Enhanced Raman-scattering measurements in low-density supersonic flows

Raman scattering, enhanced by a light trapping cell, has been used to measure temperature and density in the inviscid and viscous regions of the flow from an open-jet supersonic nozzle. Raman temperatures and densities in the inviscid regions are in excellent agreement with static temperatures and densities calculated from measurements of stagnation temperature, stagnation pressure and Pitot pressure.     

Passive scalar intermittency in low temperature helium flows

We report new measurements of mixing of passive temperature field in a turbulent flow. The use of low temperature helium gas allows us to span a range of microscale Reynolds number, R(lambda), from 100 to 650. The exponents xi(n) of the temperature structure functions approximately r(xi(n)) are shown to saturate to xi(infinity) approximately 1.45+/-0.1 for the highest orders, n approximately 10. This saturation is a signature of statistics dominated by frontlike structures, the cliffs. Statistics of the cliffs' characteristics are performed, particularly their widths are shown to scale as the Kolmogorov length scale.     

Passive scalar transport in peripheral regions of random flows

We investigate statistical properties of the passive scalar mixing in random (turbulent) flows assuming its diffusion to be weak. Then at advanced stages of the passive scalar decay, its unmixed residue is primarily concentrated in a narrow diffusive layer near the wall and its transport to the bulk goes through the peripheral region (laminar sublayer of the flow). We conducted Lagrangian numerical simulations of the process for different space dimensions d and revealed structures responsible for the transport, which are passive scalar tongues pulled from the diffusive boundary layer to the bulk. We investigated statistical properties of the passive scalar and of the passive scalar integrated along the wall. Moments of both objects demonstrate scaling behavior outside the diffusive boundary layer. We propose an analytic scheme for the passive scalar statistics, explaining the features observed numerically.     

Passive scalar structures in peripheral regions of random flows

The statistical properties of the passive scalar near walls in random flows assuming a weakness of its diffusion have been investigated. Then, at advanced stages of the passive scalar mixing, its unmixed residue is concentrated in a narrow diffusive layer near the wall. The numerical simulations have revealed the structures responsible for the passive scalar transport to the bulk; these are passive scalar tongues pulled from the diffusive boundary layer. The passive scalar integrated along the wall possesses a well-pronounced scaling behavior. An analytical scheme, giving exponents of the integral passive scalar moments has been proposed. The exponents reasonably agree with the calculations in 3d. The text was submitted by the authors in English.     

Large-eddy simulation of shock-turbulence interaction in supersonic diffuser flows

LES based on explicit filtering is used to study the shock train phenomenon in turbulent supersonic diffuser flows with circular cross-section and isothermal wall with an incoming pipe flow at friction Reynolds number 245 and centerline Mach number 1.7. Alternate regions of compression and expansion are found in the shock train which is followed by a shock-free ‘mixing’ region as observed in experiments and simulations in the literature. Turbulence amplification and local peaks in pressure-dilatation correlation are observed in the vicinity of the shocks. Low-frequency oscillations of the shock train are also observed.     

Calculating pressure fields on the basis of PIV-measurements for supersonic flows

The velocity fields obtained by PIV (Particle Image Velocimetry) in supersonic flows are not sufficient to determine the integral characteristics of the flow. Additional data, for example, on pressure can be obtained from the solution of the Navier?Stokes equations. For incompressible flows, the solution of these equations is not too complicated. However, for supersonic flows, the need to take into account the flow density and the increasing number of experimental errors make it more difficult. This paper proposes a new method for calculating density and pressure from PIV data on the basis of the continuity equation. This method is robust and easy to implement for compressible flows.     

Ignition of supersonic propane-air flows by electric discharge

Ignition of supersonic propane-air flows by electrode discharge is experimentally investigated for various propane supply systems, electrode-flow relative configurations, and durations of energy deposition.     

Velocity vorticity vector behavior in supersonic flows behind discontinuity surfaces

The behavior of the velocity vorticity vector on a discontinuity surface arising in the supersonic non-uniform flow of combustible gas around a body with the formation of a shock or detonation wave is studied. The free stream is generally vortical and has a given distribution of parameters. The formulas are obtained for the vorticity vector components in a special coordinate system related to the wave. It is shown that in this case the vorticity vector normal to the wave remains continuous across the discontinuity surface, and in the case of axisymmetric flows, also the quantity remains continuous, which is equal to the ratio of the tangent vorticity component to density, although the quantities themselves taken separately undergo a discontinuity. The work was financially supported by the Russian Foundation for Basic Research (Project 05-01-00004) and by the Far-Eastern Branch of RAS (Project 2-C0-009).     

COIL超声速流动的水汽凝结效应数值模拟

 在开发的化学氧碘激光器3维化学反应流程序中增设水汽凝结功能,模拟了以氦气和氮气作稀释气体条件下,基于RADICL装置喷管中含水汽凝结的流动。模拟结果给出了水汽凝结形成的5种尺寸液滴的数密度分布及流场各物理量分布,比较了有无水汽凝结时气流的压力、温度、增益分布的变化。模拟结果发现,凝结使气流温度在靠近喉部的下游升高,增益峰值增高。     

Laser imaging system for determination of three-dimensional scalar gradients in turbulent flames

An imaging system for the measurement of three-dimensional (3D) scalar gradients in turbulent hydrocarbon flames is described. Combined line imaging of Raman scattering, Rayleigh scattering, and CO laser-induced fluorescence (LIF) allows for simultaneous single-shot line measurements of major species, temperature, mixture fraction, and a one-dimensional surrogate of scalar dissipation rate in hydrocarbon flames, while simultaneous use of two crossed, planar LIF measurements of OH allows for determination of instantaneous flame orientation. In this manner the full 3D scalar dissipation can be estimated in some regions of a turbulent flame on a single-shot basis.     

Numerical investigation of cross-flow separation in three-dimensional supersonic flows around circular cones

The problem of supersonic three-dimensional flow over sharp cones is solved using the system of Navier-Stokes equations in a locally conical approximation. Numerical solutions are found using an implicit finite-difference scheme with second-order exponential approximation of the equations with respect to the cross-flow coordinate. The appearance and development of cross-flow separation on the leeward side of the cones in a laminar regime of gas flow in the shock layer are investigated. Zh. Tekh. Fiz. 68, 20–26 (October 1998)     

翼片扰动对COIL超音速平行流混合的影响

氧碘混合过程是化学氧碘激光器(COIL)中的一个重要步骤,氧碘混合质量直接决定着COIL的运行效率和光束质量。采用化学荧光法,研究了两种不同结构的扰动翼片组对COIL超音速平行流混合过程的影响。实验结果表明,1#扰动翼片组对氧碘超音速平行流的混合增强效果明显,其荧光区达到主气流中心线所经历的流向距离大幅缩短,碘解离区内的荧光区与测试区的面积比相对于无混合扰动时提高了4.2倍;采用2#翼片组扰动混合时,流向距离值进一步缩短了40%~60%,碘解离区内的面积比值又提高了20%~40%。氧发生器有/无主载气条件(2#翼片组)下的混合过程比较显示后者混合效果更好。     

Experimental investigations of detonation initiation by hot jets in supersonic premixed flows

<正>A new method to initiate and sustain the detonation in supersonic flow is investigated.The reaction activity of coming flow may influence the result of detonation initiation.When a hot jet initiates a detonation wave successfully, there may exist two types of detonations.If the detonation velocity is greater than the velocity of coming flow,there will be a normal detonation here.Because of the influence of boundary layer separation,the upstream detonation velocity is much greater than the Chapman-Jouguet(CJ) detonation velocity.On the other hand,if the detonation velocity is less than the velocity of coming flow,an oblique detonation wave(ODW) will form.The ODW needs a continuous hot jet to sustain itself.If the jet pressure is lower than a certain value,the ODW will decouple.In contrast,the normal detonation wave can sustain itself without the hot jet.     

Numerical simulation of asymmetric non-steady-state turbulent flows around supersonic sharp cones

Results are presented of a numerical simulation of turbulent flows around pointed circular supersonic cones at angles of attack α≥3θ_c, where θ_c is the cone half-angle. The problem is solved in the framework of a locally conical approximation of a set of Reynolds’ equations written in terms of mass-averaged quantities with the use of a differential one-parametric turbulence model. The numerical solutions are obtained with the help of an implicit finite-difference unidirectional scheme, with the focus on violation of the symmetry and stationarity of the separated cross flow.     

Application of PIV to over-expanded supersonic flows: Possibilities and limits

Two-dimensional velocity distributions outside a Mach 2.0 supersonic nozzle have been investigated using a digital particle im age velocimetry (PIV). Mean velocities , vor ticity field and volume dilatation field were obtained from PIV images using 0 .33 μm titanium dioxide (TiO₂) particle. The seeding particle of larger size , 1.4 μrn Ti0₂, was also used for the experimental comparison of velocity lag downstream of shock waves. The results have been compared and analyzed with schlieren photographs for the locations of shock waves and over-expanded shock structure to inspect possibilities and limits of a PIV technique to over-expanded supersonic flows. It is found that although the quantitative velocity measurement using PIV on over-expanded supersonic flows with large velocity and pressure gradients is limited, the locations of normal shock and oblique shock waves can be resolved by the axial/radial velocity fields, and over-expanded shock structure can be predicted by vorticity field and volume dilatation field which are acquired from the spatial differential of the velocity field.     

Eulerian–Lagrangian multiscale methods for solving scalar equations – Application to incompressible two-phase flows

The present article proposes a new hybrid Eulerian–Lagrangian numerical method, based on a volume particle meshing of the Eulerian grid, for solving transport equations. The approach, called Volume Of Fluid Sub-Mesh method (VOF-SM), has the advantage of being able to deal with interface tracking as well as advection–diffusion transport equations of scalar quantities. The Eulerian evolutions of a scalar field could be obtained on any orthogonal curvilinear grid thanks to the Lagrangian advection and a redistribution of particles on the Eulerian grid. The Eulerian concentrations result from the projection of the volume and scalar informations handled by the particles. The particle velocities are interpolated from the Eulerian velocity field. The VOF-SM method is validated on several scalar interface tracking and transport problems and is compared to existing schemes within the literature. It is finally coupled to a Navier–Stokes solver and applied to the simulation of two free-surface flows, i.e. the two-dimensional buckling of a viscous jet during the filling of a square mold and the three-dimensional dam-break flow in a tank.