CN104149967B - 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
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- CN104149967B CN104149967B CN201410386429.9A CN201410386429A CN104149967B CN 104149967 B CN104149967 B CN 104149967B CN 201410386429 A CN201410386429 A CN 201410386429A CN 104149967 B CN104149967 B CN 104149967B
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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 the control method thereof with collaborative jet vectoring.
Background technology
Wing is that aircraft produces the major part of lift, its section shape and aerofoil profile, and what the air dynamic behaviour of aerofoil profile directly affected wing rises resistance.The design means of current routine has been difficult to the aerodynamic characteristic significantly promoting aerofoil profile, and flow control method then can break through the restriction of traditional design method, reaches the effect significantly promoting aerofoil profile lifting resistance characteristic, thus obviously improves aircraft performance.
At present, passive flow control method has extensive engineer applied.Passive flowing control refers to: by passive flow control apparatus, as wing fence, the devices such as vortex generator, many and change flowing environment.Its shortcoming is: this kind of control presets, and when off design point, then cannot reach optimal control effect.
Active Flow Control is then more flexible, it is advantageous that: can occur in the time needed and position, and inputted by local energy, the flowing obtaining local or the overall situation changes, and then aircraft flight performance is significantly improved.Compared 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., the impact due to its air dynamic behaviour causes pneumatic efficiency not high.Simultaneously this type of aircraft usually with long-time stagnant sky for design objective, and by the restriction of energy resource supply, pneumatic efficiency is low is problem anxious to be resolved.But the existing active Flow Control method for promoting aerofoil profile aerodynamic characteristic, still having larger limitation, being difficult to significantly increase lift, significantly improve stalling characteristics, and then improving aircraft performance.
Summary of the invention
For the defect that prior art exists, the invention provides a kind of low Reynolds number airfoil and the control method thereof with collaborative jet vectoring, for controlling the dynamics of fluid near aerofoil profile, reach and significantly increase profile lift, obviously reduce resistance simultaneously, promote airfoil stall characteristic, thus realize the efficient object promoting flight vehicle aerodynamic performance; In addition, also there is the little advantage of energy consumption.
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, air nozzle (2) is set in aerofoil profile (1) upper surface leading edge, air suctiton inlet (3) is set at aerofoil profile (1) upper surface trailing edge; Described air nozzle (2) is communicated with by the airflow line (5) being arranged at described aerofoil profile (1) inner with described air suctiton inlet (3), forms blowing suction loop; Be provided with for driving air-breathing and the jet air pump (4) carried out simultaneously in described airflow line (5); Further, described air nozzle (2) and described air suctiton inlet (3) are all vertical with the upper surface of described aerofoil profile (1).
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 the pipeline for settling described air pump (4), described anterior pipeline (51) is for being positioned at the pipeline before described middle part pipeline (52), and described rear portion pipeline (53) is for being positioned at the pipeline after described middle part pipeline (52);
Described rear portion pipeline (53) is by direction from back to front, and its cross section is expanded gradually; Described anterior pipeline (51) is by direction from back to front, and its cross section is shunk gradually.
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 the jet and trailing edge air-breathing of leading edge simultaneously, carries out active Flow Control to airfoil surface air-flow;
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 sprayed is aerofoil profile (1) upper surface fluid Implantation Energy, main flow is accelerated by jet injection, and then accelerate the flowing of upper surface fluid, increase lift; In addition, air-flow produces suction in aerofoil profile (1) leading edge surface, and External airflow field is pointed to perpendicular to aerofoil profile (1) surface in the direction of suction, and the component that this suction is parallel to flow direction is contrary with flow direction, and contrary with drag direction, and then reduce 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 to be done work supercharging by air pump again, flow through anterior pipeline (51), 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 the active Flow Control mode of simultaneously and trailing edge air-breathing jet in leading edge, reaching increases lift, reduces resistance, improves stalling characteristics object;
(2) jet and air-breathing does not need extra source of the gas, therefore avoids complicated vent line design;
(3) mechanism that airflow circulating utilizes can reduce energy resource consumption;
(4) moving-member is not needed, easy to implement, may be used for the wing of fixed wing aircraft, also can be used for screw propeller, rotor etc. and rotate class lift member; Both may be used 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 using collaborative jet vectoring;
Fig. 3 is the aerofoil profile upper surface velocity distribution schematic diagram not adding control;
Fig. 4 is the aerofoil profile upper surface flow field structure schematic diagram using collaborative jet vectoring;
Fig. 5 is the aerofoil profile upper surface flow field structure schematic diagram not adding control.
Detailed description of the invention
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, be aerofoil profile cutaway view, air nozzle 2 is set in aerofoil profile 1 upper surface leading edge, air suctiton inlet 3 is set at aerofoil profile 1 upper surface trailing edge; Air nozzle 2 is communicated with by the airflow line 5 being arranged at aerofoil profile 1 inside with air suctiton inlet 3, forms blowing suction loop; Be provided with for driving air-breathing and the jet air pump 4 carried out simultaneously in airflow line 5; 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 the line putting final endpoint foremost, and its length is chord length.Further, air nozzle 2 and air suctiton inlet 3 are all vertical with the upper surface of aerofoil profile 1, thus ensure that gas is tangentially ejected along upper surface and sucks.
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 is air-flow velocity in the highest region of whole flow field medium velocity, is namely the region that pressure is minimum, therefore, arranges that air nozzle is conducive to the ejection of gas herein; The gas flow be ejected is through aerofoil profile upper surface, and speed reduces gradually, in trailing edges pressure increase, is conducive to the carrying out of air-breathing herein.Visible, air nozzle provided by the invention and air suctiton inlet arrangement, airflow circulating institute energy requirement can be reduced to greatest extent, reduce the power that air pump consumes, reduce air pump burden, reduce energy resource consumption, by active Flow Control method provided by the invention, obvious lift-rising drag-reduction effect can be obtained with lower power.
In addition, the airflow line 5 that the present invention relates to comprises anterior pipeline 51, middle part pipeline 52 and rear portion pipeline 53; Middle part pipeline 52 is the pipeline for settling air pump 4, and anterior pipeline 51 is for being positioned at the pipeline before the pipeline 52 of middle part, and rear portion pipeline 53 is for being positioned at the pipeline after the pipeline 52 of middle part;
Rear portion pipeline 53 is by direction from back to front, and its cross section is expanded gradually, and air-flow is inhaled into after among the pipeline of rear portion by air suctiton inlet, along with pipeline section is expanded gradually, air current flow speed is reduced gradually, and pressure raises, and enters air pump under pressure; Anterior pipeline 51 is by direction from back to front, and its cross section is shunk gradually, and air-flow flows through anterior pipeline, along with pipeline section shrinks gradually by after air pump acting supercharging.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 the jet and trailing edge air-breathing of leading edge simultaneously, carries out active Flow Control to airfoil surface air-flow;
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 sprayed 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 namely the lift of aerofoil profile depends on aerofoil profile upper and lower surface velocity contrast.Thus the flowing accelerating upper surface can reach the object increasing lift.Conventional aerofoil profile accelerates upper surface air current flow by the Curvature varying of leading edge surface and then produces lift, this accelerating action is very limited, and carry out injection acceleration by the jet of high speed, upper surface air-flow velocity can reach very high, and the circular rector value around aerofoil profile is that conventional aerofoil profile institute is inaccessiable.Therefore, mode of the present invention greatly can increase the lift of aerofoil profile.
The reduction of the present resistance of another aspect acting body of jet.As front, jet accelerates the mainstream speed of surface area, also comprises the flowing near leading edge.Fast air-flow produces large suction in aerofoil profile leading edge surface, and External airflow field is pointed to perpendicular to surface in the direction of suction, 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 reduction 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; Rear portion pipeline 53 streamwise is expanded gradually, and air current flow speed is reduced gradually, and pressure raises, and air-flow is inhaled into air pump, then, air-flow to be done work supercharging by air pump again, flows through anterior pipeline 51, along with anterior pipeline 51 shrinks gradually, flow velocity increases, and becomes high-speed jet and injects among main flow.The effect of air-breathing can accelerate the flowing velocity of airfoil trailing edge equally, makes flowing can keep attachment state, the generation of control separation eddy current, improves the stalling characteristics of aerofoil profile.Jet and synergy that is air-breathing can reach the object of remarkable lift-rising drag reduction.
Collaborative jet control method provided by the invention, local flow field characteristic can be changed, see Fig. 2, for using the aerofoil profile upper surface velocity distribution schematic diagram of collaborative jet vectoring, 10 is velocity distribution near air nozzle downstream, and 11 is air suctiton inlet upstream vicinity velocity distribution, can find out, the velocity distribution of upper surface becomes fuller due to the accelerating action of jet 8 and getter action, and the ability of control separation is strengthened.See Fig. 3, for not adding the aerofoil profile upper surface velocity profile of control, 12 control velocity distribution near aerofoil profile leading edge for not adding, and 13 control velocity distribution near 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 ability of the gas control separation of low speeds flow is more weak, easily produces large separation eddy, namely enter stall condition when airfoil angle-of-attack is larger, 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, still remains adhered to the state of upper surface, be delayed the stall of aerofoil profile under being flowing in At High Angle of Attack; And under not adding the aerofoil profile At High Angle of Attack of control there is stall in separated region 14.
Empirical tests, adopt low Reynolds number airfoil and the control method thereof with collaborative jet vectoring provided by the invention, the lift coefficient of aerofoil profile, maximum lift coefficient, stalling incidence all have remarkable lifting.Lift coefficient wherein under null alpha can be increased to 70%, and maximum lift coefficient can bring up to about 150%, stalling incidence increase about 60%.Meanwhile, its zero liter of angle of attack, 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 the active Flow Control mode of simultaneously and trailing edge air-breathing jet in leading edge, reaching increases lift, reduces resistance, improves stalling characteristics object;
(2) jet and air-breathing does not need extra source of the gas, therefore avoids complicated vent line design;
(3) mechanism that airflow circulating utilizes can reduce energy resource consumption;
(4) moving-member is not needed, easy to implement, may be used for the wing of fixed wing aircraft, also can be used for screw propeller, rotor etc. and rotate class lift member; Both may be used 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 look protection scope of the present invention.
Claims (4)
1. there is a low Reynolds number airfoil for collaborative jet vectoring, it is characterized in that, air nozzle (2) is set in aerofoil profile (1) upper surface leading edge, air suctiton inlet (3) is set at aerofoil profile (1) upper surface trailing edge; Described air nozzle (2) is communicated with by the airflow line (5) being arranged at described aerofoil profile (1) inner with described air suctiton inlet (3), forms blowing suction loop; Be provided with for driving air-breathing and the jet air pump (4) carried out simultaneously in described airflow line (5); Further, described air nozzle (2) and described air suctiton inlet (3) are all vertical with the upper surface of described aerofoil profile (1);
Wherein, described airflow line (5) comprises anterior pipeline (51), middle part pipeline (52) and rear portion pipeline (53); Described middle part pipeline (52) is the pipeline for settling described air pump (4), described anterior pipeline (51) is for being positioned at the pipeline before described middle part pipeline (52), and described rear portion pipeline (53) is for being positioned at the pipeline after described middle part pipeline (52);
Described rear portion pipeline (53) is by direction from back to front, and its cross section is expanded gradually; Described anterior pipeline (51) is by direction from back to front, and its cross section is shunk gradually.
2. the low Reynolds number airfoil with collaborative jet vectoring according to claim 1, it 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 aerofoil profile is applied to fixed wing aircraft, screw propeller or rotor.
4., for a collaborative jet control method for low Reynolds number airfoil, it is characterized in that, comprise the following steps:
Air pump (4) drives the jet and trailing edge air-breathing of leading edge simultaneously, carries out active Flow Control to airfoil surface air-flow;
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 sprayed is aerofoil profile (1) upper surface fluid Implantation Energy, main flow is accelerated by jet injection, and then accelerate the flowing of upper surface fluid, increase lift; In addition, air-flow produces suction in aerofoil profile (1) leading edge surface, and External airflow field is pointed to perpendicular to aerofoil profile (1) surface in the direction of suction, and the component that this suction is parallel to flow direction is contrary with flow direction, and contrary with drag direction, and then reduce 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 to be done work supercharging by air pump again, flow through anterior pipeline (51), along with anterior pipeline (51) shrinks gradually, flow velocity increases, and becomes high-speed jet and injects among main flow.
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