流场非均匀性对非平面激波诱导的Richtmyer-Meshkov不稳定性影响的数值研究

基于Navier-Stokes方程组,采用可压缩多介质黏性流动和湍流大涡模拟程序MVFT (multi-viscousflow and turbulence),模拟了均匀流场与初始密度呈现高斯函数分布的非均匀流场中马赫数为1.25的非平面激波加载初始扰动air/SF6界面的Richtmyer-Meshkov (RM)不稳定性现象。数值模拟结果表明,初始流场非均匀性将会影响非平面激波诱导的RM不稳定性演化过程。反射激波加载前,非平面激波导致的界面扰动振幅随着流场非均匀性增强而增大;反射激波加载后,非均匀流场与均匀流场条件下的界面扰动振幅差异有所减小。进一步,定量分析流场中环量分布及脉动速度统计量揭示了前述规律的原因。此外,还与平面激波诱导的RM不稳定性进行了简单对比,发现由于非平面激波波阵面区域的涡量与激波冲击界面时产生的涡量的共同作用,使得非平面激波与平面激波诱导的界面失稳过程存在差异。     

激波冲击下air/SF6界面的Richtmyer-Meshkov不稳定性

实验研究了低马赫数(1.27)激波作用air/SF6界面的RM不稳定性问题.air/SF6初始正弦界面由厚度为1～2 μm的薄膜相隔得到,用阴影法测试界面演化过程.实验结果表明:由于不稳定性重流体(SF6)向轻流体(air)演化成“尖钉”结构,而轻流体演化为“气泡”结构;由于界面切向速度差的Kelvin-Helm-ho...     

绕射激波和反射激波作用下N_2/SF_6界面R-M不稳定性实验研究

利用高速纹影测试实验研究低马赫数入射激波绕圆柱体后冲击N2/SF6平面界面,以及来自固壁的反射激波再冲击过程的(Richmyer--Meshkov,R--M)不稳定性特征.与平面激波作用不同的是,绕射后的激波会在界面处生成局部扰动.实验结果显示,入射激波作用下界面宽度增长缓慢,而反射激波再冲击后,局部扰动会产生大的"尖钉"和"气泡"结构;以及反射激波与边界层相互作用产生壁面涡,它们会加剧湍流混合区的增长;实验中反射激波过后混合区增长率不十分依赖于波前状态,增长规律同Mikaelian模型较吻合;来自尾部固壁的反射稀疏波会再次加剧湍流混合区的增长.     

反射激波作用重气柱的Richtmyer-Meshkov不稳定性的实验研究

采用高速摄影结合激光片光源技术,研究了反射激波冲击空气环境中重气体(SF₆)气柱的Richtmyer-Meshkov不稳定性。通过在横式激波管试验段采用可移动反射端壁获得不同反射距离,实现了反射激波在不同时刻二次冲击处于演化中后期的气柱界面,得到了不同的界面演化规律。反射距离较小时,斜压机制对气柱界面形态演化的影响显著,界面衍生出二次涡对结构;反射距离较大时,压力扰动机制的影响显著,界面在流向上被明显地压缩,没有形成明显的涡结构。由气柱界面形态的时间演化图像得到了界面位置和整体尺度随时间的变化,对反射激波作用后气柱界面的演化进行了量化分析。     

反射激波冲击重气柱的RM不稳定性数值研究

数值研究了二维气柱在入射激波以及反射激波作用下的Richtmyer-Meshkov(RM)不稳定性发展规律, 采用有限体积法结合网格自 适应技术的VAS2D程序, 精确刻画激波和界面的演化. 入射平面激波的马赫数为1.2, 气柱界面内气体为六氟化硫(SF₆), 环境气体为空气, 激波管的尾端为固壁. 通过改变气柱与尾端之间的距离调节反射激波再次作用已经变形的气柱的时间, 获得不同时刻下已经变形的气柱形态、界面尺寸以及环量演化受到反射激波的影响. 结果表明, 反射激波再次作用气柱时, 气柱所处发展阶段不同, 界面演化规律以及环量随时间的变化也不相同, 反射激波与气柱相互作用过程中的涡量产生和分布与无反射情况差异较大, 揭示了不同情况下界面演化的物理机理.     

激波与超细堆积粉尘相互作用的流场实验显示

本文在水平激波管中研究激波与堆积粉尘的相互作用。利用带示踪粒子的X光脉冲摄影和阴影摄影,成功拍摄了反映激波作用后堆积粉尘内部波系结构的X光照片和反映入射激波阵面和波后卷扬粉尘云形状的阴影照片,进而测得与注场结构有关的特征参数。本文还对入射激波强度对流场的影响进行了实验和理论方面的研究,两者符合较好。     

Richtmyer-Meshkov不稳定性流体混合区发展的实验研究

使用矩形激波管,在马赫数分别为$M=1.5$和1.7的条件下实验研究了气/液界面 上(即Atwood数$A$接近1时)由Richtmyer-Meshkov不稳定性引起的流体混合现象. 得到 了气/液界面上Richtmyer-Meshkov不稳定性后期流体混合区域宽度随时间的发展呈现出线 性关系的结果,即$h \propto t$. 比较了不同马赫数和初始扰动下的发展情况,发现当 马赫数增加时,同一时间混合区域 宽度随之增加,混合区域宽度增长变快;而相比于波长差别不大的弱多模态初始扰动(无人 为干扰界面), 当界面初始扰动获得随机外界干扰时,界面混合区域具有较大的宽度以及增 长速度. 并且增加激波马赫数和初始扰动多模态性,流体混合程度更为剧烈.     

激波在波前有非均匀定常流动的变截面管道中传播及波后流场特性的数值研究

本文采用分裂算子的随机选取法,对激波在波前有非均匀定常流动的一维变截面管道中的传播进行了数值模拟,得到了激波强度和波后流动的变化规律,并对结果作了初步分析。     

柱形汇聚激波冲击球形重气体界面的实验研究

采用高速纹影法实验研究了柱形汇聚激波与球形重气体界面相互作用的 Richtmyer-Meshkov不稳定性问题. 激波管实验段基于激波动力学理论设计, 将马赫数为1.2 的平面激波转化为柱形汇聚激波, 气体界面由肥皂膜分隔六氟化硫(内)和空气(外)得到. 采用高速摄影机在单次实验中拍摄激波运动的全过程, 对柱形激波的形成进行了实验验证, 并进一步观测了汇聚激波与球形气体界面相互作用过程中的波系发展和气体界面变形以及反射激波同已变形界面二次作用的流场演化. 结果表明: 当柱形汇聚激波穿过气泡界面以后, 气泡左侧界面极点沿激波传播方向保持匀速运动, 气泡右侧界面发展成为射流结构, 气泡主体发展成为涡环结构; 在反射激波的二次作用下, 流场中无序运动显著增强并很快进入湍流混合阶段.     

柱状交界面Richtmyer-Meshkov不稳定性的数值研究

采用基于有限体积法的二阶Godunov格式模拟了柱形密度交界面在同轴激波加速下的演化过程。得到了以下初步结果:在参数相同的情形下,内聚激波比中心爆炸波对界面的扰动更危险;内聚激波从轻质流体进入重质流体与从重质流体进入轻质流体相比,界面有更快的增长。周向波数大小对界面增长率有很大的影响,在计算的参数下,n=8～12有最大增长率,大于和小于这个范围的周向波长,增长率均明显减弱。     

Numerical investigation of Richtmyer-Meshkov instability driven by cylindrical shocks

In this paper, a numerical method with high order accuracy and high resolution was developed to simulate the Richtmyer-Meshkov(RM) instability driven by cylindrical shock waves. Compressible Euler equations in cylindrical coordinate were adopted for the cylindrical geometry and a third order accurate group control scheme was adopted to discretize the equations. Moreover, an adaptive grid technique was developed to refine the grid near the moving interface to improve the resolution of numerical solutions. The results of simulation exhibited the evolution process of RM instability, and the effect of Atwood number was studied. The larger the absolute value of Atwood number, the larger the perturbation amplitude. The nonlinear effect manifests more evidently in cylindrical geometry. The shock reflected from the pole center accelerates the interface for the second time, considerably complicating the interface evolution process, and such phenomena of reshock and secondary shock were studied. The project supported by the National Natural Science Foundation of China (10176033, 10135010 and 90205025). The English text was polished by Yunming Chen.     

Hot-wire method for measurements of turbulent mixing induced by Richtmyer-Meshkov instability in shock tube

A constant temperature hot-wire anemometry method is applied to the study of mixing zones induced by the interaction of a shock wave with Mach number 1.25 in air with air/helium (heavy/light), air/argon or air/krypton (light/heavy) initially plane interfaces. The single wire gauge is positioned at various locations along the shock tube axis. At the present stage of our investigation, although the analysis of the hot-wire signal is not achieved yet, we report the interesting concept of using hot-wire anemometry as a diagnostic method for shock tube studies of the Richtmyer-Meshkov instability. Based on this preliminary work, we discuss prospective experimental signal conversion, in order to provide some new results for this field of investigation, in particular for resolving characteristics of the turbulent mixing zone which is of most interest. Received 3 August 2000 / Accepted 15 February 2001     

单模大扰动的Richtmyer-Meshkov不稳定性

采用高精度的多介质Ghost-Fluid方法,对马赫数为1.15的激波分别作用于单模大扰动Air-CO2、Air-SF6、Air-N2和Air-He界面后的Richtmyer-Meshkov不稳定现象进行了数值研究,得到了不同时刻扰动界面的演化图像,给出了流场的密度等值线和密度纹影图,同实验结果吻合较好。给出了界面的扰动增长随时间变化的情况,并同理论模型进行了对比。对激波从轻气体进入重气体的情况,扰动增长可采用Sadot模型描述线性阶段和早期非线性阶段;对于弱激波同密度接近的气体界面的相互作用,线性阶段时间较长,可用线性模型描述。     

Shock induced Richtmyer-Meshkov instability in the presence of a wall boundary layer

An experimental investigation on gaseous mixing zones originated from the Richtmyer-Meshkov instability has been undertaken in a square cross section shock tube. Mass concentration fields, of one of the two mixing constituents, have been determined within the mixing zone when the shock wave passes from the heavy gas to the light one, from one gas to an other of close density, and from the light gas to the heavy one. Results have been obtained before and after the coming back of the reflected shock wave. The diagnostic method is based on the infrared absorption of one of the two constituents of the mixing zone. It is shown that the mixing zone is strongly deformed by the wall boundary layer. The consequence is the presence of strong gradients of concentration in the direction perpendicular to the shock wave propagation. Finally, it is pointed out that the mixing goes more homogeneous when the Atwood number tends to zero.     

用浮阻力模型研究Richtmyer-Meshkov不稳定性诱导混合

采用浮阻力模型对激波管低压缩和激光加载高压缩情况下的Richtmyer-Meshkov不稳定性诱导混合现象进行了研究。通过与实验和理论分析结果进行比较发现:为了达到好的吻合, Richtmyer-Meshkov不稳定性情况下阻力系数的取值范围(2.0~5.36)比Rayleigh-Taylor不稳定性情况下的值(3.3~4.0)宽得多; 而在Richtmyer-Meshkov不稳定性情况下, 高压缩时阻力系数的不确定度(约为3.36)明显高于低压缩时的值(约为1.46), 模型的进一步完善还有待于更精确实验的验证。研究显示:指数律经验公式中指数随工况的不同而显著变化, 目前工程设计中采用指数律经验公式是粗糙的。     

Damping of mesh-induced errors in Free-Lagrange simulations of Richtmyer-Meshkov instability

Mesh-induced errors at material interfaces are identified as a source of unphysical behaviour in Lagrangian numerical simulations of Richtmyer-Meshkov instability. The mesh geometry introduces interface perturbations with wavelengths of the same order as the mesh resolution. When a shock propagates through the interface, these perturbations can grow, severely contaminating the predicted interface development. Here an algorithm is presented which damps small-scale interface perturbations. A body force is applied at the interface which depends upon the disturbance amplitude and growth rate, and which resembles surface tension. Using this technique, qualitative improvements are obtained in Free-Lagrange simulations of single-mode Richtmyer-Meshkov instability. Growth rate behaviour and the evolution of the instability are seen to agree well with previously published results. Received 9 March 2000 / Accepted 30 May 2000     

Experiments on the Richtmyer-Meshkov instability of an air/SF6 interface

Results of flow visualization experiments of an impulsively accelerated plane interface between air and SF₆ are reported. The shock tube used for the experiments has a larger test section than in previous experiments. The larger extent of uniform test flow relative to nonuniform boundary-layer flow permits unambiguous interpretation of flow-visualization photographs, and the influence of shock-wave/boundary-layer interactions is no longer dominant. The strong wall vortex observed in previous studies is not observed in these experiments. It is found that the thin membrane, which forms the initially plane interface, has a significant influence on the initial growth rate of the interface thickness. However, the measured growth rates after the first reflected shock are independent of membrane configuration and are in good agreement with analytical predictions.On leave from Stosswellenlabor (Shock Wave Laboratory), RWTH Aachen, Templergraben 55, D-52056 Aachen, Germany.This article was processed by the author using theLAT_EX style filepljour2 from Springer-Verlag.