JP2010243309A - Measuring method of fluid force distribution and measuring device - Google Patents

Measuring method of fluid force distribution and measuring device Download PDF

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JP2010243309A
JP2010243309A JP2009091785A JP2009091785A JP2010243309A JP 2010243309 A JP2010243309 A JP 2010243309A JP 2009091785 A JP2009091785 A JP 2009091785A JP 2009091785 A JP2009091785 A JP 2009091785A JP 2010243309 A JP2010243309 A JP 2010243309A
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distribution
resistance
lift
component velocity
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JP5354659B2 (en
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Hiroyuki Kato
裕之 加藤
Shigeya Watanabe
重哉 渡辺
Kisa Matsushima
紀佐 松島
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Japan Aerospace Exploration Agency JAXA
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Abstract

<P>PROBLEM TO BE SOLVED: To provide a measuring method that measures fluid forces (a drag force and a lift force) applied to an object even when measurement by using a balance is impossible, does not change flowing by insertion of a probe or the like, and does not take a measuring time period as compared to measurement by a pressure probe so as to complete the measurement in a short time, and to provide a measuring device. <P>SOLUTION: This method for measuring distributions of a shape resistance, an inductive resistance and a lift force applied to an object includes the step of measuring a three-component velocity distribution value of rear flow of an object residing in a fluid field, and the step of calculating a pressure distribution by means of a numerical fluid analysis method by using the three-component velocity distribution value as an input. The method further includes a rear flow integration method with the use of the three-component velocity distribution value and the pressure distribution value, thereby calculating out the distributions of the shape resistance, the inductive resistance and the lift force applied to the object. <P>COPYRIGHT: (C)2011,JPO&INPIT

Description

本発明は、風洞試験における計測装置、航空宇宙、自動車、鉄道車両、船舶、建築物、風車、生物、スポーツ等における空力設計に関する。   The present invention relates to an aerodynamic design in a measuring device, aerospace, automobile, railway vehicle, ship, building, windmill, organism, sports, etc. in a wind tunnel test.

従来、物体に作用する流体力(抗力及び揚力)は、例えば非特許文献１に見られるような天秤を使用した計測が主流であるが、微小物体等の天秤の使用が困難な状況では、物体に作用する流体力を計測することが難しい。さらに、天秤による計測では、抗力を形状抵抗と誘導抵抗に分離して計測することができない。また、物体全体でどれだけの力が働いているかの合計のみしか計測できず、流体力の物体の各構成要素における流体力分布は計測できないため、物体のどの構成要素において、抗力や揚力が生じているか知ることができない。
抵抗成分を形状抵抗と誘導抵抗に分離し、その各構成要素における流体力分布を計測するための手法として、後流積分法という手法が知られている［非特許文献２参照］が、従来の後流積分法では、物体後流の計測に、圧力プローブを使用し、物体後流領域全域に対して、プローブを移動させながら計測を行うために、計測に時間がかかるとともに、プローブの挿入により、流れが変化し、プローブのない状態とは結果が変わってしまい、正確な計測が困難であるといった問題がある。 Conventionally, the fluid force (drag and lift) acting on an object is mainly measured using a balance such as that shown in Non-Patent Document 1, but in situations where it is difficult to use a balance such as a micro object, It is difficult to measure the fluid force acting on Furthermore, in the measurement using a balance, it is impossible to measure the drag separately into shape resistance and induction resistance. In addition, since only the total of how much force is acting on the entire object can be measured, and the fluid force distribution in each component of the fluid force object cannot be measured, drag and lift occur in which component of the object. I can't know if
As a method for separating a resistance component into a shape resistance and an inductive resistance and measuring a fluid force distribution in each component, a method called a wake integration method is known [see Non-Patent Document 2]. In the wake integration method, a pressure probe is used to measure the wake of the object, and the measurement is performed while moving the probe over the entire wake region of the object. However, there is a problem that the flow changes, the result changes from the state without the probe, and accurate measurement is difficult.

後流計測の別の計測手法として、粒子画像流速測定法(ＰＩＶ)を使った方法がある。ＰＩＶは、流体中に分散させた微小粒子をシート状にしたレーザ光で２回発光させ、その２回の発光の間に微小粒子が移動した距離を画像処理技術によって求め、その移動距離を２回の発光の時間間隔で割ることで、空間の速度を計測する手法［従来技術文献３参照］である。ＰＩＶの特徴としては、１回の計測で、シート光面内の２次元空間の計測が可能であること、プローブを使った計測と異なり、流れにセンサを挿入しないため、流れを変化させることのない計測が可能であること、といった特徴がある。しかしながら、ＰＩＶで直接計測できるものは流体の速度のみであり、圧力プローブのように流体の圧力に関する情報を測ることはできない。ＰＩＶの計測結果から、圧力を推算する手法に関しては、既に何件かの報告［例えば従来技術文献４参照］があり、物体後流の速度分布から圧力を推算することが示されている。   As another measurement method of the wake measurement, there is a method using a particle image velocimetry (PIV). In PIV, fine particles dispersed in a fluid are emitted twice with a sheet-form laser beam, and the distance that the fine particles have moved between the two times of light emission is determined by an image processing technique. This is a method of measuring the velocity of space by dividing by the time interval of light emission [see Prior Art Document 3]. The characteristics of PIV are that it is possible to measure the two-dimensional space in the light plane of the sheet with a single measurement. Unlike the measurement using a probe, no sensor is inserted in the flow, so the flow can be changed. There is a feature that no measurement is possible. However, what can be directly measured by the PIV is only the velocity of the fluid, and information on the pressure of the fluid cannot be measured like a pressure probe. Regarding the method for estimating the pressure from the PIV measurement result, there have already been several reports [see, for example, Prior Art Document 4], which indicate that the pressure is estimated from the velocity distribution of the wake of the object.

本発明の課題は、天秤を使用した計測が不可能な場合でも、物体に作用する流体力(抗力及び揚力)計測を可能とするものであって、プローブ等の挿入により流れを変化させてしまうことがなく、圧力プローブによる計測のように計測時間がかからず、短時間で計測が終了可能となる後流積分法を用いた計測方法及び計測装置を提案することにある。   An object of the present invention is to enable measurement of fluid force (drag and lift) acting on an object even when measurement using a balance is impossible, and the flow is changed by inserting a probe or the like. Therefore, it is an object of the present invention to propose a measurement method and a measurement device using a wake integration method that does not take a measurement time as in the case of measurement with a pressure probe and can complete the measurement in a short time.

本発明の物体に作用する形状抵抗、誘導抵抗及び揚力分布を計測する方法は、流体場に存する物体の後流の３成分速度分布を計測するステップと、前記３成分速度分布値を入力として、数値流体解析手法により、圧力分布を計算するステップと、前記３成分速度分布値と前記圧力分布値を用いて後流積分法により、物体に作用する形状抵抗、誘導抵抗及び揚力分布を算出するようにした。
本発明の物体に作用する流体力(抗力及び揚力)を計測する方法は、請求項１に記載の方法によって得られた物体に作用する形状抵抗、誘導抵抗及び揚力分布を次式により積分することにより、物体に作用する抗力及び揚力を計測する方法。
ただし、CFは抗力係数、揚力係数それぞれについてCD、CLを表し、形状抵抗係数、誘導抵抗係数それぞれについてCDP、CDIを表す。Cfは形状抵抗係数、誘導抵抗係数、揚力係数それぞれについて、Cdp、Cdi、Clを表し、Cf*Cは各係数と翼弦長の積を表す。cfは、形状抵抗係数、誘導抵抗係数それぞれについて、cdp、cdiを表し、WAは積分領域が後流領域であることを示す。
また、物体後流の３成分速度分布を計測する手法として、粒子画像流速測定法、レーザドップラ流速計、２焦点式レーザ流速計、ドップラーグローバル流速計、レーザ誘起蛍光法、超音波流速計のいずれかを用いることにより、流体の流れを変化させることなく計測するようにした。
本発明は、上記方法において流れと交叉する複数方向の計測面における物体後流の３成分速度分布値を総合することにより、流れ方向の速度変化に対し、高精度の圧力分布を推算するものとした。 The method of measuring the shape resistance, the induction resistance and the lift distribution acting on the object of the present invention includes a step of measuring a three-component velocity distribution of the wake of the object existing in the fluid field, and the three-component velocity distribution value as input. The step of calculating the pressure distribution by the numerical fluid analysis method, and the shape resistance, the induction resistance and the lift distribution acting on the object are calculated by the wake integration method using the three-component velocity distribution value and the pressure distribution value. I made it.
The method of measuring the fluid force (drag and lift) acting on the object of the present invention is to integrate the shape resistance, induction resistance and lift distribution acting on the object obtained by the method according to claim 1 by the following equation. To measure drag and lift acting on an object.
However, CF represents CD and CL for drag coefficient and lift coefficient, respectively, and CDP and CDI for shape resistance coefficient and induction resistance coefficient, respectively. Cf represents Cdp, Cdi, and Cl for each of the shape resistance coefficient, the induction resistance coefficient, and the lift coefficient, and Cf * C represents the product of each coefficient and the chord length. cf represents cdp and cdi for the shape resistance coefficient and the induction resistance coefficient, respectively, and WA indicates that the integration region is the wake region.
In addition, as a method for measuring the three-component velocity distribution in the wake of an object, any of particle image velocimetry, laser Doppler velocimeter, bifocal laser velocimeter, Doppler global velocimeter, laser induced fluorescence method, and ultrasonic velocimeter By using this, measurement was made without changing the flow of fluid.
The present invention estimates the pressure distribution with high accuracy with respect to the velocity change in the flow direction by integrating the three component velocity distribution values of the wake of the object on the measurement surface in a plurality of directions intersecting with the flow in the above method. did.

本発明の物体に作用する形状抵抗、誘導抵抗及び揚力分布を計測する装置は、流体場に存する物体の後流の３成分速度分布を計測する手段と、前記３成分速度分布値を入力として、数値流体解析手法により、圧力分布を計算する手段と、前記３成分速度分布値と前記圧力分布値を用いて後流積分法により、形状抵抗、誘導抵抗及び揚力分布を算出する手段とを備えるものとした。
本発明の模型に作用する抗力及び揚力を計測する装置は、風洞内に模型とシーディングジェネレータを配置すると共に、前記模型の後方部にレーザーライトシートを形成する手段と、該レーザーライトシートを異なる角度から撮影するステレオカメラと、制御用パソコンとを備えたものであって、該制御用パソコンはステレオ画像情報から３成分速度分布を、該３成分速度分布値を入力として数値流体解析手法により圧力分布を、前記３成分速度分布値と前記圧力分布値を用いて後流積分法により形状抵抗、誘導抵抗及び揚力分布を、さらには、これを積分することにより、抗力及び揚力を計測するようにした。 The apparatus for measuring the shape resistance, the induction resistance and the lift distribution acting on the object of the present invention has means for measuring the three-component velocity distribution of the wake of the object existing in the fluid field, and the three-component velocity distribution value as an input. Means for calculating pressure distribution by a numerical fluid analysis method, and means for calculating shape resistance, induction resistance and lift distribution by wake integration using the three-component velocity distribution value and the pressure distribution value It was.
The apparatus for measuring drag and lift acting on the model of the present invention is different from the laser light sheet in that a model and a seeding generator are arranged in a wind tunnel and a laser light sheet is formed in the rear part of the model. A stereo camera that captures an image from an angle and a control personal computer, the control personal computer uses a three-component velocity distribution from the stereo image information and inputs the three-component velocity distribution value as a pressure by a numerical fluid analysis method. Using the three-component velocity distribution value and the pressure distribution value, the shape resistance, the induction resistance and the lift distribution are calculated by the wake integration method, and the drag and the lift are measured by integrating the distribution. did.

本発明の計測方法及び計測装置は、計測方法として、ＰＩＶやレーザードップラー流速計(ＬＤＶ)を使用することで、圧力プローブ等を使用する場合と異なり、流れを変化させることなく、計測が行えるため、より正確な空気力分布を求めることができる。
本発明の計測方法及び計測装置は、１回の計測で、２次元平面の計測が可能なため、ＰＩＶ等における圧力プローブ等の１点１点の計測と異なり、計測時間が大幅に短縮される。
本発明の計測方法及び計測装置は、得られる速度分布のみでは、抵抗成分を直接計測することはできないが、速度分布から圧力分布を推算する手法を採用することにより、抵抗成分を推定することが可能となる。 The measurement method and measurement apparatus of the present invention can measure without changing the flow by using PIV or a laser Doppler velocimeter (LDV) as a measurement method, unlike when using a pressure probe or the like. More accurate aerodynamic force distribution can be obtained.
Since the measurement method and the measurement apparatus of the present invention can measure a two-dimensional plane in one measurement, the measurement time is greatly shortened unlike measurement of one point such as a pressure probe in PIV or the like. .
Although the measuring method and measuring device of the present invention cannot directly measure the resistance component only by the obtained velocity distribution, the resistance component can be estimated by adopting a method of estimating the pressure distribution from the velocity distribution. It becomes possible.

本発明の計測・演算ステップを説明するフローチャートである。It is a flowchart explaining the measurement and calculation step of this invention. 本発明が使用する風洞における粒子画像流速測定(ＰＩＶ)法による計測システムのモデルを示す図である。It is a figure which shows the model of the measurement system by the particle image velocimetry (PIV) method in the wind tunnel which this invention uses. 風洞に設置された本発明の流体力分布計測装置を説明する図である。It is a figure explaining the fluid force distribution measuring apparatus of this invention installed in the wind tunnel. 本発明で計測した３成分速度分布を示す図である。It is a figure which shows 3 component velocity distribution measured by this invention. 本発明で計測した３成分速度分布を用い、数値流体解析手法によって、空間圧力分布を計算した結果を示す図である。It is a figure which shows the result of having calculated spatial pressure distribution by the numerical fluid analysis method using the three-component velocity distribution measured by this invention. 得られた３成分速度分布と空間圧力分布を用いて、後流積分法により、計算された形状抵抗分布を示すグラフである。It is a graph which shows the shape resistance distribution calculated by the wake integration method using the obtained three-component velocity distribution and spatial pressure distribution. 得られた３成分速度分布と空間圧力分布を用いて、後流積分法により、計算された誘導抵抗分布を示すグラフである。It is a graph which shows the induced resistance distribution calculated by the wake integration method using the obtained three-component velocity distribution and spatial pressure distribution. 得られた３成分速度分布と空間圧力分布を用いて、後流積分法により、計算された揚力分布を示すグラフである。It is a graph which shows the lift distribution calculated by the wake integration method using the obtained three-component velocity distribution and spatial pressure distribution. 得られた３成分速度分布と空間圧力分布を用いて、後流積分法により、計算された後流断面における形状抵抗分布を示す図である。It is a figure which shows the shape resistance distribution in the wake flow cross section calculated by the wake flow integration method using the obtained three-component velocity distribution and space pressure distribution. 得られた３成分速度分布と空間圧力分布を用いて、後流積分法により、計算された後流断面における誘導抵抗分布を示す図である。It is a figure which shows the induced resistance distribution in the wake flow cross section calculated by the wake integration method using the obtained three-component velocity distribution and spatial pressure distribution.

以下、本発明の実施の形態について、詳細に説明する。
第１ステップでは物体が配置されている流体場において、物体後流の３成分速度分布を計測する。３成分速度分布計測は、流れ方向に１または複数の面を対象とする。また、３成分速度分布計測では、流れを変化させることなく、計測が可能な方法として、ステレオＰＩＶ、ＬＧＶ、２焦点式レーザ流速計(Ｌ２Ｆ)、ドップラーグローバル流速計(ＤＧＶ)、レーザ誘起蛍光法(ＬＩＦ)、超音波流速計等を用いる。ステレオＰＩＶを使った方法では、短時間のデータ取得で、広範囲の３成分速度分布を計測することが可能である。 Hereinafter, embodiments of the present invention will be described in detail.
In the first step, the three-component velocity distribution of the wake of the object is measured in the fluid field where the object is arranged. The three-component velocity distribution measurement targets one or more surfaces in the flow direction. In three-component velocity distribution measurement, stereo PIV, LGV, bifocal laser anemometer (L2F), Doppler global anemometer (DGV), laser-induced fluorescence method can be used without changing the flow. (LIF), an ultrasonic current meter or the like is used. In the method using the stereo PIV, it is possible to measure a wide range of three-component velocity distribution by acquiring data in a short time.

第２のステップでは、数値流体解析手法を用いて、１つのｙ−ｚ平面内の３成分速度場から、空間圧力分布を計算する。本手法は、物体の後流においては、主流方向(ｘ方向)の流れは、主流に垂直な方向(ｙ及びｚ方向)と比較して変化が少なく、主流方向(ｘ方向)の流れの状態量の変化はｙ方向やｚ方向の変化に比べて十分小さいということを仮定している。主流(ｘ軸)方向の圧力及び速度勾配を０と仮定し、時間については定常と仮定すると、圧力のPoisson方程式は(１)のようになり、これに、ＰＩＶにより計測された空間速度場データを式(１)の右辺に代入し、差分法により、圧力を求める。
In the second step, a spatial pressure distribution is calculated from a three-component velocity field in one yz plane using a numerical fluid analysis method. In this method, in the wake of an object, the flow in the main flow direction (x direction) is less changed compared to the direction perpendicular to the main flow (y and z directions), and the flow state in the main flow direction (x direction) It is assumed that the change in quantity is sufficiently small compared to the change in the y direction or the z direction. Assuming that the pressure and velocity gradient in the main flow (x-axis) direction is 0 and the time is assumed to be steady, the Poisson equation of pressure is as shown in (1), and the space velocity field data measured by PIV Is substituted into the right side of Equation (1), and the pressure is obtained by the difference method.

第３ステップで、後流積分法を使用して、抗力係数ＣＤと揚力係数ＣＬを算出する。その際、３成分速度分布に加え、３成分速度分布から求めた圧力推算値を使用し、以下に示す演算式に基づいてそれぞれの物理量を算出する。
抗力係数ＣＤは、次式より求める。
ここで、ＣＤＰ、ＣＤＩ、ＣＤＰ２は、それぞれ形状抵抗係数、誘導抵抗係数、２次形状抵抗係数を表す。Ｏ(Δ３)は、３次の微小量を表し、本計測では無視できる。よって、抗力係数ＣＤは、形状抵抗係数ＣＤＰ、誘導抵抗係数ＣＤＩ、２次形状抵抗係数ＣＤＰ２の和として求める。 In the third step, the drag coefficient CD and the lift coefficient CL are calculated using the wake integration method. At that time, in addition to the three-component velocity distribution, the pressure estimated value obtained from the three-component velocity distribution is used, and each physical quantity is calculated based on the following arithmetic expression.
The drag coefficient CD is obtained from the following equation.
Here, CDP, CDI, and CDP2 represent a shape resistance coefficient, an induction resistance coefficient, and a secondary shape resistance coefficient, respectively. O (Δ 3 ) represents a third-order minute amount and can be ignored in this measurement. Therefore, the drag coefficient CD is obtained as the sum of the shape resistance coefficient CDP, the induction resistance coefficient CDI, and the secondary shape resistance coefficient CDP2.

形状抵抗係数ＣＤＰは、以下の式で表される。
ここで、右辺分母は動圧、Ｓは代表面積を表す。Ｐ∞、ρ∞、Ｕ∞は、それぞれ、一様流の静圧、密度、速度、Δｓはエントロピの変化量、Ｒは気体定数を表す。また、WAは積分領域が後流領域であることを表す。 The shape resistance coefficient CDP is expressed by the following equation.
Here, the right side denominator represents the dynamic pressure, and S represents the representative area. P ∞ , ρ ∞ , and U ∞ are the static pressure, density, and velocity of uniform flow, Δs is the amount of change in entropy, and R is the gas constant. WA represents that the integration region is the wake region.

誘導抵抗係数ＣＤＩは次の式で表される。ここで、次式の誘導抵抗は、Maskellの誘導抵抗である。
ここで、xは渦度の一様流方向成分を表す。yおよびfは、次式を満たすスカラ関数である。
The induction resistance coefficient CDI is expressed by the following equation. Here, the induction resistance of the following equation is Maskell's induction resistance.
Here, x represents a uniform flow direction component of vorticity. y and f are scalar functions that satisfy the following expression.

２次形状抵抗係数ＣＤＰ２は、次式のように表される。
The secondary shape resistance coefficient CDP2 is expressed as follows.

揚力係数ＣＬは、次式より求める。
The lift coefficient CL is obtained from the following equation.

図３に示す実際の風洞実験の計測結果では、抗力係数ＣＤ、形状抵抗係数ＣＤＰ、誘導抵抗係数ＣＤＩと揚力係数ＣＬを示した。なお、２次形状抵抗係数ＣＤＰ２は、その値が１カウント程度であったため、今回の結果には含めなかった。また、形状抵抗と誘導抵抗及び揚力に関しては、翼断面(翼をｙ＝一定値でカットしたもの)での各係数と翼弦長の積Ｃｆ＊Ｃのスパン方向分布を示した。さらに、形状抵抗と誘導抵抗に関しては、後流領域の局所の抗力係数ｃｆをｙ−ｚ断面の２次元分布図として示した。各係数の定義は次式の通りである。ここで、ＣＦ及びＣｆは、形状抵抗係数、誘導抵抗係数、揚力係数それぞれについて、ＣＤＰ、ＣＤＩ、ＣＬ及び、Ｃｄｐ、Ｃｄｉ、Ｃｌを表し、ｃｆは形状抵抗係数、誘導抵抗係数それぞれについて、ｃｄｐ、ｃｄｉを表す。
なお、Ｃｆは後流積分法によって求めることができるもので、翼断面（翼をｙ＝一定値でカットしたもの）に働く抵抗・揚力を表し、断面抗力係数(cross-sectional Profile-drag coefficient) ＣＤＰ、ＣＤＩが該当する。そして、ｃｆは後流積分法で、後流断面(ｙ−ｚ面)における局所の形状抵抗及び誘導抵抗を表し、ｃｄｉ、ｃｄｐが該当する。 In the measurement result of the actual wind tunnel experiment shown in FIG. 3, the drag coefficient CD, the shape resistance coefficient CDP, the induction resistance coefficient CDI, and the lift coefficient CL are shown. The secondary shape resistance coefficient CDP2 was not included in this result because the value was about 1 count. In addition, regarding the shape resistance, induction resistance, and lift force, the distribution in the span direction of the product Cf * C of each coefficient and the chord length in the blade cross section (the blade cut with y = constant value) is shown. Further, regarding the shape resistance and the inductive resistance, the local drag coefficient cf in the wake region is shown as a two-dimensional distribution diagram of the yz section. The definition of each coefficient is as follows. Here, CF and Cf represent CDP, CDI, CL and Cdp, Cdi, and Cl for the shape resistance coefficient, the induction resistance coefficient, and the lift coefficient, respectively, and cf represents the cdp, represents cdi.
Cf can be obtained by the wake integration method, and represents the resistance and lift acting on the blade cross section (the blade cut with y = constant value), and the cross-sectional profile-drag coefficient. CDP and CDI are applicable. Cf is a wake integration method, which represents local shape resistance and induction resistance in the wake cross section (yz plane), and corresponds to cdi and cdp.

風洞試験において、図２のようなステレオＰＩＶ装置を用いて、風洞試験模型の後流の３成分速度分布を計測した。ステレオＰＩＶ装置は、ＰＩＶカメラ２台、ダブルパルスNd:YAGレーザ及び制御用ＰＣから構成されており、シーディングジェネレータによって発生させたシード粒子を風洞内に導入し、風路全域に分散させた。シーディングジェネレータは測定部の後方に設置されているが、ここで導入されたシード粒子は循環される過程で風路全域に一様な分布となって測定部に流入されることとなる。レーザはシート光学系により、シート状に広げて照射されることにより、風路内に分散したシード粒子が、ＰＩＶカメラによって撮影される。ＰＩＶカメラとダブルパルスNd:YAGレーザとは制御用ＰＣによって、同期信号が送られ、ＰＩＶカメラで撮影される２枚１組の画像のそれぞれにおいて、１回、レーザが発光するように制御されており、２回の発光の間にシード粒子が移動する移動量を撮影された画像から、画像解析により計測し、その移動量を発光間隔で割って、速度を算出する。２台のカメラそれぞれにおいて計測された２次元速度分布は、事前に行ったカメラキャリブレーションで求められたカメラパラメータによって、３成分速度分布（一般にはｘ，ｙ，ｚ直交座標成分）に変換される。   In the wind tunnel test, the ternary velocity distribution in the wake of the wind tunnel test model was measured using a stereo PIV apparatus as shown in FIG. The stereo PIV apparatus is composed of two PIV cameras, a double pulse Nd: YAG laser, and a control PC. The seed particles generated by the seeding generator are introduced into the wind tunnel and dispersed throughout the wind path. The seeding generator is installed behind the measurement unit, but the seed particles introduced here are introduced into the measurement unit in a uniform distribution over the entire air path in the process of circulation. The laser is spread and irradiated in a sheet form by the sheet optical system, and the seed particles dispersed in the air path are photographed by the PIV camera. The PIV camera and the double pulse Nd: YAG laser are controlled by the control PC so that the synchronization signal is sent and the laser is emitted once in each of a pair of images taken by the PIV camera. In addition, the amount of movement of the seed particles between the two times of light emission is measured by image analysis from the captured image, and the speed is calculated by dividing the amount of movement by the light emission interval. The two-dimensional velocity distribution measured by each of the two cameras is converted into a three-component velocity distribution (generally, x, y, z orthogonal coordinate components) according to camera parameters obtained by camera calibration performed in advance. .

本実施例では、図３のような航空機模型を計測対象とした風洞試験を実施した。図２のＰＩＶシステムモデルはレーザーライトシートを前後から挟むようにＰＩＶカメラが設置されているが、本実験の場合ＰＩＶカメラは測定部の下流レーザーライトシートの左右後方から撮影するように設置され、計測面の撮影を行った。この実施例では、１回の計測では、計測面全体を計測することができなかったため、計測面を複数に分けて、計測することで、計測面全体の撮影を行った。この風洞試験によって計測された３成分速度分布を図４に示す。上段が主流方向の速度(ｕ)分布、中段が横方向の速度(ｖ)分布、そして下段が上下方向の速度(ｗ)分布である。
図４で示された３成分速度分布を入力として、数値流体解析手法を用いて、空間圧力分布を計算した結果を図５に示す。図４で示された３成分速度分布と図５で示された空間圧力分布を入力とし、後流積分法を使用して、計算された形状抵抗分布(Ｃｄｐ＊Ｃ)、誘導抵抗分布(Ｃｄｉ＊Ｃ)及び揚力分布(Ｃｌ＊Ｃ)を図６〜８、また、後流積分法を使用して計算された後流断面での形状抵抗分布(ｃｄｐ)及び誘導抵抗分布(ｃｄｉ)を図９、１０に示す。図６より、模型中心部分と翼の左右で形状抵抗が大きいことが分かり、さらに、図９の後流断面の分布では、より明確に模型と形状抵抗の対応が明確にわかる。図７より、翼端付近で誘導抵抗が大きいことが分かり、図１０の後流断面の分布でも同様の結果となっている。 In the present example, a wind tunnel test was performed on an aircraft model as shown in FIG. In the PIV system model of FIG. 2, the PIV camera is installed so that the laser light sheet is sandwiched from the front and back, but in the case of this experiment, the PIV camera is installed so as to shoot from the left and right rear of the downstream laser light sheet of the measurement unit. The measurement surface was photographed. In this example, since the entire measurement surface could not be measured by one measurement, the entire measurement surface was photographed by dividing the measurement surface into a plurality of measurements. FIG. 4 shows a three-component velocity distribution measured by this wind tunnel test. The upper row is the velocity (u) distribution in the mainstream direction, the middle row is the velocity (v) distribution in the horizontal direction, and the lower row is the velocity (w) distribution in the vertical direction.
FIG. 5 shows the result of calculating the spatial pressure distribution using the numerical fluid analysis method with the three-component velocity distribution shown in FIG. 4 as an input. Using the three-component velocity distribution shown in FIG. 4 and the spatial pressure distribution shown in FIG. 5 as inputs, the calculated shape resistance distribution (Cdp * C), induced resistance distribution (Cdi) using the wake integration method. * C) and lift distribution (Cl * C) are shown in FIGS. 6 to 8, and the shape resistance distribution (cdp) and induced resistance distribution (cdi) in the wake cross section calculated using the wake integration method are shown. 9 and 10. From FIG. 6, it can be seen that the shape resistance is large between the left and right sides of the model center and the wing, and further, the distribution of the wake cross section of FIG. 9 clearly shows the correspondence between the model and the shape resistance. From FIG. 7, it can be seen that the induced resistance is large in the vicinity of the blade tip, and the distribution of the wake cross section of FIG.

本明細書では航空機に作用する空力を例に説明してきたが、本発明はこれに限らず、航空宇宙、自動車、鉄道車両、船舶、建築物、風車、生物、スポーツ等の空力設計において、模型を使った風洞実験を実施する際に、本計測方法及び装置を利用することにより、物体の各構成要素における形状抵抗、誘導抵抗及び揚力の分布を知ることで、空力設計の妥当性評価及び、各流体力の発生要因の把握が可能となる。
物体の各構成要素における流体力の分布を知ることで、空力設計において、抗力及び揚力を低下あるいは増大させることを目的とした装置の効果を直接評価することが可能となる。
本発明の計測方法及び装置を使うことで、天秤を使った空気力計測が困難な状況においても、その物体の後流を計測することで、抗力と揚力を計測することができる。 In the present specification, aerodynamics acting on an aircraft has been described as an example. However, the present invention is not limited to this, and in aerodynamic design of aerospace, automobiles, railway vehicles, ships, buildings, windmills, living things, sports, etc. By using this measurement method and device when carrying out wind tunnel experiments using, we can evaluate the validity of aerodynamic design by knowing the distribution of shape resistance, induction resistance and lift in each component of the object, and It is possible to grasp the cause of each fluid force.
Knowing the distribution of fluid forces in each component of an object makes it possible to directly evaluate the effectiveness of a device aimed at reducing or increasing drag and lift in aerodynamic design.
By using the measurement method and apparatus of the present invention, drag and lift can be measured by measuring the wake of the object even in situations where it is difficult to measure aerodynamic force using a balance.

Jewel B. Barolow, William H. Rae, Jr., Alan Pope, “Low-Speed Wind Tunnel Testing”,Wiley-Interscience 1999年発行Jewel B. Barolow, William H. Rae, Jr., Alan Pope, “Low-Speed Wind Tunnel Testing”, published by Wiley-Interscience 1999 Kazuhiro Kusunose, “A Wake Integration Method for Airplane Drag Prediction”, Tohoku University Press 2005年発行Kazuhiro Kusunose, “A Wake Integration Method for Airplane Drag Prediction”, Tohoku University Press 2005 Markus Raffel, Jurgen Kompenhans, Christian E. Willert, 小林 敏雄(監修), 岡本孝司(翻訳), 西尾茂(翻訳), 川橋正昭(翻訳),小林敏雄(監修), 「PIVの基礎と応用―粒子画像流速測定法」、シュプリンガー・フェアラーク東京 2000年6月20日発行Markus Raffel, Jurgen Kompenhans, Christian E. Willert, Toshio Kobayashi (supervised), Takashi Okamoto (translation), Shigeru Nishio (translation), Masaaki Kawahashi (translation), Toshio Kobayashi (supervision), `` PIV Basics and Applications-Particle Image "Flow velocity measurement method", Springer Fairlark Tokyo, June 20, 2000 麻生智大、松島紀佐、中橋和博、「PIV風洞実験結果によるCFDの圧力推定」、航空宇宙数値シミュレーション技術シンポジウム2006論文集、pp.56-59 2006年6月23日Tomohiro Aso, Kisa Matsushima, Kazuhiro Nakahashi, “Pressure Estimation of CFD Based on PIV Wind Tunnel Experiment Results”, Aerospace Numerical Simulation Symposium 2006, pp.56-59 June 23, 2006

Claims (6)

流体場に存する物体の後流の３成分速度分布を計測するステップと、前記３成分速度分布値を入力として、数値流体解析手法により、圧力分布を計算するステップと、前記３成分速度分布値と前記圧力分布値を用いて後流積分法により、物体に作用する形状抵抗、誘導抵抗及び揚力分布を算出して得る方法。   A step of measuring a three-component velocity distribution of the wake of an object existing in a fluid field; a step of calculating a pressure distribution by a numerical fluid analysis method using the three-component velocity distribution value as an input; and the three-component velocity distribution value; A method of calculating and obtaining shape resistance, induction resistance and lift distribution acting on an object by a wake integration method using the pressure distribution value. 請求項１に記載の方法によって得られた物体に作用する形状抵抗、誘導抵抗及び揚力分布を次式により積分することにより、物体に作用する抗力及び揚力を計測する方法。
ただし、CFは抗力係数、揚力係数それぞれについてCD、CLを表し、形状抵抗係数、誘導抵抗係数それぞれについてCDP、CDIを表す。Cfは形状抵抗係数、誘導抵抗係数、揚力係数それぞれについて、Cdp、Cdi、Clを表し、Cf*Cは各係数と翼弦長の積を表す。cfは、形状抵抗係数、誘導抵抗係数それぞれについて、cdp、cdiを表し、WAは積分領域が後流領域であることを示す。 A method for measuring drag and lift acting on an object by integrating shape resistance, induction resistance and lift distribution acting on the object obtained by the method according to claim 1 according to the following equations.
However, CF represents CD and CL for drag coefficient and lift coefficient, respectively, and CDP and CDI for shape resistance coefficient and induction resistance coefficient, respectively. Cf represents Cdp, Cdi, and Cl for each of the shape resistance coefficient, the induction resistance coefficient, and the lift coefficient, and Cf * C represents the product of each coefficient and the chord length. cf represents cdp and cdi for the shape resistance coefficient and the induction resistance coefficient, respectively, and WA indicates that the integration region is the wake region. 物体後流の３成分速度分布を流体の流れを変化させることなく計測する手法として、粒子画像流速測定法、レーザドップラ流速計、２焦点式レーザ流速計、ドップラーグローバル流速計、レーザ誘起蛍光法、超音波流速計のいずれかを用いて計測した請求項１に記載の形状抵抗、誘導抵抗及び揚力分布を計測する方法。   Particle image velocimetry, laser Doppler velocimeter, two-focus laser velocimeter, Doppler global velocimeter, laser-induced fluorescence method, as a method to measure the three-component velocity distribution of the wake of the object without changing the fluid flow, The method of measuring shape resistance, induction resistance, and lift distribution according to claim 1, which is measured using any one of ultrasonic velocimeters. 流れと交叉する複数方向の計測面における物体後流の３成分速度分布値を総合することにより、流れ方向の速度変化に対し、高精度の圧力分布を推算する請求項１に記載の形状抵抗、誘導抵抗及び揚力分布を計測する方法。   The shape resistance according to claim 1, wherein a high-precision pressure distribution is estimated with respect to a velocity change in the flow direction by integrating three-component velocity distribution values of the object wake on a measurement surface in a plurality of directions intersecting with the flow. A method of measuring induction resistance and lift distribution. 流体場に存する物体の後流の３成分速度分布を計測する手段と、前記３成分速度分布値を入力として、数値流体解析手法により、圧力分布を計算する手段と、前記３成分速度分布値と前記圧力分布値を用いて後流積分法により、形状抵抗、誘導抵抗及び揚力分布を算出する手段とを備えた物体に作用する形状抵抗、誘導抵抗及び揚力分布を計測する装置。   Means for measuring the three-component velocity distribution of the wake of the object in the fluid field, means for calculating the pressure distribution by the numerical fluid analysis method using the three-component velocity distribution value as input, and the three-component velocity distribution value; An apparatus for measuring shape resistance, induction resistance and lift distribution acting on an object having means for calculating shape resistance, induction resistance and lift distribution by wake integration using the pressure distribution value. 風洞内に模型とシーディングジェネレータを配置すると共に、前記模型の後方部にレーザーライトシートを形成する手段と、該レーザーライトシートを異なる角度から撮影するステレオカメラと、制御用パソコンとを備えたものであって、該制御用パソコンはステレオ画像情報から３成分速度分布を、該３成分速度分布値を入力として数値流体解析手法により圧力分布を、前記３成分速度分布値と前記圧力分布値を用いて後流積分法により形状抵抗、誘導抵抗及び揚力分布を、さらには、これを積分することにより、物体に作用する抗力及び揚力を計測する装置。   A model and a seeding generator are arranged in a wind tunnel, provided with means for forming a laser light sheet at the rear of the model, a stereo camera for photographing the laser light sheet from different angles, and a control personal computer The personal computer for control uses a three-component velocity distribution from stereo image information, a pressure distribution by a numerical fluid analysis method using the three-component velocity distribution value as an input, and the three-component velocity distribution value and the pressure distribution value. An apparatus for measuring drag and lift acting on an object by integrating the shape resistance, induction resistance and lift distribution by the wake integration method.
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