Momentum and Energy Transfer in a Shock Wave

The macroparameter profiles in a strong shock wave propagating in a single-component monatomic gas are investigated. The interaction between the molecules is described by the variable-diameter sphere model. Qualitative information concerning the shock wave parameters is obtained by direct statistical simulation (Monte-Carlo) method. Using the data obtained, simple approximate gas-velocity dependences of the stress and the heat flow are found and the linear Newton and Fourier relations are generalized.     

Effects of a Single-pulse Energy Deposition on Steady Shock Wave Reflection

The effects of energy deposition in the free stream on steady regular and Mach shock wave reflections are studied numerically. A short-duration laser pulse is focused upstream of the incident shock waves. It causes formation of the expanding blast wave and the residual hot-spot interacting in a complex way with the steady shock wave reflection. It was found that the laser energy addition in the free stream may force the transition from regular to Mach reflection in the dual solution domain. In contrast to previously reported numerical results, the transition from Mach to regular reflection has not been reproduced in our refined computations since the Mach reflection is restored after the flow perturbation.     

Controlling Transonic Flow around Airfoils by Means of Local Pulsed Addition of Energy

The influence of local pulsed-periodic addition of energy into a supersonic region on the flow structure and wave drag of an airfoil in transonic flow regimes is considered by methods of mathematical modeling. The study reveals significant prospects of the considered method of controlling airfoil performance in transonic flow regimes, including wave-drag reduction.     

激波作用下三维涡的形成及其界面捕捉计算

针对三维多介质可压缩流体,给出了可压缩多介质流体三维高精度数值计算方法,以及界面捕捉方程和带重新初始化的三维LevelSet方法,对初始压力间断和密度间断条件形成激波、接触间断以及稀疏波的三维复杂流场相互作用情况进行数值计算,给出流场中涡的形成过程和界面位置。并对计算方法进行理论验证。     

Numerical Study of a Turbulent Flow Compressed by a Weak Shock Wave

Abstract

Modification of a two-dimensional isotropic trbulent flow by passage of a weak shock wave was numerically studied by the explicit spectral collocation method with the fourier series in the ranges of M₁ = 0.14?0.21 and M_s = 1.06?1.14. The density 1 trbulent kinetic energy increased by 10 to 19 % and density fluctuation increased by 14 to 50 % in proportion to the shock wave mach number. The amplification of turbulent kinetic energy did not change by increase of the turbulent Mach number, while that of density fluctuation decreased from1.35 to 1.15%. The argumentation of turbulent kinetic energy appeared at moderate and high wave numbers of energy spectra and resulted in a reduction of the integral scale by3.33 to 5.4%. Modifications mechanisms of turbulent kinetic energy, density fluctuation and vorticity were verified by the transport equations It was shown that the decreased amplification of the density fluctuation In the increased trbulent Mach number attributed to the unchanged production terms and the negative dilatation correlation behind the shock wave.the vorticity-dilatation term was responsible for more than 80 % of the total vorticity production at the shock front.     

Interference of a Bow Shock with an Oblique Shock and an Isentropic Compression Wave

The features of the flow in the zone of interaction between a plane bow shock and an oblique shock or an isentropic compression wave are studied. The limiting interaction regimes are considered analytically, the similarity conditions are formulated, and the limiting values of the flow parameters are determined for the high-pressure compressed gas jet formed in the interference and for the body surface. On the basis of a numerical solution of the Euler equations the flow specifics in the neighborhood of the spreading line on the body are determined and ways of reducing the dynamic and thermal loadings on this line are proposed.     

Head-on Collision of a Detonation with a Planar Shock Wave

The phenomenon that occurs when a Chapman–Jouguet (CJ) detonation collides with a shock wave is discussed. Assuming a one-dimensional steady wave configuration analogous to a planar shock–shock frontal interaction, analytical solutions of the Rankine–Hugoniot relationships for the transmitted detonation and the transmitted shock are obtained by matching the pressure and particle velocity at the contact surface. The analytical results indicate that there exist three possible regions of solutions, i.e. the transmitted detonation can have either strong, weak or CJ solution, depending on the incident detonation and shock strengths. On the other hand, if we impose the transmitted detonation to have a CJ solution followed by a rarefaction fan, the boundary conditions are also satisfied at the contact surface. The existence of these multiple solutions is verified by an experimental investigation. It is found that the experimental results agree well with those predicted by the second wave interaction model and that the transmitted detonation is a CJ detonation. Unsteady numerical simulations of the reactive Euler equations with both simple one-step Arrhenius kinetic and chain-branching kinetic models are also carried out to look at the transient phenomena and at the influence of a finite reaction thickness of a detonation wave on the problem of head-on collision with a shock. From all the computational results, a relaxation process consisting of a quasi-steady period and an overshoot for the transmitted detonation subsequent to the head-on collisions can be observed, followed by the asymptotic decay to a CJ detonation as predicted theoretically. For unstable pulsating detonations, it is found that, due to the increase in the thermodynamic state of the reactive mixture caused by the shock, the transmitted pulsating detonation can become more stable with smaller amplitude and period oscillation. These observations are in good agreement with experimental evidence obtained from smoked foils where there is a significant decrease in the detonation cell size after a region of relaxation when the detonation collides head-on with a shock wave.     

On the Mutual Penetrations of Two Fluids Whose Interface is Accelerated by a Shock Wave

A shock tube experimental investigation and numerical simulations are undertaken to study the evolution of a perturbed interface of two different gases accelerated by a shock wave. The experimental method is based on a high-speed camera laser sheet diagnostic technique, and simulations are provided by our code CARBUR based on a finite volume discretization of Navier–Stokes’s equations. Two gas pairs are used to illustrate both the heavy/light (air/He) and the light/ heavy (air/SF₆) cases. Two simultaneous large initial perturbations, one positive and one negative, are tested for an incident shock wave Mach number in air of about 1.3. The thin membrane (less than 1 μ) which materializes the initial interface between the two test gases presents 2D perturbations whose wave number is close to 1 in order to rapidly reach the non-linear regime. The development of the perturbations is captured at a frequency of 10 kHz after the interface acceleration, and the experiments are complemented with a numerical simulation to validate the interface deformations. Results show an asymmetric mutual gas penetration increasing with the absolute value of the Atwood’s number. Furthermore, they confirm that the heavier gas penetrates the lighter as thin spikes and the lighter gas penetrates the heavier as large bubbles. Moreover, we show that the spike moves faster than the bubble in the heavy/light case and slightly faster in the light/heavy one. Finally, numerical and experimental results are in agreement.     

Interaction Between a Slow Magnetohydrodynamic Shock Wave and a Tangential Discontinuity

The self-similar problem of the oblique interaction between a slow MHD shock wave and a tangential discontinuity is solved within the framework of the ideal magnetohydrodynamic model. The constraints on the initial parameters necessary for the existence of a regular solution are found. Various feasible wave flow patterns are found in the steady-state coordinate system moving with the line of intersection of the discontinuities. As distinct from the problems of interaction between fast shock waves and other discontinuities, when the incident shock wave is slow the state ahead of it cannot be given and must to be determined in the process of solving the problem. As an example, a flow in which the slow shock wave incident on the tangential discontinuity is generated by an ideally conducting wedge located in the flow is considered. The basic features of the developing flows are determined.     

冲击加载条件下材料之间摩擦系数的确定

尝试利用自制分离式霍普金森压剪装置对聚氨酯泡沫塑料、硅橡胶和MDF水泥材料与铝合金在冲击加载条件下的摩擦系数进行测试.结果表明:在冲击加载条件下,聚氨酯泡沫塑料、硅橡胶和MDF水泥与铝杆之间的摩擦系数与材料的性质关系不大,其摩擦系数测试结果存在一定的分散性,摩擦曲线出现抖动,且与加载条件有关,摩擦系数比通常意义下所得到的摩擦系数小;不同加载条件对所测试材料与铝压杆之间的摩擦系数数值影响不大,只是曲线的走势稍有不同.在冲击加载条件下硬质聚氨酯泡沫塑料与铝杆之间的静摩擦系数为0.29,动摩擦系数为0.25;硅橡胶与铝杆之间的静摩擦系数为0.285,动摩擦系数为0.24;MDF水泥与铝合金杆之间的静摩擦系数为0.28～0.29,动摩擦系数约0.23.     

On the Passage of a Shock Wave through a Layer of Charged Gas

A class of exact solutions of the ideal electrohydrodynamics equations is presented. These solutions describe the propagation of a plane shock wave along a static background with decreasing density in the presence of gravity and longitudinal electric fields. This class of solutions contains an arbitrary function of the Lagrangian variable which makes it possible to consider many physically different cases.     

激波驱动下固体颗粒抛撒的实验研究

本文使用阴影照相技术、高速摄像技术及压力测试手段,实验记录和研究了激波与固体颗粒群的作用及激波作用后固体颗粒群的抛撒和云团的形成过程.结果表明:在激波与固体颗粒群作用过程中,存在着清晰的激波透射、反射及绕射现象,同时激波强度在作用后有明显的下降趋势;在固体颗粒抛撒及云团形成过程中,实验发现对同一粒径的颗粒抛撒来说,抛撒的颗粒群质量越大,云团形成的均匀性及稳定性越好,而对不同粒径的颗粒群来说,粒径越大,形成的云.团集中性越强.     

Nonequilibrium Ionization Behind a Strong Shock Wave in the Mars Atmosphere

The paper reports results of experimental and numerical studies of nonequilibrium ionization behind a strong shock wave in the Mars atmosphere. The calculated kinetic model is verified by measuring the electron concentrations and temperature in the relaxation zone     

Wave Processes in the Hypersonic Shock Layer on a Flat Plate

An electron-beam fluorescence technique is used to investigate the properties of density waves in the shock layer on a flat plate placed in a hypersonic stream (M_x=21) at zero incidence; the Reynolds number based on the longitudinal coordinate and the freestream parameters is Re_x=(2.7–3)·10⁵. Transverse profiles of the mean density and the overall and spectral levels of the density fluctuations are obtained, the longitudinal and lateral phase velocities of the waves and the correlation scales are determined, and the longitudinal increments of the waves are derived. The data are compared with the experimental results obtained at Re_x=(2.6–7)10·⁴.     

激波作用下水膜变形和雾化实验研究

在激波与液滴作用研究的基础上,开展了激波作用下水膜的变形和雾化过程研究。通过阴影照相技术捕捉激波与水膜作用的典型照片,并以此分析其作用机理。通过改变激波强度观察水膜的变形和雾化情况。研究发现激波强度越大,水膜雾化后抛撒的距离越远,证明气动力在作用过程中起主导作用。使用PDPA系统对抛撒后水雾粒子的直径和速度进行测量,结果发现激波作用后初期,气动力仍起着主导作用。     

Interaction of a Streamwise Vortex with an Oblique Shock Wave

Interaction of a supersonic streamwise vortex with an oblique shock wave is considered. A mathematical model of the streamwise vortex is constructed. Three interaction regimes (weak, moderate, and strong) are found. It is shown numerically that vortex breakdown is possible in the case of strong interaction. The influence of the governing parameters on the interaction type is studied. It is shown that the main effect on the interaction type is exerted by the streamwise velocity and angle of the wedge forming the shock wave. The effect of splitting of the primary vortex on the shock wave in the case of moderate and strong interaction regimes is found.     

Shock Wave Pressure and Velocity Measuring Using a Novel Optic Sensor in a Newly Designed Diaphragm-less Shock Tube

Experimental Techniques - This paper suggests a new optical system for measuring shock wave characteristic that is installed in a shock tube. This shock tube has an innovative pneumatic rapid...     

On the Normal Reflection of a Shock Wave from the End of a Rectangular Cavity

The normal reflection of a plane shock, propagating in carbon dioxide at the Mach number 3.7, from the end of a cavity with a rectangular cross-section is experimentally investigated in a shock tube. The flow is visualized using the Cranz-Schardin system. Streak photographs and shadowgraphs of the time-dependent interaction of the reflected shock with the boundary layer under separation conditions with three-shock system formation are presented. On the basis of the experimental results the process of time variation of the flow pattern is described, the triple point trajectories are determined, and their distinctive features for the case of coalescence of the bifurcation zones, formed at opposite sides of the cavity, are discussed.     

Collective Bow Shock Ahead of a Transverse System of Spheres in a Supersonic Flow Behind a Moving Shock Wave

The results of investigating the dynamics and physical conditions of formation of a collective bow shock ahead of a system of spheres with the line of centers normal to the supersonic flow behind a traveling shock wave are presented. Two types of shock-wave patterns that necessarily precede the formation of the collective shock wave and correspond to regular and Mach interaction of the bow shocks were detected experimentally. On the basis of a local gasdynamic-discontinuity interference theory, quantitative criteria of the existence of these regimes and of the formation of a common shock wave are determined. These criteria are confirmed in a series of experiments for the transitional regimes.