JP2014214851A - Surface flow control system and surface flow control method - Google Patents

Surface flow control system and surface flow control method Download PDF

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JP2014214851A
JP2014214851A JP2013094903A JP2013094903A JP2014214851A JP 2014214851 A JP2014214851 A JP 2014214851A JP 2013094903 A JP2013094903 A JP 2013094903A JP 2013094903 A JP2013094903 A JP 2013094903A JP 2014214851 A JP2014214851 A JP 2014214851A
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flow
moving body
boundary layer
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plasma actuator
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JP6029068B2 (en
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東潤 郭
Toujun Kaku
東潤 郭
良稲 上田
Yoshine Ueda
良稲 上田
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Japan Aerospace Exploration Agency JAXA
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
    • B64C21/10—Influencing air flow over aircraft surfaces by affecting boundary layer flow using other surface properties, e.g. roughness
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05H—PLASMA TECHNIQUE; PRODUCTION OF ACCELERATED ELECTRICALLY-CHARGED PARTICLES OR OF NEUTRONS; PRODUCTION OR ACCELERATION OF NEUTRAL MOLECULAR OR ATOMIC BEAMS
    • H05H1/00—Generating plasma; Handling plasma
    • H05H1/24—Generating plasma
    • H05H1/2406—Generating plasma using dielectric barrier discharges, i.e. with a dielectric interposed between the electrodes
    • H05H1/2439—Surface discharges, e.g. air flow control
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
    • B64C23/005—Influencing air flow over aircraft surfaces, not otherwise provided for by other means not covered by groups B64C23/02 - B64C23/08, e.g. by electric charges, magnetic panels, piezoelectric elements, static charges or ultrasounds
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
    • F15D1/00—Influencing flow of fluids
    • F15D1/002—Influencing flow of fluids by influencing the boundary layer
    • F15D1/0065—Influencing flow of fluids by influencing the boundary layer using active means, e.g. supplying external energy or injecting fluid
    • F15D1/0075—Influencing flow of fluids by influencing the boundary layer using active means, e.g. supplying external energy or injecting fluid comprising electromagnetic or electrostatic means for influencing the state of the fluid, e.g. for ionising the fluid or for generating a plasma
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05H—PLASMA TECHNIQUE; PRODUCTION OF ACCELERATED ELECTRICALLY-CHARGED PARTICLES OR OF NEUTRONS; PRODUCTION OR ACCELERATION OF NEUTRAL MOLECULAR OR ATOMIC BEAMS
    • H05H1/00—Generating plasma; Handling plasma
    • H05H1/24—Generating plasma
    • H05H1/2406—Generating plasma using dielectric barrier discharges, i.e. with a dielectric interposed between the electrodes
    • H05H1/2418—Generating plasma using dielectric barrier discharges, i.e. with a dielectric interposed between the electrodes the electrodes being embedded in the dielectric
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/12—Boundary layer controls by using electromagnetic tiles, fluid ionizers, static charges or plasma
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/10—Drag reduction

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Spectroscopy & Molecular Physics (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Electromagnetism (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Plasma Technology (AREA)

Abstract

PROBLEM TO BE SOLVED: To provide a surface flow control system that can control the laminar flow of a boundary layer in a wide area from low speed to high speed irrespective of the shape of a movable body, and has good efficiency with a simple structure only using electrical means, and provide a surface control method.SOLUTION: In a surface flow control system controlling a plasma actuator 110 provided on the surface of a movable body relatively moving with respect to a fluid, the plasma actuator 110 is arranged in the vicinity of a front end edge part, and can be controlled so as to change the lateral flow speed component of the boundary layer flow of the fluid on the surface of the movable body.

Description

本発明は、流体に対して相対的に移動する移動体と、前記移動体の表面に設けられたプラズマアクチュエータと、前記プラズマアクチュエータを制御する制御手段とを備えた表面流制御システムおよび表面流制御方法に関し、特に航空機の翼に好適な表面流制御システムおよび表面流制御方法に関する。   The present invention relates to a surface flow control system and a surface flow control including a moving body that moves relative to a fluid, a plasma actuator provided on a surface of the moving body, and a control unit that controls the plasma actuator. More particularly, the present invention relates to a surface flow control system and a surface flow control method suitable for aircraft wings.

流体に対して相対的に移動する移動体に働く抵抗は、圧力抵抗と摩擦抵抗に分けられ、特に航空機の場合、これらの抵抗を小さくすることで燃費の向上を図ることが可能となる。
摩擦抵抗は境界層内の流れの状態に依存し、層流の場合が乱流の場合より摩擦抵抗が小さく、飛行中の機体周りの流れを層流に維持させることで摩擦抵抗の低減に大きく貢献するため、翼などの機体周りの流れを層流化することが望ましい。
層流から乱流に境界層流れが遷移を起こす空気力学的な現象は、大きく分けて、Ｔ−Ｓ（Ｔｏｌｌｍｉｅｎ−Ｓｃｈｌｉｃｈｔｉｎｇ）不安定とＣ−Ｆ（Ｃｒｏｓｓ−Ｆｌｏｗ；横流れ）不安定の２つが挙げられる。
特に、Ｃ−Ｆ不安定による遷移は、後退角の大きい物体形状（例えば、航空機の後退翼）において遷移を起こす支配的な要因である。
境界層外縁流れの方向に対して横流れ速度成分が大きいと、Ｃ−Ｆ不安定性は顕著に発達し、これに起因して境界層は層流から乱流へ遷移する。 The resistance acting on the moving body that moves relative to the fluid is divided into pressure resistance and frictional resistance. In particular, in the case of an aircraft, it is possible to improve fuel consumption by reducing these resistances.
Frictional resistance depends on the flow conditions in the boundary layer, and the laminar flow has a lower frictional resistance than the turbulent flow, and the flow around the aircraft in flight is maintained in a laminar flow, greatly reducing the frictional resistance. To contribute, it is desirable to laminate the flow around the aircraft, such as wings.
Aerodynamic phenomena in which boundary layer flow transitions from laminar flow to turbulent flow can be broadly divided into two types: TS (Tollmien-Schrichting) instability and CF (Cross-Flow) instability. Can be mentioned.
In particular, transition due to C-F instability is a dominant factor causing transition in an object shape having a large receding angle (for example, a swept wing of an aircraft).
When the transverse flow velocity component is large with respect to the direction of the boundary layer outer edge flow, the CF instability develops remarkably, and as a result, the boundary layer transitions from laminar flow to turbulent flow.

超音速航空機のように後退角の大きい主翼形態を持つ場合、層流から乱流へ遷移は横流れ（Ｃｒｏｓｓ−Ｆｌｏｗ）不安定に起因する。
これは翼スパン方向に圧力勾配があることから境界層内の横流れ成分が卓越することにより発生する遷移メカニズムである。
そのため、従来の技術では翼スパン方向に圧力分布が発生しないような機体形状にすることにより、Ｃ−Ｆ不安定を抑制した層流翼化が主流であるが、このような方法では、ある飛行状態での層流翼化のため翼形状に拘束されるため、離着陸から巡航飛行時の低速から高速飛行領域の広い飛行領域において必ずしも最適な空力性能を持つことができないという問題があった。 In the case of a main wing form with a large receding angle such as a supersonic aircraft, the transition from laminar flow to turbulent flow is caused by cross-flow instability.
This is a transition mechanism that occurs due to the dominant cross-flow component in the boundary layer due to the pressure gradient in the blade span direction.
Therefore, in the conventional technique, laminar airfoil with suppressed CF instability is mainstream by making the airframe shape so that pressure distribution does not occur in the blade span direction. Since it is constrained by the wing shape due to laminar wing in the state, there is a problem that it is not always possible to have optimum aerodynamic performance in a wide flight region from low speed to high speed flight region during takeoff and landing and cruise flight.

一方、流体に対して相対的に移動する移動体の表面に設けられたプラズマアクチュエータによって、流体の流れを制御するものが公知である（特許文献１、２、３等参照。）。
これらの公知のものは、いずれも移動体の表面に対して鉛直方向の気流を発生させることにより移動体表面の流体の境界層の剥離を制御したり下流側の流れを制御するものである。 On the other hand, there is known one that controls the flow of fluid by a plasma actuator provided on the surface of a moving body that moves relative to the fluid (see Patent Documents 1, 2, 3, etc.).
All of these known ones control the separation of the boundary layer of the fluid on the surface of the moving body or the downstream flow by generating a vertical airflow with respect to the surface of the moving body.

特開２００７−３１７６５６号公報JP 2007-317656 A 特開２００８−２９０７１０号公報JP 2008-290710 A 特開２０１２−０４７０６７号公報JP 2012-047067 A

特許文献１乃至３等で公知のものは、移動体の表面に対してその垂線方向の気流を発生させることで境界層の剥離を制御したり下流側の流れを制御するものであって、境界層の層流から乱流へ遷移を制御することは不可能であり、境界層の層流化は依然として機体形状と流体との相対速度に依存するという問題があった。
また、Ｃ−Ｆ不安定を抑制することで境界層遷移を制御するために、ジェット流を境界層に噴き込んだり、境界層内の流れを吸い込んだりする方法が考えられるが、複雑な機構を有し、また、多くのエネルギーの供給が必要になるという、構造的、効率的な問題があった。 Known in Patent Documents 1 to 3 and the like control the separation of the boundary layer or control the flow on the downstream side by generating an air flow in the direction perpendicular to the surface of the moving body. It was impossible to control the transition from laminar flow to turbulent flow, and laminarization of the boundary layer was still dependent on the relative velocity between the airframe shape and the fluid.
Moreover, in order to control boundary layer transition by suppressing CF instability, a method of injecting a jet flow into the boundary layer or sucking a flow in the boundary layer can be considered. In addition, there is a structural and efficient problem that a lot of energy needs to be supplied.

そこで、本発明者は、プラズマアクチュエータによって、移動体表面の流体の境界層流れの横流れ速度成分を変化させることでＣ−Ｆ不安定性を変化させて、移動体の形状に関係なく、また低速から高速までの幅広い領域において境界層の層流化を制御可能であるという、従来にない全く新規な発想に至った。
すなわち、本発明は、移動体の形状に関係なく、低速から高速までの幅広い領域において境界層の層流化を制御可能であり、かつ、電気的な手段のみの簡単な構造で効率のよい表面流制御システムおよび表面流制御方法を提供することを目的とする。 Therefore, the present inventor changes the CF instability by changing the transverse flow velocity component of the boundary layer flow of the fluid on the surface of the moving body by the plasma actuator, so that the instability can be changed regardless of the shape of the moving body. This led to a completely new idea that the laminarization of the boundary layer can be controlled in a wide range up to high speed.
That is, the present invention can control the laminarization of the boundary layer in a wide range from low speed to high speed regardless of the shape of the moving body, and has an efficient surface with a simple structure using only electric means. It is an object to provide a flow control system and a surface flow control method.

本請求項１に係る発明は、流体に対して相対的に移動する移動体と、前記移動体の表面に設けられたプラズマアクチュエータと、前記プラズマアクチュエータを制御する制御手段とを備えた表面流制御システムであって、前記移動体の前方端縁部が、流体の移動方向に対して垂直でない方向に延びるように形成され、前記プラズマアクチュエータが、前記前方端縁部の近傍に配置され、前記制御手段が、前記移動体表面の流体の境界層流れの横流れ速度成分を変化させるようにプラズマアクチュエータを制御可能に構成されていることにより、前記課題を解決するものである。   The invention according to claim 1 is a surface flow control including a moving body that moves relative to a fluid, a plasma actuator provided on a surface of the moving body, and a control unit that controls the plasma actuator. In the system, a front end edge of the moving body is formed to extend in a direction not perpendicular to a moving direction of the fluid, and the plasma actuator is disposed in the vicinity of the front end edge. The means is configured to control the plasma actuator so as to change the transverse flow velocity component of the boundary layer flow of the fluid on the surface of the moving body, thereby solving the above-mentioned problem.

本請求項２に係る発明は、請求項１に係る表面流制御システムの構成に加え、前記プラズマアクチュエータが、前記前方端縁部の近傍から所定の間隔で多段に配置されていることにより、前記課題を解決するものである。
本請求項３に係る発明は、請求項１または請求項２に係る表面流制御システムの構成に加え、前記制御手段が、前記移動体表面の流体の境界層流れの横流れ速度成分を減少させるようにプラズマアクチュエータを制御可能に構成されていることにより、前記課題を解決するものである。
本請求項４に係る発明は、請求項１乃至請求項３のいずれかに係る表面流制御システムの構成に加え、前記移動体が、航空機の後退翼であることにより、前記課題を解決するものである。
本請求項５に係る発明は、請求項１乃至請求項４のいずれかに係る表面流制御システムの構成に加え、前記制御手段が、前記移動体と流体の相対速度に応じて前記プラズマアクチュエータの動作を制御可能に構成されていることにより、前記課題を解決するものである。 In the invention according to claim 2, in addition to the configuration of the surface flow control system according to claim 1, the plasma actuator is arranged in multiple stages at a predetermined interval from the vicinity of the front end edge. It solves the problem.
According to the third aspect of the invention, in addition to the configuration of the surface flow control system according to the first or second aspect, the control means reduces the lateral flow velocity component of the boundary layer flow of the fluid on the surface of the moving body. Further, the above-described problem is solved by being configured to be able to control the plasma actuator.
According to a fourth aspect of the present invention, in addition to the configuration of the surface flow control system according to any one of the first to third aspects, the moving body is a swept wing of an aircraft, thereby solving the problem. It is.
According to the fifth aspect of the present invention, in addition to the configuration of the surface flow control system according to any one of the first to fourth aspects, the control means is configured to control the plasma actuator according to the relative velocity between the moving body and the fluid. The above-described problem is solved by being configured to be able to control the operation.

本請求項６に係る発明は、流体に対して相対的に移動する移動体の表面に設けられたプラズマアクチュエータを制御して、移動体表面の流体の境界層流れを変化させる表面流制御方法であって、前記プラズマアクチュエータによって、前記移動体表面の流体の境界層流れの横流れ速度成分を変化させる流れを誘起することにより、前記課題を解決するものである。
本請求項７に係る発明は、請求項６に係る表面流制御方法の構成に加え、前記プラズマアクチュエータによって、前記移動体表面の流体の境界層流れの横流れ速度成分を減少させる流れを誘起することにより、前記課題を解決するものである。 The invention according to claim 6 is a surface flow control method for controlling the plasma actuator provided on the surface of the moving body that moves relative to the fluid to change the boundary layer flow of the fluid on the surface of the moving body. Then, the problem is solved by inducing a flow that changes the transverse flow velocity component of the boundary layer flow of the fluid on the surface of the movable body by the plasma actuator.
In the invention according to claim 7, in addition to the configuration of the surface flow control method according to claim 6, the plasma actuator induces a flow that reduces the transverse flow velocity component of the boundary layer flow of the fluid on the surface of the moving body. Thus, the problem is solved.

本請求項１に係る表面流制御システムによれば、移動体の前方端縁部が流体の移動方向に対して垂直でない方向に延びている、すなわち、移動体の境界層流れの層流から乱流への遷移がＣ−Ｆ不安定が支配的な要因となるものであり、プラズマアクチュエータが前方端縁部の近傍に配置され、移動体表面の流体の境界層流れの横流れ速度成分を変化させることによって、移動体の形状に関係なく、低速から高速までの幅広い領域において境界層の層流化を制御可能であり、かつ、電気的な手段のみの簡単な構造で効率よく制御することが可能となる。   According to the surface flow control system of the first aspect of the present invention, the front end edge of the moving body extends in a direction that is not perpendicular to the moving direction of the fluid, that is, turbulence occurs from the laminar flow of the boundary layer flow of the moving body. C-F instability is the dominant factor in the transition to the flow, and the plasma actuator is disposed in the vicinity of the front edge, and changes the lateral flow velocity component of the boundary layer flow of the fluid on the moving body surface. Therefore, it is possible to control the laminar flow of the boundary layer in a wide range from low speed to high speed regardless of the shape of the moving body, and it is possible to control it efficiently with a simple structure using only electrical means. It becomes.

プラズマアクチュエータは境界層内の表面近くに体積力を発生させ、表面に沿った流れを誘起（コアンダー効果）し、遷移を誘発する横流れ速度方向の逆方向にプラズマアクチュエータによる流れを誘起することにより横流れ速度成分の発達を抑制し、横流れ不安定性に起因する遷移を抑制することができ、横流れ速度方向に流れを誘起することで、逆に遷移を促進することも可能である。
また、横流れ不安定性による遷移は翼の前方端縁部付近で卓越する場合が多く、境界層が非常に薄い前方端縁部付近での他のデバイスを適用した場合、圧力抵抗の増加がデバイスによる凸凹が境界層遷移を促進する恐れがあるが、プラズマアクチュエータを前方端縁部の近傍に配置することで、圧力抵抗に変化を与えることなく、横流れ速度成分のみを制御することが可能となる。
さらに、主流方向速度に比べ横流れ方向成分が遅いことから、プラズマアクチュエータによる制御で、十分な効果を得ることができる。 The plasma actuator generates a volume force near the surface in the boundary layer, induces a flow along the surface (counder effect), and induces a flow by the plasma actuator in the opposite direction of the transverse flow velocity direction that induces the transition. It is possible to suppress the development of the velocity component, to suppress the transition caused by the lateral flow instability, and to reverse the transition by inducing the flow in the direction of the lateral flow velocity.
Also, transitions due to cross-flow instability often predominate near the front edge of the wing, and when other devices are applied near the front edge where the boundary layer is very thin, the increase in pressure resistance depends on the device. Although the unevenness may promote the boundary layer transition, it is possible to control only the lateral flow velocity component without changing the pressure resistance by arranging the plasma actuator in the vicinity of the front edge.
Furthermore, since the transverse direction component is slower than the mainstream direction velocity, a sufficient effect can be obtained by the control by the plasma actuator.

本請求項２に記載の構成によれば、プラズマアクチュエータが前方端縁部の近傍から所定の間隔で多段に配置されていることにより、流れ方向のより広い範囲で横流れ速度成分の制御が可能となり、さらに確実に制御することが可能となる。
本請求項３に記載の構成によれば、制御手段が移動体表面の流体の境界層流れの横流れ速度成分を減少させるようにプラズマアクチュエータを制御可能に構成されていることにより、確実に横流れ不安定性に起因する境界層の層流から乱流への遷移を抑制することができ、摩擦抵抗を低減することができる。
本請求項４に記載の構成によれば、移動体が航空機の後退翼であることにより、超音速航空機等において、ある飛行状態での層流翼化のため翼形状に拘束されることなく、離着陸から巡航飛行時の低速飛行領域、さらに高速飛行領域の広い飛行領域において最適な空力性能を得ることができる。
本請求項５に記載の構成によれば、制御手段が移動体と流体の相対速度に応じて前記プラズマアクチュエータの動作を制御可能に構成されていることにより、低速から高速までの幅広い領域において境界層の層流化を最適に制御可能となる。 According to the second aspect of the present invention, the plasma actuators are arranged in multiple stages at a predetermined interval from the vicinity of the front edge, so that the lateral flow velocity component can be controlled in a wider range in the flow direction. Further, it becomes possible to control more reliably.
According to the configuration of the third aspect of the present invention, the control means is configured to be able to control the plasma actuator so as to reduce the transverse flow velocity component of the boundary layer flow of the fluid on the surface of the moving body. Transition from laminar flow to turbulent flow due to the qualitative property can be suppressed, and frictional resistance can be reduced.
According to the configuration of the present invention, since the moving body is a retreating wing of an aircraft, in a supersonic aircraft or the like, without being constrained by a wing shape for laminar wing in a certain flight state, Optimum aerodynamic performance can be obtained in the low-speed flight region during cruise flight from take-off and landing and in the wide flight region of the high-speed flight region.
According to the configuration of the fifth aspect of the present invention, the control means is configured to be able to control the operation of the plasma actuator in accordance with the relative velocity between the moving body and the fluid, so that the boundary in a wide range from low speed to high speed can be obtained. The laminar flow can be optimally controlled.

本請求項６に係る表面流制御方法によれば、流体に対して相対的に移動する移動体の表面に設けられたプラズマアクチュエータを制御して、移動体表面の流体の境界層流れの横流れ速度成分を変化させることによって、移動体の形状に関係なく、低速から高速までの幅広い領域において境界層の層流化を制御可能であり、かつ、電気的な手段のみの簡単な構造で効率よく制御することが可能となる。
本請求項７に記載の構成によれば、プラズマアクチュエータによって移動体表面の流体の境界層流れの横流れ速度成分を減少させる流れを誘起することにより、確実に横流れ不安定性に起因する境界層の層流から乱流への遷移を抑制することができ、摩擦抵抗を低減することができる。 According to the surface flow control method according to the sixth aspect of the present invention, the plasma actuator provided on the surface of the moving body that moves relative to the fluid is controlled to control the lateral flow velocity of the boundary layer flow of the fluid on the surface of the moving body. By changing the components, it is possible to control the laminarization of the boundary layer in a wide range from low speed to high speed regardless of the shape of the moving body, and to control efficiently with a simple structure using only electrical means. It becomes possible to do.
According to the configuration of the seventh aspect of the present invention, by inducing a flow that reduces the transverse flow velocity component of the boundary layer flow of the fluid on the surface of the moving body by the plasma actuator, the layer of the boundary layer is surely caused by the instability of the transverse flow. Transition from flow to turbulent flow can be suppressed, and frictional resistance can be reduced.

翼外縁と中心から１００ｍｍの位置の流れの説明図。Explanatory drawing of the flow of the position of 100 mm from a wing outer edge and center. 図１の数値解析による横流れ成分のグラフ。The graph of the transverse flow component by the numerical analysis of FIG. 図２の状態の境界層流の遷移解析のグラフ。The graph of the transition analysis of the boundary layer flow of the state of FIG. 図３の状態のＰｓｉのグラフ。The graph of Psi in the state of FIG. 横流れ０とした時の境界層流の遷移解析のグラフ。Graph of transition analysis of boundary layer flow when cross flow is zero. 図５の状態のＰｓｉのグラフ。6 is a graph of Psi in the state of FIG. 本発明の一実施形態に係る表面流制御システムのモデル説明図。The model explanatory view of the surface flow control system concerning one embodiment of the present invention. 図７のプラズマアクチュエータの断面説明図。Sectional explanatory drawing of the plasma actuator of FIG. 翼の表面流速のグラフ。Graph of wing surface flow velocity. 境界層のプロファイルのグラフ。Boundary layer profile graph. 他の条件での翼の表面流速のグラフ。Graph of wing surface velocity at other conditions. さらに他の条件での翼の表面流速のグラフ。The graph of the surface velocity of the wing in other conditions.

本発明の表面流制御システムは、流体に対して相対的に移動する移動体と、移動体の表面に設けられたプラズマアクチュエータと、プラズマアクチュエータを制御する制御手段とを備えた表面流制御システムであって、移動体の前方端縁部が、流体の移動方向に対して垂直でない方向に延びるように形成され、プラズマアクチュエータが、前方端縁部の近傍に配置され、制御手段が、移動体表面の流体の境界層流れの横流れ速度成分を変化させるようにプラズマアクチュエータを制御可能に構成されるものであり、移動体の形状に関係なく、低速から高速までの幅広い領域において境界層の層流化を制御可能であり、かつ、電気的な手段のみの簡単な構造で効率のよいものであれば、その具体的な実施態様はいかなるものであっても良い。   The surface flow control system of the present invention is a surface flow control system comprising a moving body that moves relative to a fluid, a plasma actuator provided on the surface of the moving body, and a control means for controlling the plasma actuator. The front end edge of the moving body is formed to extend in a direction not perpendicular to the moving direction of the fluid, the plasma actuator is disposed in the vicinity of the front end edge, and the control means is provided on the surface of the moving body. The plasma actuator can be controlled so as to change the transverse flow velocity component of the boundary layer flow of the fluid. Laminarization of the boundary layer in a wide range from low speed to high speed regardless of the shape of the moving body As long as it is controllable and efficient with a simple structure using only electric means, any specific embodiment may be used.

本発明に係る表面流制御システムおよび表面流制御方法について、さらに詳しく説明する。
例えば、図１に示すように、中心からの幅２５０ｍｍ、前方端縁部の後退角６０°、迎角（ＡＯＡ）３°の翼について、流速（Ｕ）１９ｍ／ｓの時、中心から１００ｍｍの位置では、おおよそ点線で示すような表面流れを形成する。
この位置の流れ場について数値解析（ＣＦＤ）により解析すると、図２のような横流れ速度成分が存在することが解った。
ここで、Ｃは翼の長さ、Ｘは前方端縁部からの距離、Ｚ（ｍｍ）は翼の表面からの高さ、Ｖ（ｍ／ｓ）は横流れ（翼端方法（図１の下方向）がプラス、中心方向（図１の上方）がマイナス）の速度成分である。 The surface flow control system and the surface flow control method according to the present invention will be described in more detail.
For example, as shown in FIG. 1, for a wing having a width of 250 mm from the center, a receding angle of the front edge of 60 °, and an angle of attack (AOA) of 3 °, when the flow velocity (U) is 19 m / s, the blade is 100 mm from the center. In position, it creates a surface flow, roughly as shown by the dotted line.
When the flow field at this position was analyzed by numerical analysis (CFD), it was found that there was a transverse flow velocity component as shown in FIG.
Where C is the blade length, X is the distance from the front edge, Z (mm) is the height from the blade surface, and V (m / s) is the transverse flow (blade tip method (bottom of Fig. 1 Direction) is a positive speed component, and the center direction (upward in FIG. 1) is a negative speed component.

この条件で、境界層流の遷移解析（ｅｎ法）を行った結果、図３に示すように、翼の前方端縁部付近でＮ値が急激に増加しており、これにより、前方端縁部付近で層流から乱流への遷移が発生する可能性が高いことがわかる。
図３に示すＮ値の主たる要因は図４に示すＰｓｉの特性から判断することができる。図４のＰｓｉが０でないことから、図３のＮ値が横流れ成分により発達したＮ値であることを示している。
これらの解析結果から後退角６０度の翼の場合、境界層遷移はＣ−Ｆ不安定性に起因する遷移であると判断される。
上記の条件で横流れ成分を強制的に０にした場合、図５に示すように、Ｎ値分布が急激に減少する。そして、図６に示すように、Ｐｓｉ値は０あり、図５のＮ値はＴ−Ｓ不安定に起因する遷移であると判断される。
以上の解析結果を総合すると、境界層遷移は横流れ成分よるＣ−Ｆ不安定による遷移であり、横流れがない場合では境界層遷移の発生可能性が大幅に低減される事がわかる。 In this condition, transition analysis of a boundary layer flow (e n method) the result of, as shown in FIG. 3, and N value abruptly increases in the vicinity of the front edge of the wing, thereby, the front end It can be seen that a transition from laminar to turbulent flow is likely to occur near the edge.
The main factor of the N value shown in FIG. 3 can be determined from the characteristics of Psi shown in FIG. Since Psi in FIG. 4 is not 0, it is indicated that the N value in FIG. 3 is an N value developed by the transverse flow component.
From these analysis results, in the case of a blade with a receding angle of 60 degrees, it is determined that the boundary layer transition is a transition caused by C—F instability.
When the lateral flow component is forcibly set to 0 under the above conditions, the N value distribution decreases rapidly as shown in FIG. As shown in FIG. 6, the Psi value is 0, and the N value in FIG. 5 is determined to be a transition caused by TS instability.
When the above analysis results are combined, the boundary layer transition is a transition due to CF instability due to the lateral flow component, and it can be seen that the occurrence of the boundary layer transition is greatly reduced when there is no lateral flow.

本発明の１実施形態である表面流制御システムは、図７に示すように、上述した翼（中心からの幅２５０ｍｍ、前方端縁部の後退角６０°）の前方端縁部の近傍表面に、中心から１００ｍｍの位置を中心として長さ１００ｍｍのプラズマアクチュエータを設け、制御手段（図示せず）にプラズマアクチュエータの出力を制御して境界層流れの横流れ速度成分を変化させるものである。
プラズマアクチュエータ１１０は、図８に示すように、誘電体層１１２の両面に２つの電極１１１が位置をずらして設けられた誘電体バリア放電プラズマアクチュエータからり、翼１００の表面に沿って埋め込まれるように設置されている。
また、プラズマアクチュエータ１１０の２つの電極１１１に印加される電圧は、制御手段（図示せず）によって制御される。 As shown in FIG. 7, the surface flow control system according to an embodiment of the present invention is formed on the surface near the front edge of the above-described blade (width 250 mm from the center, receding angle 60 ° of the front edge). A plasma actuator having a length of 100 mm centering on a position 100 mm from the center is provided, and a control means (not shown) controls the output of the plasma actuator to change the transverse flow velocity component of the boundary layer flow.
As shown in FIG. 8, the plasma actuator 110 is a dielectric barrier discharge plasma actuator in which two electrodes 111 are provided on both surfaces of the dielectric layer 112 so as to be shifted in position, and is embedded along the surface of the blade 100. Is installed.
Further, the voltage applied to the two electrodes 111 of the plasma actuator 110 is controlled by a control means (not shown).

上記の表面流制御システムを備えた翼１００に対し、迎角（ＡＯＡ）４°、流速（Ｕ）１０ｍ／ｓの条件で風洞実験を行った。
なお、境界層流れの層流から乱流への遷移位置は、直径１ｍｍのプレストン管によって測定される翼の表面の流速（Ｕｐ）により判定可能である。
すなわち、層流の場合は、表面付近では流速は小さく、表面から離れるに連れて急激に流速が大きくなるが、乱流の場合は、表面付近での流速はやや大きく、表面から離れるに連れて徐々に流速が大きくなることがわかっている。
従って、プレストン管によって測定される流速（Ｕｐ）が低いレベルから高いレベルに変化する位置が、境界層流れの層流から乱流への遷移位置と判断できる。 A wind tunnel experiment was performed on the blade 100 equipped with the above-described surface flow control system under conditions of an angle of attack (AOA) of 4 ° and a flow velocity (U) of 10 m / s.
The transition position of the boundary layer flow from laminar flow to turbulent flow can be determined by the flow velocity (Up) of the blade surface measured by a Preston tube having a diameter of 1 mm.
In other words, in the case of laminar flow, the flow velocity is small near the surface, and the flow velocity suddenly increases as it moves away from the surface, but in the case of turbulent flow, the flow velocity near the surface is slightly larger and as it moves away from the surface. It is known that the flow rate gradually increases.
Therefore, the position where the flow velocity (Up) measured by the Preston tube changes from the low level to the high level can be determined as the transition position from the laminar flow to the turbulent flow of the boundary layer flow.

風洞実験の結果、図９に示すように、境界層流れの層流から乱流への遷移位置は、プラズマアクチュエータを用いない場合、前方端縁部から２５０ｍｍの位置であったのに対し、プラズマアクチュエータに１３ｋＶの電圧を印加した場合、前方端縁部から４５０ｍｍの位置まで後退した。
図７のＸ＝４００ｍｍ（Ｘ／Ｃ＝０．３９）の位置での境界層のプロファイルでも、図１０に示すように、プラズマアクチュエータを用いない場合には、乱流のプロファイルを示し、プラズマアクチュエータに１３ｋＶの電圧を印加した場合には、層流のプロファイルを示しており、境界層流れの層流から乱流への遷移位置が後退しているのが確認できる。 As a result of the wind tunnel experiment, as shown in FIG. 9, the transition position of the boundary layer flow from the laminar flow to the turbulent flow was 250 mm from the front edge when the plasma actuator was not used. When a voltage of 13 kV was applied to the actuator, the actuator retracted to a position 450 mm from the front edge.
Even in the boundary layer profile at the position of X = 400 mm (X / C = 0.39) in FIG. 7, as shown in FIG. 10, when the plasma actuator is not used, a turbulent flow profile is shown. When a voltage of 13 kV is applied, a laminar flow profile is shown, and it can be confirmed that the transition position of the boundary layer flow from the laminar flow to the turbulent flow is retreated.

迎角（ＡＯＡ）４°、流速（Ｕ）１５ｍ／ｓおよび迎角（ＡＯＡ）４°、流速（Ｕ）１９ｍ／ｓの条件で風洞実験を行った結果について、図１１および図１２に示す。
これらの条件においても、境界層流れの層流から乱流への遷移位置は、プラズマアクチュエータを用いることで後退していることがわかる。
すなわち、プラズマアクチュエータを用いて、横流れ速度成分を低減することで容易に境界層流れの層流から乱流への遷移位置を後退させることが可能である。
なお、逆に、横流れ速度成分を増加させるようにプラズマアクチュエータを動作させれば、境界層流れの層流から乱流への遷移位置を前進させることも可能である。 FIG. 11 and FIG. 12 show the results of wind tunnel experiments conducted under conditions of an angle of attack (AOA) of 4 °, a flow velocity (U) of 15 m / s, an angle of attack (AOA) of 4 °, and a flow velocity (U) of 19 m / s.
Even under these conditions, it can be seen that the transition position of the boundary layer flow from laminar flow to turbulent flow is retreated by using the plasma actuator.
That is, it is possible to easily retreat the transition position from the laminar flow to the turbulent flow of the boundary layer flow by reducing the transverse flow velocity component using the plasma actuator.
Conversely, if the plasma actuator is operated so as to increase the transverse flow velocity component, the transition position of the boundary layer flow from laminar flow to turbulent flow can be advanced.

また、上記実施形態においては、プラズマアクチュエータを前方端縁部に平行に１列のみ設けたが、横流れ速度成分を変化させることが可能であれば、どのような角度で取り付けてもよく、また、所定の間隔で多段に設けてもよく、各段それぞれ異なる電圧を印加可能としてもよい。
このことで、翼長方向に広い範囲で横流れ速度成分を細かく制御することが可能となり、異なる条件下でも境界層流れの層流から乱流への遷移位置を最適に制御することが可能となる。例えば、超音速航空機等において、離着陸から巡航飛行時の低速飛行領域、さらに高速飛行領域の広い飛行領域において最適となるように、境界層流れの層流から乱流への遷移位置を変位させることが可能となり、最適な空力性能を得ることができる。 In the above embodiment, only one row of plasma actuators is provided parallel to the front edge, but any angle may be used as long as the lateral flow velocity component can be changed. Multiple stages may be provided at predetermined intervals, and different voltages may be applied to each stage.
This makes it possible to finely control the lateral flow velocity component over a wide range in the blade length direction, and to optimally control the transition position of the boundary layer flow from laminar flow to turbulent flow even under different conditions. . For example, in a supersonic aircraft, etc., the transition position from laminar to turbulent flow of the boundary layer flow should be displaced so as to be optimal in the low speed flight region during cruise flight from takeoff and landing, and in the wide flight region of the high speed flight region. Can be achieved and optimum aerodynamic performance can be obtained.

以上のように、本発明によれば移動体の形状に関係なく、低速から高速までの幅広い領域において境界層の層流化を制御可能であり、かつ、電気的な手段のみの簡単な構造で効率よく表面流を制御することができる。
本発明の表面流制御システムは、航空機、特に後退翼を有する超音速航空機に適用するのが好適であるが、船舶、あるいは、陸上の移動体に適用されてもよく、移動体自体は構造物等に固定され、流体のみが移動するような用途で用いられてもよい。
また、移動体はプロペラや風車等のように、回転することで流体に対して相対的に移動するものであってもよい。 As described above, according to the present invention, it is possible to control laminarization of the boundary layer in a wide range from low speed to high speed regardless of the shape of the moving body, and with a simple structure using only electric means. The surface flow can be controlled efficiently.
The surface flow control system of the present invention is preferably applied to an aircraft, particularly a supersonic aircraft having a swept wing, but may be applied to a ship or a land mobile body, and the mobile body itself is a structure. Etc., and may be used in applications where only the fluid moves.
Further, the moving body may move relative to the fluid by rotating, such as a propeller or a windmill.

１００ ・・・翼
１１０ ・・・プラズマアクチュエータ
１１１ ・・・電極
１１２ ・・・誘電体層 100 ... Wing 110 ... Plasma actuator 111 ... Electrode 112 ... Dielectric layer

Claims (7)

流体に対して相対的に移動する移動体と、前記移動体の表面に設けられたプラズマアクチュエータと、前記プラズマアクチュエータを制御する制御手段とを備えた表面流制御システムであって、
前記移動体の前方端縁部が、流体の移動方向に対して垂直でない方向に延びるように形成され、
前記プラズマアクチュエータが、前記前方端縁部の近傍に配置され、
前記制御手段が、前記移動体表面の流体の境界層流れの横流れ速度成分を変化させるようにプラズマアクチュエータを制御可能に構成されていることを特徴とする請求項１に記載の表面流制御システム。 A surface flow control system comprising a moving body that moves relative to a fluid, a plasma actuator provided on a surface of the moving body, and a control unit that controls the plasma actuator,
The front end edge of the moving body is formed to extend in a direction not perpendicular to the moving direction of the fluid,
The plasma actuator is disposed near the front edge,
2. The surface flow control system according to claim 1, wherein the control means is configured to control a plasma actuator so as to change a transverse flow velocity component of a boundary layer flow of a fluid on the surface of the moving body. 前記プラズマアクチュエータが、前記前方端縁部の近傍から所定の間隔で多段に配置されていることを特徴とする請求項１に記載の表面流制御システム。   2. The surface flow control system according to claim 1, wherein the plasma actuators are arranged in multiple stages at a predetermined interval from the vicinity of the front edge portion. 前記制御手段が、前記移動体表面の流体の境界層流れの横流れ速度成分を減少させるようにプラズマアクチュエータを制御可能に構成されていることを特徴とする請求項１または請求項２に記載の表面流制御システム。   3. The surface according to claim 1, wherein the control means is configured to control a plasma actuator so as to reduce a transverse flow velocity component of a boundary layer flow of a fluid on the surface of the moving body. Flow control system. 前記移動体が、航空機の後退翼であることを特徴とする請求項１乃至請求項３のいずれかに記載の表面流制御システム。   The surface flow control system according to claim 1, wherein the moving body is a swept wing of an aircraft. 前記制御手段が、前記移動体と流体の相対速度に応じて前記プラズマアクチュエータの動作を制御可能に構成されていることを特徴とする請求項１乃至請求項４のいずれかに記載の表面流制御システム。   5. The surface flow control according to claim 1, wherein the control unit is configured to be able to control an operation of the plasma actuator in accordance with a relative velocity between the moving body and the fluid. system. 流体に対して相対的に移動する移動体の表面に設けられたプラズマアクチュエータを制御して、移動体表面の流体の境界層流れを変化させる表面流制御方法であって、
前記プラズマアクチュエータによって、前記移動体表面の流体の境界層流れの横流れ速度成分を変化させる流れを誘起することを特徴とする表面流制御方法。 A surface flow control method for controlling a plasma actuator provided on a surface of a moving body that moves relative to a fluid to change a boundary layer flow of the fluid on the surface of the moving body,
A surface flow control method characterized by inducing a flow that changes a transverse flow velocity component of a boundary layer flow of a fluid on the surface of the moving body by the plasma actuator. 前記プラズマアクチュエータによって、前記移動体表面の流体の境界層流れの横流れ速度成分を減少させる流れを誘起することを特徴とする請求項６に記載の表面流制御方法。   The surface flow control method according to claim 6, wherein the plasma actuator induces a flow that reduces a transverse flow velocity component of a boundary layer flow of a fluid on the surface of the moving body.
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