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| 1 | 等离子体流动控制研究进展与展望显示文摘等离子体流动控制是基于等离子体气动激励的新型主动流动控制技术,具有响应时间短、激励频带宽等显著技术优势,在改善飞行器/发动机空气动力特性方面具有广阔的应用前景,已成为国际上等离子体动力学与空气动力学交叉领域的前沿研究热点。鉴于此,从介质阻挡放电(DBD)、电弧放电等离子体气动激励特性,等离子体气动激励抑制流动分离、控制附面层、控制激波与激波/附面层干扰、控制压气机与涡轮内部流动、控制管道流动和飞行控制等方面,综合评述了国际上等离子体流动控制的研究进展情况;从创新等离子体气动激励方式,揭示等离子体气动激励与复杂流动的非定常耦合机制,突破等离子体流动控制系统关键技术等方面,对未来的发展进行展望。 | 吴云 李应红 | 2015 | 航空学报2015，36，2： | 137 |
| 2 | NS-SDBD等离子体流动控制研究现状与展望显示文摘纳秒脉冲表面介质阻挡放电等离子体在高速、高雷诺数下的流动控制领域具有非常大的潜力。文章对纳秒脉冲等离子体流动控制发展的起源、现状和趋势进行了综述。分别从实验研究和数值模拟两方面进行,主要以气动激励机理探索、现象研究以及流动控制机理为主线进行相关文献的总结归纳。目前,纳秒脉冲等离子体研究的关键科学问题集中在电场激励-气动诱导过程的机理探索与流动控制应用机理研究两方面,研究的难点在于涉及多时间尺度、多物理场耦合。注重解决多时间尺度、多物理场耦合问题的数值模拟算法、实验技术将成为解决上述科学问题的关键突破点。关键科学问题的解决有利于为激励器及控制系统的设计提供优化准则。 | 孟宣市 宋科 龙玥霄 李华星 | 2018 | 空气动力学学报2018，36，6： | 17 |
| 3 | Aerodynamic control of NACA 0021 airfoil model with spark discharge plasma synthetic jets显示文摘Spark discharge plasma synthetic jets(SPJs) have been used for the active flow control study on an NACA 0021 straight-wing model in a wind tunnel. The model forces and moments were measured using a six-component sting balance at a 20 m/s wind speed. The aim was to explore the SPJ's effect on airfoil aerodynamic by examining SPJ generators' position along the chordwise and the jet flow direction about the chord. Near the wing leading edge, two SPJ generators raised the stall angle by 2° and increased the maximum lift coefficient by 9%. The drag coefficient was decreased by 33.1%, and the lift-drag ratio was increased by 104.2% at an angle of attack above 16°. The rolling-moment coefficient was modified by 0.002, and the yawing-moment coefficient was changed by 0.0007 at angles of attack in the range of 0°–16°. The results showed that SPJs can control wing aerodynamic forces at a high angle of attack and moments at a low angle of attack. | LIU RuBing NIU ZhongGuo WANG MengMeng HAO Ming LIN Qi | 2015 | Science China(Technological Sciences)2015，58，11： | 8 |
| 4 | Leading-edge flow separation control over an airfoil using a symmetrical dielectric barrier discharge plasma actuator显示文摘In order to promote an in-depth understanding of the mechanism of leading-edge flow separation control over an airfoil using a symmetrical Dielectric Barrier Discharge(DBD) plasma actuator excited by a steady-mode excitation, an experimental investigation of an SC(2)-0714 supercritical airfoil with a symmetrical DBD plasma actuator was performed in a closed chamber and a low-speed wind tunnel. The plasma actuator was mounted at the leading edge of the airfoil.Time-resolved Particle Image Velocimetry(PIV) results of the near-wall region in quiescent air suggested that the symmetrical DBD plasma actuator could induce some coherent structures in the separated shear layer, and these structures were linked to a dominant frequency of f0= 39 Hz when the peak-to-peak voltage of the plasma actuator was 9.8 kV. In addition, an analysis of flow structures without and with plasma actuation around the upper side of the airfoil at an angle of attack of18° for a wind speed of 3 m/s(Reynolds number Re = 20000) indicated that the dynamic process of leading-edge flow separation control over an airfoil could be divided into three stages. Initially, this plasma actuator could reinforce the shedding vortices in the separated shear layer. Then, these vortical structures could deflect the separated flow towards the wall by promoting the mixing between the outside flow with a high kinetic energy and the flow near the surface. After that, the plasma actuator induced a series of rolling vortices in the vicinity of the suction side of the airfoil, and these vortical structures could transfer momentum from the leading edge of the airfoil to the separated region, resulting in a reattachment of the separated flow around the airfoil. | Xin ZHANG Huaxing LI Yong HUANG Kun TANG Wanbo WANG | 2019 | Chinese Journal of Aeronautics2019，32，5： | 7 |
| 5 | 纳秒等离子体激励控制翼型流动分离机理研究显示文摘为研究纳秒介质阻挡放电(NSDBD)等离子体控制翼型流动分离的物理机理,采用已建立的NSDBD唯象学模型耦合非定常Navier-Stokes方程模拟纳秒等离子体对流场的作用。使用非定常雷诺平均NavierStokes方程(URANS)和大涡模拟(LES)两种求解方法,研究纳秒等离子体激励对NACA0015翼型流动分离控制。结果表明:NSDBD等离子体激励促使边界层提前转捩,转捩对控制流动分离起重要作用;NSDBD激励开始时在翼型前缘形成展向涡,展向涡促使分离剪切层失稳并最终进入尾迹,展向涡贴近壁面运动,将外区的高能气流带入近壁区,使上翼面流场结构发生变化,然后翼型前缘流动提前转捩促使流动经过一个小层流分离泡后发生湍流再附,最终在上翼面形成稳定的附着流动。 | 郝琳召 张彬乾 陈真利 | 2014 | 航空工程进展2014，5，1： | 6 |
| 6 | 基于数值模拟的NSDBD等离子体激励器防冰特性显示文摘飞行器表面在一定气象条件下会产生积冰,积冰会使飞行器气动性能下降,是危害飞行安全的重要因素之一。常见的气热及电热防冰系统已经广泛运用于现有飞行器上。近些年,在纳秒脉冲阻挡介质放电(NSDBD)等离子体激励器的相关研究中发现NSDBD等离子体激励器可对周围流场进行快速加热,考虑到这种热效应可能作为飞机防冰的一种新方式。本文用数值方法对NSDBD等离子体激励器防冰特性开展了研究。首先,建立了基于Messinger模型的积冰模型,对典型积冰条件进行了验证计算;其次,耦合唯象学等离子体模型与非定常雷诺平均Navier-Stokes方程,计算等离子体对空气流场的影响;最后,将NSDBD等离子体激励器布置在NACA0012翼型前缘防冰区,结合积冰模型与唯象学等离子模型,对其防冰特性进行了研究。计算结果表明等离子体加热的热气流会覆盖在翼型表面防冰区。在相同的霜冰条件下,开启等离子体激励器时机翼前缘没有出现积冰,说明等离体子激励器应用于机翼防冰是有效的。针对不同的激励器参数对防冰特性的影响规律进行了研究,总体上防冰效果与峰值电压、激励器频率有关,从防冰效果和能耗方面考量,在给定计算条件下,存在最优电压值和最优激励器频率值。激励器分布方式对防冰特性的影响与其具体流场有关,需要具体分析。 | 贾韫泽 桑为民 蔡旸 | 2018 | 航空学报2018，39，4： | 3 |
| 7 | Operation methods of resistive random access memory显示文摘In this paper, different electrical measurement and operation methods of resistive random access memory(RRAM) have been summarized, including voltage sweeping mode(VSM), current sweeping mode(CSM), constant current stress(CCS), constant voltage stress(CVS), rectangular pulse mode(RPM), and triangle pulse mode(TPM). Meanwhile, the effects of these measurement methods on the forming, set, reset and read operation as well as endurance performance have been compared. Finally, their respective controllability of various resistive switching parameters have been summarized and analyzed. | WANG Guo Ming LONG Shi Bing ZHANG Mei Yun LI Yang XU Xiao Xin LIU Hong Tao WANG Ming SUN Peng Xiao SUN Hai Tao LIU Qi Lü Hang Bing YANG Bao He LIU Ming | 2014 | Science China(Technological Sciences)2014，57，12： | 1 |
| 8 | AC/NS-DBD等离子体激励分离剪切层的涡量输运特性显示文摘AC-DBD激励和NS-DBD激励是等离子体流动控制中的典型激励形式。研究发现二者均能在翼型分离剪切层处诱导形成展向涡,进而实现流动控制。为深入理解AC-DBD激励和NS-DBD激励在诱导展向涡形成上的区别,在Ma=0.1、Re=7.5×10^(5)条件下开展数值模拟,研究了两种激励对翼型大迎角(α=20°)分离的控制。将AC-DBD激励和NS-DBD激励分别以空间分布的动量源项和能量源项的形式耦合到非定常雷诺平均Navier-Stokes方程。引入二维涡量动力学方程,分析了两种激励诱导展向涡量的来源。在激励施加时,对于AC-DBD激励,涡量体积力项是边界涡量变化的主要来源;对于NS-DBD激励,涡量斜压项是边界涡量变化的主要来源。在两种激励施加结束后1 ms时,前缘上翼面附近逐渐形成展向涡结构;展向涡形成后,发现两种激励诱导当地涡量变化的主要因素均是对流项,区别最大的是斜压项,其次是斜黏项,原因是NS-DBD激励后的残留热引起了流体密度梯度和机械应力(黏性应力和压力)梯度的不平行。通过分析AC-DBD激励诱导涡量的变化和发展,提出了提升前缘AC-DBD激励控制流动分离效果的反向激励方法。 | 赵光银 杨永东 李婷婷 肖春华 阎丽 | 2023 | 空气动力学学报2023，41，12： | 0 |
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