Interface Proximity Effect on the Evolution of a Shock-Accelerated Heavy Gas Cylinder
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摘要: 针对实际应用中激波与物质近表面杂质及孔洞等相互作用中的界面邻近效应，通过数值模拟开展了下游平面重-轻界面对激波诱导重气柱演化影响的简化机理研究。结果表明，激波冲击气柱形成的衍射和透射波系依次冲击下游界面，在气柱与下游界面之间形成来回反射的波系结构，这些波系不仅影响气柱的界面演化，而且在下游界面诱导产生射流。在不同的界面间距条件下，气柱外部衍射波系在下游界面的反射波系不同，这些反射波系及气柱内部聚焦波系冲击气柱右极点的先后顺序也存在差异。当界面间距较小时，气柱射流可以穿透气柱与下游界面之间的间隙流体，并与下游界面射流耦合，显著促进气柱射流的演化。随着界面间距的增大，射流耦合现象逐渐减弱，重气柱演化涡对抑制了气柱射流的发展。当界面间距进一步增大时，气柱射流又会因下游界面反射稀疏波系的拉伸作用而被促进。此外，在不同的界面间距条件下，下游界面的存在均对气柱界面宽度、高度的发展及环量沉积起到促进作用。Abstract: To uncover the interface proximity effect arising from the interaction between shock wave and near-surface impurity and hole of material in practical applications, a simplified mechanism study on the influence of downstream planar heavy-light interfaces on the evolution of a shock-accelerated heavy gas cylinder was carried out through numerical simulation. The findings reveal that the diffracted and transmitted wave systems formed by the incident shock impacting the heavy gas cylinders successively interact with the downstream planar slow-fast interface, leading to the formation of wave systems that reflect back and forth between the gas cylinder and the downstream planar slow-fast interface. Significantly, these wave systems not only govern the evolution of the gas cylinder interface but also trigger the generation of jets at the downstream planar slow-fast interfaces. Under diverse interfacial spacing conditions, the type of reflected waves originating from the diffracted wave system outside the gas cylinder varies at the downstream interface, and the sequence of the reflected wave system and the focused wave system inside the gas cylinder interacting with the right pole of the gas cylinder is different. When the interfacial distance is narrow, the gas cylinder jet can permeate the gap fluid sandwiched between the gas cylinder and the downstream slow-fast interface and couple with the jet at the downstream planar slow-fast interface, which significantly promotes the evolution of the gas cylinder jet. As the interfacial distance increases, the jet coupling phenomenon progressively wanes, and the gas cylinder jet succumbs to the inhibitory effect of the vortex pair within the gas cylinder. With a further augmentation in interfacial distance, the gas cylinder jet will be promoted by the stretching effect of the reflected rarefaction wave system at the downstream interface. In addition, under different interface spacing conditions, the presence of a downstream planar slow-fast interface invariably augments the development of interfacial width, height, as well as circulation deposition.
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Key words:
- shock wave /
- Richtmyer-Meshkov instability /
- gas cylinder /
- jet /
- micro-jet /
- circulation
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图 1 数值模拟计算域示意图 (a)及网格收敛性验证 (b)
Figure 1. (a) Schematic diagram of the computational domain, (b) grid convergence validation
图 2 激波冲击重气柱的实验和数值模拟纹影图像对比
Figure 2. Comparison of experimental and numerical schlieren sequences of the shock-accelerated heavy gas cylinder
图 3 重气柱左、右极点x坐标（xL/D0和xR/D0）的实验与数值模拟结果定量比较
Figure 3. Quantitative comparison of experimental and numerical results of x coordinates of left and right poles (xL/D0, xR/D0) of the shock-accelerated heavy gas cylinder
图 4 工况Ⅰ条件下激波与重气柱作用过程的数值纹影图（上）和压力云图（下）（IS、DS、TS1和TDS分别代表入射激波、衍射激波、透射激波和透射衍射激波，RS1和RS2代表反射激波，SS1、SS2和SS3代表流场横波，MS1和MS2代表马赫杆，U代表未扰动区）
Figure 4. Numerical schlieren (upper) and pressure contour (lower) of the flow field resulting from the interaction between a planar incident shock wave and a heavy gas cylinder for case Ⅰ (Here IS, DS, TS1 and TDS, respectively, denote the incident shock, the diffracted shock, the transmitted shock and the transmitted diffracted shock; RS1 and RS2 represent the reflected shocks; SS1, SS2, and SS3 denote the transverse shocks; MS1 and MS2 represent the Mach stems; U denote the undisturbed flow region.)
图 5 工况Ⅱ条件下激波与气柱作用过程的数值纹影图（上）和压力云图（下）（TS1、TS2和TS3代表透射激波，RS1、RS2、RS3和RS4代表反射激波，RW1、RW2、RW3和RW4代表反射稀疏波，SS1代表流场横波，FPS代表自由前驱激波，IP1和IP2代表激波与界面交点）
Figure 5. Numerical schlieren (upper) and pressure contour (lower) of the flow field resulting from the interaction between a planar incident shock wave and a heavy gas cylinder for case Ⅱ (Here TS1, TS2 and TS3 denote the transmitted shocks; RS1, RS2, RS3 and RS4 denote the reflected shocks; RW1, RW2, RW3 and RW4 denote the reflected rarefaction waves; SS1 denotes the transverse shock; FPS denotes the free precursor shock wave; IP1 and IP2 represent the shock-interface intersection points.)
图 6 工况Ⅲ条件下激波与气柱作用过程的密度纹影图（上）和压力云图（下）（FPR代表自由前驱激波折射）
Figure 6. Numerical schlieren (upper) and pressure contour (lower) of the flow field resulting from the interaction between a planar incident shock wave and a heavy gas cylinder for case Ⅲ (Here FPR denotes the free precursor shock refraction.)
图 7 工况Ⅳ条件下激波与气柱作用过程的密度纹影图（上）和压力云图（下）
Figure 7. Numerical schlieren (upper) and pressure contour (lower) of the flow field resulting from the interaction between a planar incident shock wave and a heavy gas cylinder for case Ⅳ
图 8 4种工况下重气柱界面的演化形态
Figure 8. Evolution of heavy gas cylinder morphology for four cases
图 9 4种工况下重气柱无量纲宽度、高度及射流长度随时间的变化
Figure 9. Evolution of the non-dimensional width, height and jet length of the shock-accelerated heavy gas cylinder for four cases
图 10 工况Ⅱ、工况Ⅲ和工况Ⅳ下波系与气柱界面作用过程的涡量沉积示意图
Figure 10. Sketch diagrams of the vorticity deposition induced by the interaction between shocks and the gas cylinders for cases Ⅱ, Ⅲ and Ⅳ
图 11 4种工况下上半平面气柱界面负环量、正环量和总环量随时间演化规律
Figure 11. Evolution of the negative, positive and total circulation deposited on the shock-accelerated heavy gas cylinder at the upper half plane for four cases
表 1 初始条件设置
Table 1. Setting of initial conditions
Case Gas combinations of downstream planar heavy-light interfaces Ms L/mm Ⅰ Air-He 1.22 ∞ Ⅱ Air-He 1.22 0.6D0 Ⅲ Air-He 1.22 0.7D0 Ⅳ Air-He 1.22 2.0D0 
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