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.     

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     

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在超音速风洞中进行了等离子体气动激励改变激波系结构的实验,考察了介质阻挡放电和横向直流放电对于激波系结构的影响。实验结果表明介质阻挡放电所产生的等离子体能够影响流场附面层。采用逆气流DBD放电后,激波强度略有增大;采用顺气流放电后,激波强度略有减弱。相对于介质阻挡放电,横向直流放电对减弱激波强度影响稍大。     

高能表面电弧放电控制圆柱激波实验

采用风洞实验和高速纹影系统研究高能表面电弧等离子体激励控制圆柱激波. 在Ma=2的超声速风洞中, 分别放置了带有10, 15, 20 mm这3个不同高度圆柱的实验模型, 对比分析了不同高度圆柱的初始流场特征, 以及高能表面电弧放电的放电电容、直流源电压和圆柱高度对圆柱脱体激波控制的影响. 实验结果表明, 高能表面电弧等离子体激励诱导的冲击波和热气团与激波产生相互作用, 激波形状改变, 强度削弱. 圆柱高度越高其上方的弓形激波角越大, 在施加等离子体激励后, 弓形激波角减小, 激波强度减弱; 放电电容和直流源电压对激波控制效果的影响均呈正相关关系; 随着圆柱高度的增加, 控制效果减弱、有效控制作用时间缩短.      

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。     

边界层效应影响等离子体气动激励诱导激波机理

 针对小型暂冲式超声速风洞进行的诱导激波实验结果,提出等离子体气动激励诱导激波的机理不仅取决于放电时产生的焦耳热效应,放电区域的边界层厚度也起到了决定性的作用的推论。为进一步验证此思想,在高超声速激波风洞进行了等离子体气动激励诱导激波的实验研究。结果表明,在边界层很薄的情况下,等离子体气动激励能够诱导出斜激波。分别阐述了两种实验条件下诱导激波的机理,证实了边界层效应在等离子体与激波相互作用中起到了决定性作用。     

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。     

等离子体激励翼型分离流动控制数值模拟

文章利用CFD软件FLUENT中的自定义函数接口, 将等离子体对中性气体的激励作用模型化为体积力引入Navier-Stokes方程, 研究了等离子体气动激励诱导的平板射流, 以及介质阻挡放电(dielectric barrier discharge, DBD)等离子体激励对NACA0015翼型大迎角分离流的控制作用.计算分析表明, 多对电极等离子体激励器可以有效控制NACA0015翼型大迎角分离流动.      

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基于介质阻挡放电等离子体的体积力气动激励机理,仿真研究了等离子体增升减阻技术对沿螺旋桨桨径方向均匀分布的10个叶素气动特性的改善效果.采用叶素理论,对比分析了等离子体对螺旋桨整体气动性能的提高效果.主要结论有:桨尖和桨叶根部的叶素容易发生气动分离现象,其中根部叶素处于负攻角的工况中;采用介质阻挡放电等离子体流动控制技术可以完全抑制流动分离不太严重的桨叶中部区域的叶素气动分离,对桨尖处翼型的严重气动分离不能完全抑制但也有改善作用,但对处于负攻角工况的叶素作用不大;等离子体增升减阻技术确实可以提高螺旋桨的气动性能,对本文所研究的情况,螺旋桨的拉力和效率分别提高了28.27％和 12.3％.     

非链式化学HF(DF)激光器工作气体中电子分离的非稳定性和气体放电等离子体的自组织现象(英文)

报道了放电引发的非链式HF(DF)激光器中的激活介质由电子碰撞负离子分离引起的电离非稳定性。这种非稳性出现在电极空间分离、脉冲CO2激光加热的基于SF6的混合气体的大体积放电中。实验研究了自引发体放电过程中由激光加热引起的放电等离子体的自组织现象以及由此在放电间隙的大部分区域形成的准周期等离子体结构。重点分析了等离子体结构随气体温度和注入能量的变化,讨论了等离子体自组织对电子碰撞分离不稳定性所产生的影响,解释了混合气体中由于电子碰撞使负离子消失导致的单等离子体通道移动的产生机理。     

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.     

Wind tunnel experiments on flow separation control of an Unmanned Air Vehicle by nanosecond discharge plasma aerodynamic actuation

Plasma flow control(PFC) is a new kind of active flow control technology, which can improve the aerodynamic performances of aircrafts remarkably. The flow separation control of an unmanned air vehicle(UAV) by nanosecond discharge plasma aerodynamic actuation(NDPAA) is investigated experimentally in this paper. Experimental results show that the applied voltages for both the nanosecond discharge and the millisecond discharge are nearly the same, but the current for nanosecond discharge(30 A) is much bigger than that for millisecond discharge(0.1 A). The flow field induced by the NDPAA is similar to a shock wave upward, and has a maximal velocity of less than 0.5 m/s. Fast heating effect for nanosecond discharge induces shock waves in the quiescent air. The lasting time of the shock waves is about 80 μs and its spread velocity is nearly 380 m/s. By using the NDPAA, the flow separation on the suction side of the UAV can be totally suppressed and the critical stall angle of attack increases from 20° to 27° with a maximal lift coefficient increment of 11.24%. The flow separation can be suppressed when the discharge voltage is larger than the threshold value, and the optimum operation frequency for the NDPAA is the one which makes the Strouhal number equal one. The NDPAA is more effective than the millisecond discharge plasma aerodynamic actuation(MDPAA) in boundary layer flow control. The main mechanism for nanosecond discharge is shock effect. Shock effect is more effective in flow control than momentum effect in high speed flow control.     

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基于介质阻挡放电等离子体体积力气动激励机理,数值研究了两种等离子体流动控制方案对螺旋桨桨径根部处于负攻角工况下叶素气动性能的改善效果.结果显示,激励器布置在下翼面时等离子体体积力大于其布置在叶素前后缘时的情况;激励器布置在下翼面时,可抑制流动分离,使得螺旋桨桨根部位叶素产生更大的负拉力,但会减小螺旋桨的扭矩;激励器布置在前后缘时,会使螺旋桨根部叶素拉力增大,提高螺旋桨总拉力,但不能抑制流动分离,所以会增大螺旋桨的扭矩.     

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.     

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.