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Ignition of Hydrocarbon-Air Supersonic Flow by Volumetric Ionization

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Journal of Thermal Science 2015年第6期24卷 583-590页

作者： Marat A.Goldfeld George A.Pozdnyakov Khristianovich institute of theoretical and applied Mechanics SB RAS

The paper describes the results of the electron-beam initiation of the combustion in the mixtures of hydrogen,natural gas or kerosene vapors with *** beam characteristics were studied in closed volume with immobile *** researches included definition of an integrated current of an electronic beam,distribution of a current density and an estimation of average energy of *** of fuel mixtures ignition by means of this approach in the combustor at high velocity at the entrance was *** were carried out at Mach numbers of 4 and *** of ignition and combustion under electron beam action was *** was revealed that ignition of mixture occurs after completion of electron gun *** obtained have confirmed effectiveness of electron beam application for ignition of hydrogen and natural *** numerical simulation of the combustion of mixture in channel was carried out by means of ANSYS CFD 12.0 instrumentation on the basis of Reynolds averaged Navier-Stokes equation using SST/k-ωturbulence *** combustion modeling,a detailed kinetic scheme with 38 reactions of 8 species was implemented taking into account finite rate *** have shown that the developed model allow to predict ignition of a mixture and flame propagation even at low flow temperatures.

关键词： supersonic flow combustor electron bean ignition delay numerical simulation.

Numerical and Experimental Studies of 3D Hypersonic Inlet

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Journal of Thermal Science 2002年第3期11卷 198-206,219页

作者： MaratA.Goldfeld RomanV.Nestoulia institute of theoretical and applied Mechanics Novosibirsk Russia

The results of numerical and experimental studies of a new configuration of 3D hypersonic inlet with the minimum throat area, which was called a convergent inlet, are presented in this paper. It is shown that the use of this inlet configuration allows one to reduce the drag and thermal protection of surfaces of a hypersonic engine within the entire range of flight velocities. The calculations were performed within the framework of inviscid gas model by the method of finite volumes. The flow and inlet characteristics, taking account of viscosity, were also calculated using the boundary layer equations. The experimental studies were performed within the Mach number range from 2 to 10.7 and Reynolds number based on the model inlet height of Re=1-5×106. The results included the flow parameters on the external compression surface and in the inlet duct, the Mach number in the throat, the air flow rate, the total pressure recovery coefficient, the inlet drag, and the boundary layer characteristics on

关键词： hypersonic inlet convergent inlet boundary layer.

Skin Friction Gage for Measurements in Hypersonic Flow

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Journal of Thermal Science 2003年第1期12卷 44-50页

作者： Francois Falempin Marat Goldfeld Roman Nestoulia EADS Aerospatiale Matra Missiles ChatillonInstitute of Theoretical and Applied Mechanics NovosibirskInstitute of Theoretical and Applied Mechanics Novosibirsk France Russia Russia

A description and results of tests of a new small-scale gage for direct measurement of skin friction force are presented in the *** gage design provides separated measurement of longitudinal and transversal component of friction *** of this scheme provides high sensitivity and necessary high-frequency response of the *** tests of the gage were carried out in a blow down wind tunnel at Mach numbers of 2 and 4 within the range of Reynolds numbers Rex from 0.8 to 5 million and in the hot-shot wind tunnel at Mach number 6 and Reynolds numbers Rex=2.5-10 *** measurements of skin friction were carried out on a flat plate and on a ramp beyond the shock *** with the direct measurement of friction in the blow down wind tunnel,the measurements of profiles of average velocities and mass flow rate pulsations were *** of measurement errors has shown that the friction gage permits to measure skin friction coefficient on a flat plate with mistake not more than 10%.

关键词： skin friction gage hypersonic flow scramjet.

Orientation dependence of structural transition in fcc Al driven under uniaxial compression by atomistic simulations

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Chinese Physics B 2011年第4期20卷 391-396页

作者：李莉邵建立段素青梁九卿 institute of theoretical Physics and Department of Physics Shanxi University institute of applied Physics and Computational Mathematics

By molecular dynamics simulations employing an embedded atom method potential, we have investigated structural transformations in single crystal A1 caused by uniaxial strain loading along the [001], [011] and [111] directions. We find that the structural transition is strongly dependent on the crystal orientations. The entire structure phase transition only occurs when loading along the [001] direction, and the increased amplitude of temperature for [001] loading is evidently lower than that for other orientations. The morphology evolutions of the structural transition for [011] and [111] loadings are analysed in detail. The results indicate that only 20% of atoms transit to the hcp phase for [011] and [111] loadings, and the appearance of the hcp phase is due to the partial dislocation moving forward on {lll}fcc family. For [011] loading, the hcp phase grows to form laminar morphology in four planes, which belong to the {111}fcc family; while for [111] loading, the hcp phase grows into a laminar structure in three planes, which belong to the {111}fcc family except for the （111） plane. In addition, the phase transition is evaluated by using the radial distribution functions.

关键词： single crystal Al molecular dynamics simulations uniaxial compression phase transition

Particle-number conserving analysis of the high-K multi-quasiparticle bands in ^(179)Re

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Chinese Physics C 2010年第12期34卷 1836-1841页

作者：张振华徐巧红孙宝玺 institute of theoretical Physics Chinese Academy of Sciences institute of theoretical Physics College of Applied Sciences Beijing University of Technology

The experimentally observed ten rotational bands in 179Re are analyzed with the particle-number conserving method for treating the cranked shell model with pairing interaction, in which the blocking effects are taken into account exactly. The experimental moments of inertia of these bands are reproduced quite well by our calculations with no free parameter and the deformation driving effects are discussed. The bandhead energies and the variation in the occupation probability of each cranked orbital are also analyzed.

关键词： multi-quasiparticle band moment of inertia blocking effect particle-number conserving method

Construction of AFLT States by Reflection Method and Recursion Formula

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Communications in theoretical Physics 2014年第1期61卷 56-68页

作者：寿暴吴剑锋喻明 institute of theoretical Physics Chinese Academy of Sciences institute of theoretical Physics Department of Applied Mathematics and PhysicsBeijing University of Technology

The AFLT states|PY1,Y2has reflection symmetry,Sn|PY1,Y2=|PY2,Y2,nb=2P,where S is the screening *** state can be constructed using this reflect *** propose a recursion formula for this *** recursion formula is factoriz... 详细信息

关键词： AGT duality AFLT states reflection method recursion formula

Nonadiabatic Effect on the Rescattering Trajectories of Electrons in Strong Laser Field Ionization Process

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Chinese Physics Letters 2016年第9期33卷 29-31页

作者：涂心海郝小雷李卫东胡师林陈京 institute of theoretical Physics and Department of Physics Shanxi University institute of applied Physics and Computational Mathematics

The important features of the rescattering trajectories in strong field ionization process such as the cutoff of the return energy at 3.17Up and that of the final energy at 10Up are obtained, based on the adiabatic approximation in which the initial momentum of the electron is assumed to be zero. We theoretically study the nonadiabatic effect by assuming a nonzero initial momentum on the rescattering trajectories based on the semiclassical simpleman model. We show that the nonzero initial momentum will modify both the maximal return energy at collision and the final energy after backward scattering, but in different ways for odd and even number of return trajectories. The energies are increased for even number of returns but are decreased for odd number of returns when the nonzero （positive or negative） initial momentum is applied.

关键词： of it in Nonadiabatic Effect on the Rescattering Trajectories of Electrons in Strong Laser Field Ionization Process on is that for

The effect of electron initial longitudinal velocity on the non-sequential double ionization process in an elliptically polarized laser field

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Chinese Physics B 2012年第8期21卷 191-196页

作者：郝小雷李卫东刘杰陈京 institute of theoretical Physics and Department of Physics Shanxi University Center for applied Physics and Technology Peking University institute of applied Physics and Computational Mathematics

The effect of initial longitudinal velocity of the tunnelled electron on the non-sequential double ionization （NSDI） process in an elliptically polarized laser field is studied by a semiclassical model. We find that the non-zero initial longitudinal velocity has a suppressing effect on single-return collision （SRC） events in the double ionization process, more specifically, it results in an obvious reduction in the center part of the correlation momentum distributions in the direction of the major polarization axis （z axis） and makes the distribution of single-return collision in the minor polarization axis （x axis） become narrower.

关键词： non-sequential double ionization initial longitudinal velocity elliptically polarized laserfield single return collision

The Research of Laminar-Turbulent Transition in Hypersonic Three-Dimensional Boundary Layer

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Journal of Thermal Science 2005年第2期14卷 103-107页

作者： Marat A.GOLDFELD Evgeniy V.ORLIK institute of theoretical and applied Mechanics 4/1 Institutskaya Str. Novosibirsk 630090RussiaInstitute of Theoretical and Applied Mechanics 4/1 Institutskaya Str.Novosibirsk 630090Russia

The results of experimental investigation of laminar-turbulent transition in three-dimensional flow under the high continuous pressure gradient including the flow with local boundary layer separation are presented. The experimental studies were performed within the Mach number range from 4 to 6 and Reynolds number 10-60×106 1/m, the angles of attack were 0° and 5°. The experiments were carried out on the three-dimensional convergent inlet model with and without sidewalls. The influence of artificial tubulator of boundary layer on transition and flow structure was studied. The conducted researches have shown that adverse pressure gradient increase hastens transition and leads to decrease of transition area length. If pressure gradient rises velocity profile fullness increases and profile transformation from laminar to turbulent occurs. As a result of it the decrease of separation area length occurs. The same effect was reached with Reynolds number increase. These results are compared with the data on two-dimensional model with longitudinal curvature.

关键词： hypersonic boundary layer transition convergent inlet adverse pressure gradient.