en) | Anti- low induced drag lifting airscrew under a kind of wing tip sweepback | |
| CN105752314B (en) | A kind of high-altitude low speed Natural Laminar Flow high-lift airfoil | |
| CN104477380B (en) | Blade for a helicopter anti-torque device | |
| CN207826548U (en) | A kind of high-efficient low-noise rotor | |
| US20150217851A1 (en) | Wing configuration | |
| CN108163192B (en) | High-efficient low noise rotor | |
| US20110024552A1 (en) | Anhedral Tip Blades for Tiltrotor Aircraft | |
| US20070262205A1 (en) | Retractable multiple winglet | |
| CN205396538U (en) | Screw and aircraft | |
| CN206243477U (en) | Aircraft and its rotor | |
| CN204507266U (en) | Low induced drag lifting airscrew anti-under a kind of wing tip sweepback | |
| CN104044736A (en) | Rotor blade tip of unmanned helicopter | |
| CN106564588B (en) | Unmanned helicopter blade and unmanned helicopter | |
| CN106741923A (en) | The thickness rotor-blade airfoil of high-lift Low-torque characteristic 7% under the conditions of a kind of full working scope | |
| CN110155318A (en) | It determines the method for the initial leading edge circle of the aerofoil profile of blade and improves blade to increase the method for its negative stalling angle | |
| WO2017146028A1 (en) | Rotor blade, drone, and helicopter | |
| CN112977816B (en) | Rotor craft's paddle and rotor craft | |
| CN206954495U (en) | New type propeller | |
| CN109533314A (en) | A kind of light-duty unmanned helicopter Rotor Aerodynamics Shape | |
| CN113022849B (en) | Propeller and rotary wing aircraft | |
| US20210237862A1 (en) | Rotary-wing aircraft blade airfoil, blade having the blade airfoil, and rotary-wing aircraft including the blade | |
| CN105584625B (en) | A kind of propeller and aircraft | |
| CN211364941U (en) | Rotor craft's paddle and rotor craft | |
| CN107487438A (en) | A kind of high-lift airfoil | |
| CN209972778U (en) | Small-sized propeller |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| EXSB | Decision made by sipo to initiate substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |