Air／SF6界面RM不稳定性诱导的物质混合诊断

不同流体伴随激波的作用,在不同密度介质的界面处往往存在激波诱导的界面不稳定性,即RM(Richtmyer-Meshkov)不稳定性,由此不稳定诱导了物质间的相互混合。文中研究了低马赫(1.23)激波作用Air/SF6界面RM不稳定性问题。Air/SF6初始界面由厚度为1～2μm的硝化纤维薄膜相隔得到,利用阴影测试法研究了Air/SF6界面在1.23马赫数激波冲击下,界面混合宽度随时间的发展过程,以及反射激波作用后混合宽度的再增长。实验结果表明混合宽度线性发展前期与经验公式吻合较好。     

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-viscous-flow 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。     

NUMERICAL STUDY ON THE EFFECTS OF SMALL-AMPLITUDE INITIAL PERTURBATIONS ON RM INSTABILITY

采用Navier-Stokes 方程对入射激波及其反射激波连续诱导小振幅扰动界面的Richtmyer-Meshkov 不稳定性增长过程进行了二维数值模拟,分析了单模和随机多模两种不同初始形态的界面上钉结构和泡结构在反射激波作用前后的发展特性. 研究结果发现：单模扰动的初始界面形态对反射激波前、后界面的扰动增长都有影响,反射激波前的界面形态信息可以通过钉和泡结构之间的反转传递到反射激波过后. 扰动界面上钉结构的发展速度控制了界面混合区总体的发展速度,反射激波前界面上发展成具有完整冠部形态的钉,在反射激波后会反转成复杂的泡结构,此泡结构对反射激波后钉的发展不利. 随机多模界面显示了与单模界面类似的发展规律,但随机多模界面上的复杂泡结构分布的不对称性使得其对钉结构增长的拖曳效应相对要弱,这导致了相似扰动波长下多模随机界面的扰动发展相对单模界面扰动发展要快.     

激波与椭圆形重气柱相互作用的PLIF实验

在水平激波管中，采用平面激光诱发荧光(planar laser-induced fluorescence, PLIF)方法对椭圆形重气柱界面的Richtmyer-Meshkov不稳定性进行实验。气柱由SF₆混入一定比例的丙酮蒸气构成，环境气体为空气。通过改变椭圆形气柱的长短轴比值，得到了激波马赫数为1.25时，3种初始界面的演化形态。通过相对体积分数标定，得到了界面失稳演化过程中的相对体积分数分布，观察到了激波作用后界面气体聚集、转移、消散等现象。实验结果发现，对于流向轴长与展向轴长之比较大的气柱界面，初始界面产生的涡量更大且分布更广，其界面不稳定性发展得越迅速和剧烈。失稳发展迅速的界面甚至出现涡对碰撞并产生尾部射流结构的现象。初始界面直接决定了失稳发展初期形成的涡对强度和间距，并对后期演化有重要影响。     

小扰动界面形态对RM不稳定性影响的数值分析

采用Navier–Stokes方程对入射激波及其反射激波连续诱导小振幅扰动界面的Richtmyer–Meshkov不稳定性增长过程进行了二维数值模拟,分析了单模和随机多模两种不同初始形态的界面上钉结构和泡结构在反射激波作用前后的发展特性.研究结果发现:单模扰动的初始界面形态对反射激波前、后界面的扰动增长都有影响,反射激波前的界面形态信息可以通过钉和泡结构之间的反转传递到反射激波过后.扰动界面上钉结构的发展速度控制了界面混合区总体的发展速度,反射激波前界面上发展成具有完整冠部形态的钉,在反射激波后会反转成复杂的泡结构,此泡结构对反射激波后钉的发展不利.随机多模界面显示了与单模界面类似的发展规律,但随机多模界面上的复杂泡结构分布的不对称性使得其对钉结构增长的拖曳效应相对要弱,这导致了相似扰动波长下多模随机界面的扰动发展相对单模界面扰动发展要快.     

反射激波作用下三维凹气柱界面演化的数值研究

激波与气柱相互作用是Richtmyer-Meshkov不稳定性研究的经典案例. 单次激波与二维气柱相互作用已得到广泛关注, 但是反射激波再次冲击气柱 (尤其是三维气柱) 的研究较少, 相关演化规律和机理尚不清楚. 反射激波再次冲击演化中的气柱界面会产生新的斜压涡量, 影响涡量的输运和分布, 从而影响界面的演化. 本文采用自主开发的HOWD (high-order WENO and double-flux methods) 程序, 研究了马赫数为1.29的平面激波冲击N激波与气柱相互作用是Richtmyer-Meshkov不稳定性研究的经典案例.单次激波与二维气柱相互作用已得到广泛关注,但是反射激波再次冲击气柱(尤其是三维气柱)的研究较少,相关演化规律和机理尚不清楚.反射激波再次冲击演化中的气柱界面会产生新的斜压涡量,影响涡量的输运和分布,从而影响界面的演化.本文采用自主开发的HOWD (high-order WENO and double-flux methods)程序,研究了马赫数为1.29的平面激波冲击N_2气柱(气柱外为SF_6)的演化过程,并考察了反射激波对二维和三维凹气柱界面演化的影响规律.在数值模拟中,选取了不同的反射距离(定义为气柱和反射边界的距离),得到了二维和三维凹气柱在反射激波冲击前后的完整演化图像,提取了气柱上特征点位置随时间变化的定量数据,重点分析了不同演化阶段气柱几何特征及斜压涡量分布的变化趋势.研究表明,反射距离决定着反射激波作用气柱时的激波形状和气柱形态,从而影响斜压涡量的生成和分布,进而改变气柱的不稳定性演化过程.对于三维气柱,不同高度截面上的斜压涡量分布不同,从而诱导出复杂的三维演化结构.     

瞬态加速液柱的流体力学问题研究

介绍了用激波和压缩气体加速液柱时的流体动力现象的实验研究,实验中采用了高速摄影技术。研究分为两部分:第一部分,液柱在被加速后在管内的气/液两相流的发展以及流出管外后喷雾流的形成,喷雾流自下而上产生;第二部分,气/液界面上的流体力学不稳定性,即Rayleigh Taylor(RT)不稳定性及Richt myer Meshkov(RM)不稳定性,液柱自上而下运动。实验发现,用此方法产生的喷雾具有流量大、射程远、覆盖面积大等特点。液柱在管内的加速过程中,上端面保持平面,下端面在经历了初始的不稳定性之后形成弹状流。在本实验的驱动压力及马赫数的范围内,RT和RM不稳定性的后期的发展过程比较接近,尽管两者的增长率不同。在RT不稳定性的初始阶段,高密度流体的尖钉先伸入低密度流体中;但是,在RM不稳定性的初始阶段,低密度的气泡先伸入高密度流体中。     

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.     

柱状汇聚激波冲击单模气体界面的实验研究

在自行设计和加工的半环形汇聚激波管中,开展了柱状汇聚激波冲击单模Air/SF6气体界面的Richtmyer-Meshkov(RM)不稳定性实验研究。不同于以往的环形激波管,该激波管具有半圆形结构的实验段,使半环形管道和实验段都向外敞开,能够参考传统水平激波管的方式设置初始扰动界面和观测系统。采用线约束肥皂膜的方法形成单模初始扰动界面。利用高速纹影成像技术得到了柱形汇聚激波作用下界面演化的完整过程。为了研究初始振幅对界面演化形态的影响,实验中生成了三种不同初始振幅的单模界面,并获得了三种工况下界面位移和扰动振幅随时间的变化。结果表明,汇聚激波作用下的RM不稳定性与平面激波有很大差别,主要原因在于汇聚效应,包括结构汇聚、流动压缩以及界面反相等。     

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。     

Measurements on supersonic free jets

Summary An experimental study of round supersonic air jets discharging into quiescent air is described. The initial stagnation enthalpy of the jets was equal to that of the atmosphere. Most of the experiments concerned a fully expanded jet with initial Mach number M _I =1.74. From the experimental results the turbulent Prandtl number and the turbulent coefficient of momentum transfer could be calculated in a large part of the mixing zone of the jets. A mixing parameter K has been introduced and calculated for the jets. The results of this investigation are compared with those obtained for low-speed jets.     

Study of the membrane effect on turbulent mixing measurements in shock tubes

The effect of the thin membrane on the time evolution of the shock wave induced turbulent mixing between the two gases initially separated by it is investigated using two different sets of experiments. In the first set, in which a single-mode large-amplitude initial perturbation was studied, two gas combinations (air/SF and air/air) and two membrane thicknesses were used. The main conclusion of these experiments was that the tested membrane has a negligible effect on the evolution of the mixing zone, which evolves as predicted theoretically. In the second set, in which similar gas combinations and membrane thicknesses were used, small amplitude random-mode initial perturbation, caused by the membrane rupture, rather than the large amplitude single-mode initial perturbation used in the first set, was studied. The conclusions of these experiments were: (1) The membrane has a significant effect on the mixing zone during the initial stages of its growth. This has also been observed in the air/air experiment where theoretically no growth should exist. (2) The membrane effect on the late time evolution, where the mixing zone width has reached a relatively large-amplitude, was relatively small and in good agreement with full numerical simulations. The main conclusion from the present experiments is that the effect of the membrane is important only during the initial stages of the evolution (before the re-shock), when the perturbations have very small amplitudes, and is negligible when the perturbations reach relatively large amplitudes. Received 29 August 1998 / Accepted 25 December 1998     

Shock wave reflection off coupled surfaces

It has been shown that when a plane shock wave is reflected off a surface consisting of a 75-mm radius circular arc followed by a plane section inclined at 45°, it takes some time for the interaction to reach a pseudosteady reflection configuration. The current study extends this work at a constant Mach number of 1.346, with three compound walls, consisting of leading circular sections of 30, 50 and 75 mm radius, joined to a plane wall section. Testing was done at various wall angles for each of the test pieces. The reflected wave angle was measured and was found to increase along the plane wall section until it reached an asymptotic value, at which time pseudosteady flow was established. The asymptotic values are consistent with reflection off plane wedges and are independent of the leading radius. For lower wall angles which lead to Mach reflection the length required to reach pseudosteady flow increases as the wall angle increases to the pseudosteady transition angle. The reverse occurs when the final pseudosteady reflection is regular, in that as the wall angle increases the distance travelled to reach pseudosteady flow conditions decreases. Additional tests were conducted on a specimen consisting of a plane section at 60° wall angle with 30-mm radius circular arc sections at either end. It is demonstrated how the information from the two slope changes influences the shape of the reflected shock. The trajectories of two perturbations on the reflected shock arising from the joints between the circular sections and the plane wall show that the reflected wave remains linear between these two points, as it received no knowledge from either circular section until the perturbations from the upper and lower joints cross.     

Numerical analysis of enhanced mixing in a Gallay tote blender

The mixing performance of a multi-bladed baffle inserted into a traditional Gallay tote blender is explored by graphic processing unit-based discrete element method software. The mixing patterns and rates are investigated for a binary mixture, represented by two different colors, under several loading profiles. The baffle effectively enhances the convective mixing both in the axial and radial directions, because of the disturbance it causes to the initial flowing layer and solid-body zone, compared with a blender without a baffle. The axial mixing rate is affected by the gap between the baffle and the wall on the left and right sides, and an optimal blade length corresponds to the maximum mixing rate. However, the radial mixing rate increases with the blade length almost monotonically.     

Calculation of the length of the shock-boundary layer interaction zone

An analytic relation for determining the length of the shock-laminar or turbulent boundary layer interaction zone is obtained on the basis of an analysis of the boundary layer separation criterion. It is shown that as the Mach number of the flow increases, the interaction length decreases, and that with increase in the Reynolds number it behaves nonmonotonically: in the laminar region it increases, while on transition to the turbulent regime it falls sharply and then varies along a curve with a maximum. The results of the calculations are in satisfactory agreement with the existing experimental data.Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 2, pp. 180–183, March–April, 1987.     

时间发展平面混合流的三维演化

采用高精度差分方法和群速度控制方法，求解三维可压缩Ｎ Ｓ方程，直接数值模拟了时间发展的平面混合流．研究了平面混合流三维拟序结构的形成及发展．给出了流动失稳后涡的卷起，相邻两涡的对并，激波的形成及发展．指出，涡对并所诱导产生的激波对三维拟序结构的形成及发展过程是重要的．     

Density and compressibility effects in turbulent subsonic jets part 1: mean velocity field

The behavior of compressible jets originated from initially turbulent pipe flows issuing in still air has been investigated at three different subsonic Mach numbers, 0.3, 0.6 and 0.9. Helium, nitrogen and krypton gases were used to generate the jet flows and investigate the additional effects of density on the flow structure. Particle image velocimetry, high-frequency response pressure transducers and thermocouples were used to obtain velocity, Mach number and total temperature measurements inside the flow field. The jets were formed at the exit of an adiabatic compressible frictional turbulent pipe flow, which was developing toward its corresponding sonic conditions inside the pipe, and continued to expand within the first four diameters distance after it exited the pipe. Theoretical considerations based on flow self-similarity were used to obtain the decay of Mach number along the centerline of the jets for the first time. It was found that this decay depends on two contributions, one from the velocity field which is inversely proportional to the distance from the exit and one from the thermal field which is proportional to this distance. As a result, a small non-linearity in the variation of the inverse Mach number with downstream distance was found. The decay of the Mach number at the centerline of the axisymmetric jets increases by increasing the initial Mach number at the exit of the flow for all jets. The decay of mean velocity at the centerline of the jets is also higher at higher exit Mach numbers. However, the velocity non-dimensionalized by the exit velocity seems to decrease faster at low exit Mach numbers, suggesting a reduced mixing with increasing exit flow Mach numbers. Helium jets were found to have the largest spreading rate among the three different gas jets used in the present investigation, while krypton jets had the lowest spreading rate. The spreading rate of each gas decreases with increasing its kinetic energy relatively to its internal energy.     

Experimental investigation of the stability of a supersonic boundary layer on a plate with blunting of the leading edge

In an aerodynamic tube, an experimental investigation of the development of small natural perturbations in a laminar boundary layer on a plate was made. The measurements were made using a thermoanemometric method with a Mach number M = 2 and a unit Reynolds number Re₁ = 3.1·10⁶ m^–1. An investigation of the effect of blunting of the leading edge of the plate on the development of the perturbations was made. It is shown that blunting decreases the range of unstable frequencies and the region of instability and increases the critical Reynolds number of the loss of stability. In the initial section of the plate there is a rise in the perturbations of all frequencies up to a maximal value, whose coordinate is inversely proportional to the frequency. The development of perturbations in this region is insensitive to the state of the boundary layer. The position of the maximum does not change with blunting of the leading edge.Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 4, pp. 65–70, July–August, 1977.     

可压缩混合层中细光束畸变效应的实验研究

利用双曝光CCD相机成像技术,对小直径光束穿越可压缩混合层流场存在的大尺度结构特性及其引起的气动光学效应进行了实验研究。实验研究结果表明:在不同对流马赫数(Mc=0.17,0.45)下,可压缩混合层中的大尺度结构形状不同,因而具有不同的折射率分布场,从而导致光束投影发生了不同程度的变形和偏移。利用光束质心的概念定量分析了不同对流马赫数下光束偏移和抖动的统计特性。统计结果表明在高对流马赫数下光束投影的偏移量减小,光束沿流场展向的平均偏移角度减小,但摆动幅度加大。     

带展向曲率的超音速混合层中扰动演化的研究

超音速混合层的流动不稳定性较之亚音速或不可压的混合层大大减弱，为了提高混合效率， 通过数值模拟的方法分别研究了展向曲率、展向速度、来流马赫数等因素对混合效率所 起的作用. 计算结果表明：在给定展向速度的情况下，带有展向曲率的三维混合层，曲率越 大三维扰动增长率越大，而且法向的卷起范围也越大. 当展向曲率不为零时，展向速度的增 大也能有效地增强混合能力. 由流场中的高频扰动波产生的涡，在向下游发展过程中会有破 碎、拉伸，低频扰动波没有发现这一现象. 对于有展向曲率和展向速度的混合层，提高来流 马赫数时，流场中最不稳定扰动的增长率仍很大. 因此，这是一种提高混合层混合效率的新 途径.