CN104149967A - Low-Reynolds-number airfoil profile with cooperative fluidic control, and control method thereof - Google Patents
Low-Reynolds-number airfoil profile with cooperative fluidic control, and control method thereof Download PDFInfo
- Publication number
- CN104149967A CN104149967A CN201410386429.9A CN201410386429A CN104149967A CN 104149967 A CN104149967 A CN 104149967A CN 201410386429 A CN201410386429 A CN 201410386429A CN 104149967 A CN104149967 A CN 104149967A
- Authority
- CN
- China
- Prior art keywords
- air
- pipeline
- jet
- flow
- aerofoil profile
- 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.)
- Granted
Links
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
- Jet Pumps And Other Pumps (AREA)
Abstract
The invention provides a low-Reynolds-number airfoil profile with cooperative fluidic control, and a control method thereof. The low-Reynolds-number airfoil profile with cooperative fluidic control is characterized in that an air jet port (2) is formed in the front edge of the upper surface of an airfoil profile body (1); an air suction port (3) is formed in the rear edge of the upper surface of the airfoil profile body (1); the air jet port (2) is communicated with the air suction port (3) through an air flow pipeline (5) which is arranged inside the airfoil profile body (1); an air pump (4) which is used for driving air suction and air jet to be carried out simultaneously is mounted in the air flow pipeline (5); moreover, the air jet port (2) and the air suction port (3) are perpendicular to the upper surface of the airfoil profile body (1) respectively. The lift of the airfoil profile is greatly increased, the resistance is obviously reduced, and the stalling characteristic of the airfoil profile is improved, so that the aim of efficiently improving the aerodynamic performance of an aircraft is achieved; in addition, the low-Reynolds-number airfoil profile also has the characteristic of low energy consumption.
Description
Technical field
The invention belongs to fluid control technology field, be specifically related to a kind of low Reynolds number airfoil and control method thereof with collaborative jet vectoring.
Background technology
Wing is the major part that aircraft produces lift, and its section shape is aerofoil profile, and the air dynamic behaviour of aerofoil profile directly affects the resistance that rises of wing.Conventional design means has been difficult to significantly promote the aerodynamic characteristic of aerofoil profile at present, and flow control method can be broken through the restriction of traditional design method, reaches the effect of remarkable lifting aerofoil profile lifting resistance characteristic, thereby obviously improves aircraft performance.
At present, the existing extensive engineering application of passive flow control method.Passive mobile control refers to: by passive flow control apparatus, and as wing fence, the devices such as vortex generator are many and change flowing environment.Its shortcoming is: this kind of control is predefined, when off design point, cannot reach optimal control effect.
Active Flow Control is more flexible, it is advantageous that: can occur at time and the position of needs, by local energy, input, obtain local or overall mobile change, and then aircraft flight performance is significantly improved.Compare with Passive Control mode, active Flow Control has higher efficiency and robustness, has broad application prospects.
For low reynolds number aircraft, as High Altitude UAV, stratospheric airship etc., because the impact of its air dynamic behaviour causes pneumatic efficiency not high.Simultaneously conventionally to take long-time stagnant sky be design objective to this type of aircraft, and be subject to the restriction of energy resource supply, and pneumatic efficiency is low is problem anxious to be resolved.Yet existing still have larger limitation for promoting the active Flow Control method of aerofoil profile aerodynamic characteristic, be difficult to significantly increase lift, significantly improve stalling characteristics, and then improve aircraft performance.
Summary of the invention
The defect existing for prior art, the invention provides a kind of low Reynolds number airfoil and control method thereof with collaborative jet vectoring, for controlling near the dynamics of the fluid of aerofoil profile, reach and significantly increase profile lift, obviously reduce resistance, promote airfoil stall characteristic, thereby realize the efficient object that promotes aircraft aeroperformance simultaneously; In addition, also have advantages of that energy consumption is little.
The technical solution used in the present invention is as follows:
The invention provides a kind of low Reynolds number airfoil with collaborative jet vectoring, in aerofoil profile (1) upper surface leading edge, air nozzle (2) is set, at aerofoil profile (2) upper surface trailing edge, air suctiton inlet (3) is set; Described air nozzle (2) and described air suctiton inlet (3) are communicated with by being arranged at the inner airflow line (5) of described aerofoil profile (1), form blowing suction loop; In described airflow line (5), be provided with for drive the air-breathing and jet air pump carrying out (4) simultaneously; And described air nozzle (2) is all vertical with the upper surface of described aerofoil profile (1) with described air suctiton inlet (3).
Preferably, described air nozzle (2) is arranged at the string of a musical instrument 7.0%～10% position, and described air nozzle (2) is highly 0.8%～1.5% of chord length;
Described air suctiton inlet (3) is arranged at the string of a musical instrument 80%～88% position, and described air suctiton inlet (3) is highly 0.8%～1.5% of chord length.
Preferably, described airflow line (5) comprises anterior pipeline (51), middle part pipeline (52) and rear portion pipeline (53); Described middle part pipeline (52) is for settling the pipeline of described air pump (4), described anterior pipeline (51) is for being positioned at described middle part pipeline (52) pipeline above, and described rear portion pipeline (53) is for being positioned at described middle part pipeline (52) pipeline below;
Described rear portion pipeline (53) is pressed direction from back to front, and its cross section is expanded gradually; Described anterior pipeline (51) is pressed direction from back to front, and shrink gradually in its cross section.
Preferably, described aerofoil profile is applied to fixed wing aircraft, screw propeller or rotor.
The present invention also provides a kind of collaborative jet control method for low Reynolds number airfoil, comprises the following steps:
Air pump (4) drives leading edge jet air-breathing with trailing edge simultaneously, and airfoil surface air-flow is carried out to active Flow Control;
Wherein, the jet process of leading edge is: air nozzle (2) is along the tangential ejection high velocity jet of aerofoil profile (1) upper surface, the high velocity jet spraying is aerofoil profile (1) upper surface fluid Implantation Energy, main flow is accelerated by jet injection, and then accelerate flowing of upper surface fluid, increase lift; In addition, air-flow produces suction in aerofoil profile (1) leading edge surface, and the direction of suction is pointed to External airflow field perpendicular to aerofoil profile (1) surface, and the component that this suction is parallel to flow direction is contrary with flow direction, and contrary with drag direction, and then reduces resistance;
Trailing edge breathing process is: air-flow is tangentially inhaled into rear portion pipeline (53) at the air suctiton inlet (3) of trailing edge along upper surface; Rear portion pipeline (53) streamwise is expanded gradually, air current flow speed is reduced gradually, pressure raises, air-flow is inhaled into air pump, and then, air-flow is again by air pump acting supercharging, the anterior pipeline (51) of flowing through, along with anterior pipeline (51) shrinks gradually, flow velocity increases, and becomes high-speed jet and injects among main flow.
In sum, low Reynolds number airfoil and the control method thereof with collaborative jet vectoring provided by the invention, has the following advantages:
(1) adopt and trailing edge air-breathing active Flow Control mode jet in leading edge simultaneously, reach increase lift, reduce resistance, improve stalling characteristics object;
(2) jet and air-breathingly do not need extra source of the gas, therefore avoided complicated vent line design;
(3) mechanism of airflow circulating utilization can reduce energy resource consumption;
(4) do not need moving-member, easy to implement, can, for the wing of fixed wing aircraft, also can be used for the rotation class lift members such as screw propeller, rotor; Both can, for the landing stage of aircraft, obviously reduce ground run distance; Also can be used for cruising phase, save fuel oil, reduce operating cost.
Accompanying drawing explanation
Fig. 1 is the low Reynolds number airfoil cutaway view with collaborative jet vectoring of the present invention;
Fig. 2 is the aerofoil profile upper surface velocity distribution schematic diagram that uses collaborative jet vectoring;
Fig. 3 is the aerofoil profile upper surface velocity distribution schematic diagram that does not add control;
Fig. 4 is the aerofoil profile upper surface flow field structure schematic diagram that uses collaborative jet vectoring;
Fig. 5 is the aerofoil profile upper surface flow field structure schematic diagram that does not add control.
The specific embodiment
Below in conjunction with accompanying drawing, the present invention is described in detail:
The invention provides a kind of low Reynolds number airfoil with collaborative jet vectoring, as shown in Figure 1, is aerofoil profile cutaway view, in aerofoil profile 1 upper surface leading edge, air nozzle 2 is set, and at aerofoil profile 2 upper surface trailing edges, air suctiton inlet 3 is set; Air nozzle 2 and air suctiton inlet 3 are communicated with by being arranged at the airflow line 5 of aerofoil profile 1 inside, form blowing suction loop; In airflow line 5, be provided with for drive the air-breathing and jet air pump carrying out 4 simultaneously; As a kind of optimal way, air nozzle 2 is arranged at the string of a musical instrument 7.0%～10% position, and air nozzle 2 is highly 0.8%～1.5% of chord length; Air suctiton inlet 3 is arranged at the string of a musical instrument 80%～88% position, and air suctiton inlet 3 is highly 0.8%～1.5% of chord length.Wherein, the string of a musical instrument refers to that aerofoil profile is from putting foremost the line of final endpoint, and its length is chord length.And air nozzle 2 is all vertical with the upper surface of aerofoil profile 1 with air suctiton inlet 3, thereby guarantee that gas is tangentially ejected and sucks along upper surface.
In the present invention, the position of air nozzle and air suctiton inlet fully takes into account the feature around Airfoil Flow.Because air-flow is accelerated in aerofoil profile leading edge, leading edge near zone be air-flow velocity in the highest region of medium velocity, whole flow field, be the region that pressure is minimum, therefore, arrange that air nozzle is conducive to the ejection of gas herein; The gas flow being ejected is through aerofoil profile upper surface, and speed reduces gradually, and near pressure rise trailing edge is conducive to air-breathing carrying out herein.Visible, air nozzle provided by the invention and air suctiton inlet arrangement, can reduce to greatest extent airflow circulating institute energy requirement, reduced the power that air pump consumes, reduce air pump burden, reduce energy resource consumption, by active Flow Control method provided by the invention, can obtain obvious lift-rising drag-reduction effect with lower power.
In addition, the airflow line 5 the present invention relates to comprises anterior pipeline 51, middle part pipeline 52 and rear portion pipeline 53; Middle part pipeline 52 is for settling the pipeline of air pump 4, and anterior pipeline 51 is for being positioned at middle part pipeline 52 pipeline above, and rear portion pipeline 53 is the pipeline below of pipeline 52 in the middle part of being positioned at;
Rear portion pipeline 53 is by direction from back to front, and its cross section is expanded gradually, and air-flow along with pipeline section is expanded gradually, reduces air current flow speed after being inhaled among the pipeline of rear portion by air suctiton inlet gradually, and pressure raises, and enters under pressure air pump; Anterior pipeline 51 is by direction from back to front, and shrink gradually in its cross section, and the air-flow anterior pipeline of flowing through after by air pump acting supercharging, along with pipeline section shrinks gradually.Flow velocity increases, and becomes high-speed jet and is injected among main flow.
The present invention also provides a kind of collaborative jet control method for low Reynolds number airfoil, comprises the following steps:
Air pump 4 drives leading edge jet air-breathing with trailing edge simultaneously, and airfoil surface air-flow is carried out to active Flow Control;
Wherein, the jet process of leading edge is: air nozzle 2 is along the tangential ejection high velocity jet 8 of aerofoil profile 1 upper surface, and the high velocity jet spraying is aerofoil profile 1 upper surface fluid Implantation Energy, and main flow 9 is accelerated by jet injection; The lift of aerofoil profile is proportional to the circular rector around aerofoil profile, and the lift of aerofoil profile depends on aerofoil profile upper and lower surface velocity contrast.Thereby flowing of acceleration upper surface can reach the object that increases lift.Conventional aerofoil profile is to be accelerated upper surface air current flow and then produced lift by the curvature variation of leading edge surface, this accelerating action is very limited, and carry out injection acceleration by high-speed jet, it is very high that upper surface air-flow velocity can reach, and around the circular rector value of aerofoil profile, is that conventional aerofoil profile institute is inaccessiable.Therefore, mode of the present invention can greatly increase the lift of aerofoil profile.
Reducing of the present resistance of acting body on the other hand of jet.As front, jet has accelerated the mainstream speed of surface area, also comprises near the flowing of leading edge.Fast air-flow produces large suction in aerofoil profile leading edge surface, and the direction of suction is pointed to External airflow field perpendicular to surface, and this suction is parallel to the component of flow direction and contrary with flow direction, also contrary with drag direction.The application force of jet ejection is favourable for reducing resistance in addition.By the effect of above-mentioned two aspects, resistance greatly reduces, and control method of the present invention even can overcome aerodynamic drag completely, produces thrust.
Trailing edge breathing process is: air-flow is tangentially inhaled into rear portion pipeline 53 at the air suctiton inlet 3 of trailing edge along upper surface; Pipeline 53 streamwises in rear portion are expanded gradually, and air current flow speed is reduced gradually, and pressure raises, and air-flow is inhaled into air pump, then, air-flow is again by air pump acting supercharging, the anterior pipeline 51 of flowing through, along with anterior pipeline 51 shrinks gradually, flow velocity increases, and becomes high-speed jet and injects among main flow.Air-breathing effect can be accelerated the flowing velocity of airfoil trailing edge equally, makes to flow to keep attachment state, suppresses the generation of separation eddy, has promoted the stalling characteristics of aerofoil profile.Jet and air-breathing synergy can reach the object of remarkable lift-rising drag reduction.
Collaborative jet control method provided by the invention, can change local flow field characteristic, referring to Fig. 2, for using the aerofoil profile upper surface velocity distribution schematic diagram of collaborative jet vectoring, 10 is near velocity distribution air nozzle downstream, and 11 is near velocity distribution air suctiton inlet upstream, can find out, the velocity distribution of upper surface, because accelerating action and the getter action of jet 8 become fuller, suppresses separated ability and strengthens.Referring to Fig. 3, for not adding the aerofoil profile upper surface velocity profile of control, 12 control near the velocity distribution of aerofoil profile leading edge for not adding, and 13 control near the velocity distribution of airfoil trailing edge for not adding, due to the viscous effect of gas and airfoil surface, flowing velocity reduces rapidly along the normal direction of airfoil surface, the mobile gas of low speed suppress separated ability a little less than, when the aerofoil profile angle of attack is larger, easily produce large separation eddy, enter stall condition, lift reduces rapidly, and resistance sharply increases.As shown in Figure 4, for using the aerofoil profile upper surface flow field structure schematic diagram of collaborative jet vectoring; As shown in Figure 5, for not adding the aerofoil profile upper surface flow field structure schematic diagram of control, comparison diagram 4 and Fig. 5, adopt collaborative jet control method of the present invention, is flowing in the state that still remains adhered to upper surface under At High Angle of Attack, postponed the stall of aerofoil profile; And add separated region 14 under the aerofoil profile At High Angle of Attack of control, there are not stall.
Empirical tests, adopts low Reynolds number airfoil and the control method thereof with collaborative jet vectoring provided by the invention, and the lift coefficient of aerofoil profile, maximum lift coefficient, stalling incidence all have remarkable lifting.Wherein the lift coefficient under null alpha can be increased to 70%, and maximum lift coefficient can bring up to approximately 150%, and stalling incidence increases approximately 60%.Meanwhile, it zero rises the angle of attack, and drag coefficient all has remarkable reduction, within the scope of low incidence, even can produce thrust.
To sum up, low Reynolds number airfoil and the control method thereof with collaborative jet vectoring provided by the invention, has the following advantages:
(1) adopt and trailing edge air-breathing active Flow Control mode jet in leading edge simultaneously, reach increase lift, reduce resistance, improve stalling characteristics object;
(2) jet and air-breathingly do not need extra source of the gas, therefore avoided complicated vent line design;
(3) mechanism of airflow circulating utilization can reduce energy resource consumption;
(4) do not need moving-member, easy to implement, can, for the wing of fixed wing aircraft, also can be used for the rotation class lift members such as screw propeller, rotor; Both can, for the landing stage of aircraft, obviously reduce ground run distance; Also can be used for cruising phase, save fuel oil, reduce operating cost.
The above is only the preferred embodiment of the present invention; it should be pointed out that for those skilled in the art, under the premise without departing from the principles of the invention; can also make some improvements and modifications, these improvements and modifications also should be looked protection scope of the present invention.
Claims (5)
1. a low Reynolds number airfoil with collaborative jet vectoring, is characterized in that, in aerofoil profile (1) upper surface leading edge, air nozzle (2) is set, and at aerofoil profile (2) upper surface trailing edge, air suctiton inlet (3) is set; Described air nozzle (2) and described air suctiton inlet (3) are communicated with by being arranged at the inner airflow line (5) of described aerofoil profile (1), form blowing suction loop; In described airflow line (5), be provided with for drive the air-breathing and jet air pump carrying out (4) simultaneously; And described air nozzle (2) is all vertical with the upper surface of described aerofoil profile (1) with described air suctiton inlet (3).
2. the low Reynolds number airfoil with collaborative jet vectoring according to claim 1, is characterized in that, described air nozzle (2) is arranged at the string of a musical instrument 7.0%～10% position, and described air nozzle (2) is highly 0.8%～1.5% of chord length;
Described air suctiton inlet (3) is arranged at the string of a musical instrument 80%～88% position, and described air suctiton inlet (3) is highly 0.8%～1.5% of chord length.
3. the low Reynolds number airfoil with collaborative jet vectoring according to claim 1, is characterized in that, described airflow line (5) comprises anterior pipeline (51), middle part pipeline (52) and rear portion pipeline (53); Described middle part pipeline (52) is for settling the pipeline of described air pump (4), described anterior pipeline (51) is for being positioned at described middle part pipeline (52) pipeline above, and described rear portion pipeline (53) is for being positioned at described middle part pipeline (52) pipeline below;
Described rear portion pipeline (53) is pressed direction from back to front, and its cross section is expanded gradually; Described anterior pipeline (51) is pressed direction from back to front, and shrink gradually in its cross section.
4. the low Reynolds number airfoil with collaborative jet vectoring according to claim 1, is characterized in that, described aerofoil profile is applied to fixed wing aircraft, screw propeller or rotor.
5. for a collaborative jet control method for low Reynolds number airfoil, it is characterized in that, comprise the following steps:
Air pump (4) drives leading edge jet air-breathing with trailing edge simultaneously, and airfoil surface air-flow is carried out to active Flow Control;
Wherein, the jet process of leading edge is: air nozzle (2) is along the tangential ejection high velocity jet of aerofoil profile (1) upper surface, the high velocity jet spraying is aerofoil profile (1) upper surface fluid Implantation Energy, main flow is accelerated by jet injection, and then accelerate flowing of upper surface fluid, increase lift; In addition, air-flow produces suction in aerofoil profile (1) leading edge surface, and the direction of suction is pointed to External airflow field perpendicular to aerofoil profile (1) surface, and the component that this suction is parallel to flow direction is contrary with flow direction, and contrary with drag direction, and then reduces resistance;
Trailing edge breathing process is: air-flow is tangentially inhaled into rear portion pipeline (53) at the air suctiton inlet (3) of trailing edge along upper surface; Rear portion pipeline (53) streamwise is expanded gradually, air current flow speed is reduced gradually, pressure raises, air-flow is inhaled into air pump, and then, air-flow is again by air pump acting supercharging, the anterior pipeline (51) of flowing through, along with anterior pipeline (51) shrinks gradually, flow velocity increases, and becomes high-speed jet and injects among main flow.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410386429.9A CN104149967B (en) | 2014-08-07 | 2014-08-07 | Low-Reynolds-number airfoil profile with cooperative fluidic control, and control method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410386429.9A CN104149967B (en) | 2014-08-07 | 2014-08-07 | Low-Reynolds-number airfoil profile with cooperative fluidic control, and control method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104149967A true CN104149967A (en) | 2014-11-19 |
| CN104149967B CN104149967B (en) | 2015-05-06 |
Family
ID=51875648
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410386429.9A Active CN104149967B (en) | 2014-08-07 | 2014-08-07 | Low-Reynolds-number airfoil profile with cooperative fluidic control, and control method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104149967B (en) |
Cited By (25)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105292441A (en) * | 2015-07-11 | 2016-02-03 | 郝文朴 | Disturbance resistance reduction |
| CN105966615A (en) * | 2016-05-27 | 2016-09-28 | 西北工业大学 | Helicopter rotor dynamic stall active flow control device and method |
| CN106892105A (en) * | 2015-12-21 | 2017-06-27 | 空客直升机 | Its construction be useful in march into the arena flight during acoustics improve and in hovering flight and flight forward performance improvement rotator blade |
| CN107284660A (en) * | 2017-07-07 | 2017-10-24 | 陕西科技大学 | Four bars based on Bernoulli effect are without oar aircraft |
| CN107487436A (en) * | 2016-06-10 | 2017-12-19 | 同向射流有限公司 | Include the fluid system of coflow jet |
| WO2018120155A1 (en) * | 2016-12-30 | 2018-07-05 | 钟书豪 | Aerial vehicle, and flying unit and lifting structure thereof |
| CN108528674A (en) * | 2018-03-09 | 2018-09-14 | 中国电子科技集团公司第三十八研究所 | Near space dirigible and its surface flow field control method |
| CN109083807A (en) * | 2018-07-09 | 2018-12-25 | 上海理工大学 | H-type vertical axis windmill with coaxial jet blade |
| CN109533356A (en) * | 2018-11-21 | 2019-03-29 | 南京航空航天大学 | A kind of shock wave boundary layer interaction controller |
| CN110094293A (en) * | 2019-05-06 | 2019-08-06 | 上海理工大学 | A kind of suction of joint leading edge and the jet-propelled vertical axis windmill of leaf tail |
| US10414490B2 (en) | 2015-12-21 | 2019-09-17 | Airbus Helicopters | Aircraft rotor blade of shape adapted for acoustic improvement during an approach flight and for improving performance in forward flight |
| US10683076B2 (en) | 2017-10-31 | 2020-06-16 | Coflow Jet, LLC | Fluid systems that include a co-flow jet |
| CN111605699A (en) * | 2019-02-26 | 2020-09-01 | 三菱重工业株式会社 | Blade and machine provided with same |
| CN112874757A (en) * | 2021-01-14 | 2021-06-01 | 西北工业大学 | Device for realizing active flow control method of pulse synergistic jet |
| CN112937850A (en) * | 2021-01-14 | 2021-06-11 | 西北工业大学 | Pulse synergistic jet control device and method for remarkably improving aerodynamic characteristics of rotor wing |
| CN112977803A (en) * | 2021-03-12 | 2021-06-18 | 南京航空航天大学 | Deformed flap with enhanced blowing and sucking in coordination with high lift |
| CN113044201A (en) * | 2021-04-29 | 2021-06-29 | 合肥工业大学 | Wing section with active jet structure |
| US11111025B2 (en) | 2018-06-22 | 2021-09-07 | Coflow Jet, LLC | Fluid systems that prevent the formation of ice |
| CN113619772A (en) * | 2021-10-09 | 2021-11-09 | 中国航空研究院 | Jet-type second grade spout circulation control wing section in coordination |
| US11273907B2 (en) | 2016-06-10 | 2022-03-15 | Coflow Jet, LLC | Fluid systems that include a co-flow jet |
| US11293293B2 (en) | 2018-01-22 | 2022-04-05 | Coflow Jet, LLC | Turbomachines that include a casing treatment |
| CN115320827A (en) * | 2022-10-14 | 2022-11-11 | 中国航空工业集团公司沈阳空气动力研究所 | High-lift-drag-ratio airfoil profile with high subsonic speed and low Reynolds number flow |
| CN115571329A (en) * | 2022-12-09 | 2023-01-06 | 中国空气动力研究与发展中心低速空气动力研究所 | Wing structure, flow control method thereof, aircraft and flow control test model |
| CN117227963A (en) * | 2023-11-16 | 2023-12-15 | 西安昱辉千星航空科技有限公司 | Wing structure, aircraft and method of operation |
| US11920617B2 (en) | 2019-07-23 | 2024-03-05 | Coflow Jet, LLC | Fluid systems and methods that address flow separation |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101323371A (en) * | 2008-06-24 | 2008-12-17 | 北京航空航天大学 | Lift augmenter with united jet flow structure on wing flap |
| US20090065631A1 (en) * | 2006-04-28 | 2009-03-12 | University Of Miami | Emissionless silent and ultra-efficient airplane using cfj airfoil |
| US20100127129A1 (en) * | 2004-08-20 | 2010-05-27 | University Of Miami | High performance airfoil with co-flow jet flow control |
| CN201980037U (en) * | 2011-03-21 | 2011-09-21 | 山东大学 | Co-flow jet lift-enhancement type land-effect aerocar |
-
2014
- 2014-08-07 CN CN201410386429.9A patent/CN104149967B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100127129A1 (en) * | 2004-08-20 | 2010-05-27 | University Of Miami | High performance airfoil with co-flow jet flow control |
| US20090065631A1 (en) * | 2006-04-28 | 2009-03-12 | University Of Miami | Emissionless silent and ultra-efficient airplane using cfj airfoil |
| CN101323371A (en) * | 2008-06-24 | 2008-12-17 | 北京航空航天大学 | Lift augmenter with united jet flow structure on wing flap |
| CN201980037U (en) * | 2011-03-21 | 2011-09-21 | 山东大学 | Co-flow jet lift-enhancement type land-effect aerocar |
Cited By (39)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105292441A (en) * | 2015-07-11 | 2016-02-03 | 郝文朴 | Disturbance resistance reduction |
| US10414490B2 (en) | 2015-12-21 | 2019-09-17 | Airbus Helicopters | Aircraft rotor blade of shape adapted for acoustic improvement during an approach flight and for improving performance in forward flight |
| CN106892105A (en) * | 2015-12-21 | 2017-06-27 | 空客直升机 | Its construction be useful in march into the arena flight during acoustics improve and in hovering flight and flight forward performance improvement rotator blade |
| CN106892105B (en) * | 2015-12-21 | 2019-12-13 | 空客直升机 | Aircraft rotor blade with a configuration suitable for acoustic improvement during approach flight and performance improvement during hover flight and forward flight |
| US10220943B2 (en) | 2015-12-21 | 2019-03-05 | Airbus Helicopters | Aircraft rotor blade of shape adapted for acoustic improvement during approach flights and for improving performance in hovering flight and in forward flight |
| CN105966615A (en) * | 2016-05-27 | 2016-09-28 | 西北工业大学 | Helicopter rotor dynamic stall active flow control device and method |
| CN107487436A (en) * | 2016-06-10 | 2017-12-19 | 同向射流有限公司 | Include the fluid system of coflow jet |
| CN107487437A (en) * | 2016-06-10 | 2017-12-19 | 同向射流有限公司 | Include the fluid system of coflow jet |
| CN107487437B (en) * | 2016-06-10 | 2020-07-31 | 同向射流有限公司 | Fluidic system comprising a co-flow jet |
| CN107487436B (en) * | 2016-06-10 | 2020-08-21 | 同向射流有限公司 | Fluidic system comprising a co-flow jet |
| US11273907B2 (en) | 2016-06-10 | 2022-03-15 | Coflow Jet, LLC | Fluid systems that include a co-flow jet |
| WO2018120155A1 (en) * | 2016-12-30 | 2018-07-05 | 钟书豪 | Aerial vehicle, and flying unit and lifting structure thereof |
| CN107284660B (en) * | 2017-07-07 | 2020-04-07 | 陕西科技大学 | Bernoulli effect-based four-bar oar-free aircraft |
| CN107284660A (en) * | 2017-07-07 | 2017-10-24 | 陕西科技大学 | Four bars based on Bernoulli effect are without oar aircraft |
| US10683076B2 (en) | 2017-10-31 | 2020-06-16 | Coflow Jet, LLC | Fluid systems that include a co-flow jet |
| US11485472B2 (en) | 2017-10-31 | 2022-11-01 | Coflow Jet, LLC | Fluid systems that include a co-flow jet |
| US11034430B2 (en) | 2017-10-31 | 2021-06-15 | Coflow Jet, LLC | Fluid systems that include a co-flow jet |
| US10683077B2 (en) | 2017-10-31 | 2020-06-16 | Coflow Jet, LLC | Fluid systems that include a co-flow jet |
| US11987352B2 (en) | 2017-10-31 | 2024-05-21 | Coflow Jet, LLC | Fluid systems that include a co-flow jet |
| US11293293B2 (en) | 2018-01-22 | 2022-04-05 | Coflow Jet, LLC | Turbomachines that include a casing treatment |
| CN108528674A (en) * | 2018-03-09 | 2018-09-14 | 中国电子科技集团公司第三十八研究所 | Near space dirigible and its surface flow field control method |
| US11111025B2 (en) | 2018-06-22 | 2021-09-07 | Coflow Jet, LLC | Fluid systems that prevent the formation of ice |
| CN109083807A (en) * | 2018-07-09 | 2018-12-25 | 上海理工大学 | H-type vertical axis windmill with coaxial jet blade |
| CN109533356A (en) * | 2018-11-21 | 2019-03-29 | 南京航空航天大学 | A kind of shock wave boundary layer interaction controller |
| CN111605699A (en) * | 2019-02-26 | 2020-09-01 | 三菱重工业株式会社 | Blade and machine provided with same |
| CN110094293B (en) * | 2019-05-06 | 2020-07-31 | 上海理工大学 | Vertical axis wind turbine combining front edge suction and blade tail jet |
| CN110094293A (en) * | 2019-05-06 | 2019-08-06 | 上海理工大学 | A kind of suction of joint leading edge and the jet-propelled vertical axis windmill of leaf tail |
| US11920617B2 (en) | 2019-07-23 | 2024-03-05 | Coflow Jet, LLC | Fluid systems and methods that address flow separation |
| CN112874757A (en) * | 2021-01-14 | 2021-06-01 | 西北工业大学 | Device for realizing active flow control method of pulse synergistic jet |
| CN112937850B (en) * | 2021-01-14 | 2022-02-15 | 西北工业大学 | Pulse synergistic jet control device and method for remarkably improving aerodynamic characteristics of rotor wing |
| CN112937850A (en) * | 2021-01-14 | 2021-06-11 | 西北工业大学 | Pulse synergistic jet control device and method for remarkably improving aerodynamic characteristics of rotor wing |
| CN112874757B (en) * | 2021-01-14 | 2022-01-11 | 西北工业大学 | Device for realizing active flow control method of pulse synergistic jet |
| CN112977803A (en) * | 2021-03-12 | 2021-06-18 | 南京航空航天大学 | Deformed flap with enhanced blowing and sucking in coordination with high lift |
| CN113044201A (en) * | 2021-04-29 | 2021-06-29 | 合肥工业大学 | Wing section with active jet structure |
| CN113044201B (en) * | 2021-04-29 | 2023-12-19 | 合肥工业大学 | Airfoil with active jet structure |
| CN113619772A (en) * | 2021-10-09 | 2021-11-09 | 中国航空研究院 | Jet-type second grade spout circulation control wing section in coordination |
| CN115320827A (en) * | 2022-10-14 | 2022-11-11 | 中国航空工业集团公司沈阳空气动力研究所 | High-lift-drag-ratio airfoil profile with high subsonic speed and low Reynolds number flow |
| CN115571329A (en) * | 2022-12-09 | 2023-01-06 | 中国空气动力研究与发展中心低速空气动力研究所 | Wing structure, flow control method thereof, aircraft and flow control test model |
| CN117227963A (en) * | 2023-11-16 | 2023-12-15 | 西安昱辉千星航空科技有限公司 | Wing structure, aircraft and method of operation |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104149967B (en) | 2015-05-06 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104149967B (en) | Low-Reynolds-number airfoil profile with cooperative fluidic control, and control method thereof | |
| CN104118557B (en) | Low-Reynolds-number airfoil section with multi-seam synergetic jet flow control and control method | |
| US11034430B2 (en) | Fluid systems that include a co-flow jet | |
| US7134631B2 (en) | Vorticity cancellation at trailing edge for induced drag elimination | |
| CN104176241B (en) | High-efficiency pneumatic layout structure of synergistic jet for high-altitude propeller | |
| US20090065631A1 (en) | Emissionless silent and ultra-efficient airplane using cfj airfoil | |
| Zha et al. | A novel airfoil circulation augment flow control method using co-flow jet | |
| CN104890858A (en) | Wing structure with active flow control mechanism | |
| CN103879556A (en) | Wide flight envelop morphing aircraft | |
| US20110044796A1 (en) | Fluidfoil tip vortex disruption | |
| CN101885381A (en) | Wing with recesses | |
| CN203428021U (en) | Ducted fan | |
| CN109083807B (en) | H-shaped vertical axis wind turbine with coaxial jet flow blades | |
| CN113942651A (en) | Novel flight control device of SACCON type aircraft | |
| CN203740126U (en) | Morphing aircraft with wide flight envelope | |
| CN205779470U (en) | A kind of blunt trailing edge wind mill airfoil circulation control device | |
| CN112977803B (en) | Deformed flap with enhanced blowing and sucking in coordination with high lift | |
| CN103419935B (en) | Dish-shaped layout vertically taking off and landing flyer based on novel high-lift device | |
| CN111619789B (en) | Blade upper surface airflow control device and method | |
| CN113619772B (en) | Jet-type second grade spout circulation control wing section in coordination | |
| CN202670093U (en) | Autogiro capable of taking off and landing vertically | |
| CN216943525U (en) | Distributed electric ducted flap lift-increasing system with deflection guide vanes | |
| CN206068135U (en) | A kind of subsonic aircraft wing | |
| CN203681861U (en) | Flow control device capable of reducing aerodynamic resistance of airship and improving attitude stability | |
| CN207889978U (en) | A kind of Novel land mapping aerial device |
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 |