等离子体气动激励机理数值研究

基于介质阻挡与准直流电弧放电的物理过程, 分析了它们的气动激励机理, 建立了各自的气动激励模型, 并分别研究了它们对低速和超声速流动的激励效果. 结果显示: 介质挡板放电等离子体气动激励机理是改变了连续流体中的三种力, 即由牛顿内摩擦引起的剪切应力、由电动力学引起的体积力及由压力突变引起的冲击力, 其中基于电动力学的体积力效应占主导地位; 临近空间环境中体积力的作用效果更强, 诱导速度更大; 超声速来流下准直流电弧放电气动激励机理主要是等离子体的热阻塞效应, 本文所建立的爆炸丝传热模型可以用于仿真其控制激波的过程; 热电弧对于超声速来流而言就像一个具有一定斜坡角度的虚拟突起, 可用于高超声速飞行器前体激波的控制.     

The characteristics of surface arc plasma and its control effect on supersonic flow

The characteristic of surface arc plasma included millisecond and microsecond actuation in supersonic flow is investigated both experimentally and numerically. In the experiment, the discharge characteristic of surface arc plasma in quiescent air and supersonic flow is recorded. The stable oblique shock could be observed with millisecond actuation. And the unstable compressive wave could be also observed with microsecond actuation. In the numerical investigation, plasma actuation is defined as a source term with input power density from discharge V–I characteristic, which is expected to better describe the influence of heating process. The numerical results are coincident with experimental results. In order to confirm the capability of surface arc plasma actuation to control supersonic flow, experimental investigations on control shock induced by ramp and separation of boundary layer induced by impinging shock are performed. All the results demonstrate the control effect of surface arc plasma actuation onto supersonic flow.     

Experimental investigation of nanosecond discharge plasma aerodynamic actuation

In this paper we report on an experimental study of the characteristics of nanosecond pulsed discharge plasma aerodynamic actuation. The N 2 (C 3 Π u ) rotational and vibrational temperatures are around 430 K and 0.24 eV, respectively. The emission intensity ratio between the first negative system and the second positive system of N 2 , as a rough indicator of the temporally and spatially averaged electron energy, has a minor dependence on applied voltage amplitude. The induced flow direction is not parallel, but vertical to the dielectric layer surface, as shown by measurements of body force, velocity, and vorticity. Nanosecond discharge plasma aerodynamic actuation is effective in airfoil flow separation control at freestream speeds up to 100 m/s.     

激波/边界层干扰对等离子体合成射流的响应特性

利用高速纹影系统和数值模拟方法研究了激波/边界层干扰对逆流喷射的等离子体合成射流的响应特性,并揭示了流动控制机理.实验在来流马赫数Ma=3.1的风洞中进行,测试模型采用钝头体和压缩斜坡的组合模型,等离子体合成射流激励器安装在钝头体头部.纹影系统捕捉了放电频率为f=1 kHz和f=3 kHz的激励对附体激波形态和分离激波运动的控制效果.等离子体合成射流使压缩斜坡激波/边界层干扰区域的起始点向下游移动,分离泡尺寸减小,附体激波强度减弱,发生弯曲,再附点移向上游,与此同时分离激波向附体激波逼近.与f=3 kHz激励相比,f=1 kHz激励的射流流量更大,对激波/边界层干扰的影响范围更广、控制效果更好.通过数值模拟,揭示了射流与来流相互作用对下游流场的作用机理:射流与来流相互作用诱导出大尺度旋涡,大尺度旋涡耗散发展增强了近壁面流场的湍流度;压缩斜坡上游近壁面的流场性质发生变化,进而导致了压缩斜坡激波/边界层干扰区域流动的变化.     

电弧放电等离子体诱导激波的计算

基于电弧放电物理过程,分析气动激励机理,建立用于电弧放电等离子体诱导激波数值模拟的爆炸丝传热模型.主要结论有:电弧放电等离子体气动激励的主要机理是热等离子体的热阻塞效应,热电弧放电对于超声速来流而言就像-个具有-定斜坡角度的虚拟突起;理论分析只适用于纵坐标较小的阶段;当传热的功率设为放电功率的10%时,本文所建立的模型能够用于电弧放电等离子体诱导激波的仿真研究;等离子体虚拟斜坡角度及其诱导激波角都随来流总压和速度的增大而减小,随着放电功率的增大而增大,在总压、速度和放电功率较小的阶段这种变化较明显,在总压、速度和放电功率较大的阶段这种变化较缓慢.     

Aerodynamic actuation characteristics of radio-frequency discharge plasma and control of supersonic flow

In this paper, aerodynamic actuation characteristics of radio-frequency(RF) discharge plasma are studied and a method is proposed for shock wave control based on RF discharge. Under the static condition, a RF diffuse glow discharge can be observed; under the supersonic inflow, the plasma is blown downstream but remains continuous and stable.Time-resolved schlieren is used for flow field visualization. It is found that RF discharge not only leads to continuous energy deposition on the electrode surface but also induces a compression wave. Under the supersonic inflow condition, a weak oblique shock wave is induced by discharge. Experimental results of the shock wave control indicate that the applied actuation can disperse the bottom structure of the ramp-induced oblique shock wave, which is also observed in the extracted shock wave structure after image processing. More importantly, this control effect can be maintained steadily due to the continuous high-frequency(MHz) discharge. Finally, correlations for schlieren images and numerical simulations are employed to further explore the flow control mechanism. It is observed that the vortex in the boundary layer increases after the application of actuation, meaning that the boundary layer in the downstream of the actuation position is thickened. This is equivalent to covering a layer of low-density smooth wall around the compression corner and on the ramp surface, thereby weakening the compressibility at the compression corner. Our results demonstrate the ability of RF plasma aerodynamic actuation to control the supersonic airflow.     

Dynamic evolution of vortex structures induced by tri-electrode plasma actuator

Plasma flow control is a new type of active flow control approach based on plasma pneumatic actuation.Dielectric barrier discharge(DBD) actuators have become a focus of international aerodynamic research.However,the practical applications of typical DBDs are largely restricted due to their limited discharge area and low relative-induced velocity.The further improvement of performance will be beneficial for engineering applications.In this paper,high-speed schlieren and high-speed particle image velocimetry(PIV) are employed to study the flow field induced by three kinds of plasma actuations in a static atmosphere,and the differences in induced flow field structure among typical DBD,extended DBD(EX-DBD),and tri-electrode sliding discharge(TED) are compared.The analyzing of the dynamic evolution of the maximum horizontal velocity over time,the velocity profile at a fixed horizontal position,and the momentum and body force in a control volume reveals that the induced velocity peak value and profile velocity height of EX-DBD are higher than those of the other two types of actuation,suggesting that EX-DBD actuation has the strongest temporal aerodynamic effect among the three types of actuations.The TED actuation not only can enlarge the plasma extension but also has the longest duration in the entire pulsed period and the greatest influence on the height and width of the airflow near the wall surface.Thus,the TED actuation has the ability to continuously influencing a larger three-dimensional space above the surface of the nlasma actuator.     

基于等离子体气动激励的斜劈诱导激波控制

基于弧光等离子体气动激励,采用不同的放电通道间距、放电通道数、放电直流输入电压、斜劈劈角、有无磁场作用等激励条件,实验研究了在超音速来流条件下(马赫数为2.2)斜激波位置、角度、强度的变化规律。结果表明:施加等离子体气动激励后,激波的起始位置平均前移1～8 mm,激波角平均减小4%～8%,激波强度平均减弱8%～26%。这主要是由于等离子体气动激励产生高温高压的表面等离子体层,使边界层分离点逆气流前移,改变了原有激波系结构,使原有的激波位置前移,激波角减小;同时由于局部的高温导致当地音速增大,使得当地马赫数减小,上述两个原因均可导致激波强度减弱。     

介质阻挡放电等离子体与激波相互作用实验研究

 主要针对介质阻挡放电等离子体改变激波系结构展开了实验研究。验证了介质阻挡放电等离子体气动激励能够对边界层施加影响,顺气流放电时能减小激波强度,逆气流放电时能增大激波强度。逆气流放电时,3组电极放电与4组电极放电比较,3组电极放电时压比更高。由于在该实验中放电区域比边界层小得多,介质阻挡放电产生的体积力远小于高速来流条件下的气动力,因此对激波的作用效果十分微弱。     

Pressure dynamics in a supersonic flow during initiation of pulse surface sliding discharges

The supersonic air flow at Mach numbers of 1.1–1.6 in a shock tube is experimentally investigated during initiation of nanosecond pulse surface sliding discharges. The shadow images of the flow field after discharge initiation, which characterize the dynamics of shock waves propagating from the discharge area, are obtained. Periodic pressure pulsations on the shock tube channel wall are recorded. The pressure dynamics is shown to correspond to both the motion of shock waves from the discharge area and a supersonic flow of the discharge-excited gas near the channel wall. The pressure increase on the shock tube channel wall was 6–18%, as compared to the pressure in an unperturbed flow. Original Russian Text ? D.F. Latfullin, I.V. Mursenkova, N.N. Sysoev, 2009, published in Vestnik Moskovskogo Universiteta. Fizika, 2009, No. 3, pp. 114–116.     

Analysis of Plasmadynamic Nanosecond-Range Processes in the Formation of Shock Waves from Pulsed Discharges

We have studied the dynamics of the plasma glow of pulsed discharges (sliding surface discharge and combined volume discharge with plasma electrodes) in the nanosecond range (100–12 000 ns) in stationary air and in the flow behind the front of a plane shock wave with Mach numbers 1.7–5.0 in the shock tube channel. The temporal characteristics of the flow, the radiation spectra, and the discharge currents in air are compared in the pressure range 5–150 Torr, a pulsed voltage of 20–30 kV, and a current of about 1 kA. It is shown that the time of current under various conditions does not exceed 400 ns, and the duration of the glow can reach a few microseconds. It is shown that as a result of energy supply near the planar shock wave front, the decay of discontinuities occurs with the formation of shock waves and contact surfaces. The positions of the plasma glow regions are compared with the positions of discontinuity surfaces of numerically calculated gasdynamic parameters in the flow.     

纳秒脉冲表面介质阻挡等离子体激励唯象学仿真

结合NS-DBD实验数据和理论分析, 建立NS-DBD单区非均匀唯象学模型, 旨在通过合理的模型进行流动控制仿真, 揭示流动控制机理. 在平板无来流时, 运用单区非均匀唯象学模型, 通过引入涡量输运方程, 求解涡量方程各项, 分析展向涡形成机理. 展向涡主要是由压力升诱导激励区压力梯度和密度梯度的不正交性产生的, 其次是激励区附近流场的对流引起的涡量转移. 圆柱上的激励仿真得到与实验一致的压缩波结构和冲击波位置, 验证了模型合理性. NACA 0015翼型大迎角分离控制的仿真表明, 激励诱导展向涡促使主流和分离流相互作用, 使分离点移向下游; 脉冲激励频率通过诱导展向涡的数量对流动分离产生不同的作用效果, 本文最佳的无量纲激励频率为6.     

多相等离子体气动激励流动特性

 等离子体激励器电极组相位不同便产生多相等离子体气动激励,建立了粒子图像测速仪流场参数测试系统,利用粒子图像测速仪技术,研究了非对称布局等离子体气动激励诱导空气流动特性,分析了多相等离子体气动激励对诱导空气流动速度的影响。结果表明：粒子图像测速仪流场测试系统能够准确地反映等离子体气动激励诱导空气流动的流场空间结构,等离子体气动激励诱导空气流动是平行于激励器的近壁面射流,多相等离子体气动激励能够增大等离子体气动激励诱导气流速度,或者使等离子体气动激励影响流场区域增大。粒子图像测速仪系统是深入研究等离子体气动激励的流场结构最佳的方式之一。     

亚微秒脉冲表面介质阻挡放电等离子体诱导连续漩涡的研究

使用粒子激光图像测速技术对亚微秒脉冲激励表面介质阻挡放电激励器连续产生诱导漩涡进行了实验研究, 给出了包含脉冲重复频率和漩涡频率的双频率激励模式的具体形式. 实验过程中出现了原发型与继发型两类示踪粒子空白区, 前者由放电释热的微爆炸作用造成, 使得诱导流动远离壁面, 能够减小壁面摩擦阻力的作用; 以暴露电极左侧继发型空白区被完全吹除作为重复启动激励的临界点. 为提高控制效果应采用尽可能高的脉冲重复频率, 漩涡时间内脉冲数量应大于10, 最大诱导速度随脉冲数量增大而增大, 但动量传递效率降低. 使用亚微秒脉冲激励具备释热、体积力两种作用机理. 关键词： 双频率亚微秒脉冲 表面介质阻挡放电 连续漩涡     

等离子体气动激励控制激波的机理研究

针对等离子体气动激励控制激波的热效应机理和电离效应机理的争议,分别采用热阻塞模型和离子声波模型,理论推导出了不同机理前提下电弧等离子体对尖劈斜激波的影响规律.对于热效应机理,激波变化规律是激波起始点前移、形状不弯曲以及角度减小;对于电离效应机理,激波变化规律是激波起始点仍维持在尖劈前缘点处、形状分为两段发生弯曲以及起始段的角度增大.针对该对立的理论推导结果,进行了电弧等离子体控制尖劈斜激波的超声速风洞实验研究,实验观察到尖劈斜激波起始点前移4 mm,激波角度减小8.6%,激波形状未发生弯曲.以热效应机理为前提推导出的理论结果与该实验结果相符,从而验证了等离子体气动激励控制激波是热效应机理在起主要作用. 关键词： 等离子体气动激励 激波 热效应 电离效应     

冲击波在空气和熔石英元件界面传播的超快诊断

基于球面波在弹性介质界面上的反射和折射特性的基本理论,采用超快时间分辨的光学诊断技术,研究了532nm纳秒激光辐照熔石英元件表面产生的冲击波在空气和样品界面的传播特性,获得了冲击波在材料内部传输以及在空气与样品界面反射的时间分辨图像。结果表明:激光脉冲与材料作用在前后表面产生了向体内传输的冲击波,且产生的冲击波在玻璃与空气界面处反射为两个波,即反射波和反射剪切波;反射波和反射剪切波的强度与入射冲击波的入射角有关。     

Cathode-sheath driven low-speed aerodynamic flow actuation using direct-current surface glow discharges

Flow actuation by a continuous/pulsed, direct-current (DC) surface glow discharge is explored. The discharge comprises an array of pin electrode pairs flush mounted on a dielectric actuator surface that lies adjacent to stagnant air. Strong electrostatic fields produced in the cathode sheath region of the discharge provides a motive force on the ions which in turn drag the background gas resulting in directed air flow from the anode to the cathode. The induced flow velocity is estimated by particle image velocimetry (PIV) at 10 Hz with TiO₂ seeding. For a pulsed DC discharge with peak power of 5 W per electrode pair, the induced flow velocity reaches peak values of about 1.7 m/s which is comparable to dielectric-barrier discharge (DBD) or corona discharge actuators. The actuation effect quantified by the magnitude of induced velocity increases as the pulse frequency increases from 0 to 1 kHz. The actuation effect decreases for further increase in frequency above 1 kHz. Decreased actuation effect at high frequency is accompanied by structural change in the discharge. At fixed frequency of 1 kHz, flow actuation effect is highest for a square wave pulse with a duty cycle of 50% indicating that pulsed DC discharges produces better actuation than continuous DC with a corresponding reduction in energy consumption.     

介质阻挡体放电对甲烷扩散火焰特性的影响

本文在高频交流激励模式下,采用同轴圆柱构型激励器,开展了介质阻挡体放电对空气/甲烷同轴剪切扩散火焰燃烧特性影响实验研究。激励器敷设在外喷嘴环缝以电离空气,采用纹影系统和B型热电偶分别获取流场形态和火焰温度,激励频率为8 kHz,通过改变气体流量和放电电压,分析了不同工况下射流流场、火焰结构和火焰温度在等离子体作用下的变化规律。结果表明:等离子体气动效应能有效增强射流湍流强度,强化空气/甲烷掺混,增大射流角,并随激励电压提高作用效果逐渐增强,实验中未形成明显扩张流动的初始射流在放电电压30 kV时其射流角最大为23.5°。贫燃条件下等离子体激励会改善火焰形态,增强燃烧稳定性,并在流量较低时缩短火焰长度。此外,富燃火焰下游温度会随着激励强度增大不断升高,而贫燃火焰下游温度变化受上游燃烧强度影响存在升高和降低两种情况。     

On the possibility of controlling transonic profile flow with energy deposition by means of a plasma-sheet nanosecond discharge

A way of effectively affecting the gasdynamic structures of a transonic flow over a surface by means of instantaneous local directed energy deposition into a near-surface layer is proposed. Experimental investigations into the influence of a pulsed high-current nanosecond surface discharge of the “plasma sheet” type on gas fast flow with a shock wave near the surface are carried out. The self-localization of energy deposition into a low-pressure region in front of the shock wave is described. Based on this effect, a facility for automated energy deposition into a dynamic region bounded by the moving shock front can be designed. The limiting value of the specific energy deposition on the surface in front of the shock wave is found. With the help of the direct-shadow method, an unsteady quasi-two-dimensional discontinuous flow arising when a plasma sheet is initiated on the wall in a flow with a plane shock wave is studied. By numerically solving the two-dimensional nonstationary equations of gas dynamics, the influence of the energy of a pulsed nanosecond discharge, which is applied in the frequency regime, on the aerodynamic characteristics of a high-lift profile is investigated. It is ascertained that the energy delivered to the gas before the closing shock wave in a local supersonic region that is located in the neighborhood of the profile contour in zones extended along the profile considerably decreases the wave drag of the profile.     

Ultra-fast diagnosis of shock waves and plasma at front and rear surfaces in the bulk of fused silica induced by an Nd:YAG pulse laser

We investigate the dynamic processes of the Nd:YAG pulse laser ablation of fused silica by ultrafast timeresolved optical diagnosis with a nanosecond time resolution. The evolution process of plasma expansion in air and shock waves propagation in the bulk are both obtained with spatial and temporal resolutions.Laser-induced damage in the bulk of fused silica with filaments and shock waves are observed. Thermoelastic wave,mechanical wave,and shock wave dependence on the laser fluence and intensity of the plasma are analyzed. The shock pressure P and temperature T calculated through the measured shock velocity D and the Hugoniot data of fused silica are measured.