Laminar Base Flow Downstream of Slender Cones in Hypersonic Flow

The base flow downstream of slender cones in a stream of perfect gas at Mach numbers 8 and 10 and Reynolds numbers 10⁴ and 10⁵ is numerically investigated. The calculated heat fluxes to the rear face of the body are compared with experimental data. It is shown that the friction and heat transfer coefficients increase without bound as the corner point is approached from both the lateral surface and the rear face, the sign of the latter coefficient being dependent on the body surface temperature factor.     

Tollmien-Schlichting Waves in a Hypersonic Boundary Layer Flow in the Neighborhood of a Cooled Surface

A nonlinear time-dependent model of the development of longwave perturbations in a hypersonic boundary layer flow in the neighborhood of a cooled surface is constructed. The pressure in the flow is assumed to be induced the combined variation of the thicknesses of the near-wall and main parts of the boundary layer. Numerical and analytic solutions are obtained in the linear approximation. It is shown that if the main part of the boundary layer is subsonic as a whole, its action reduces the perturbation damping upstream and the perturbation growth downstream, while a supersonic, as a whole, main part of the boundary layer creates the opposite effects. An analysis of the solutions obtained makes it possible to conclude that the asymptotic model proposed can describe the three-dimensional instability of the Tollmien-Schlichting waves.     

A Limiting Solution for Flow Past a Delta Wing in the Presence of Supercritical Flow Regions

The flow past a planar delta wing is studied for strong interaction between the boundary layer and the outer supersonic flow. An analytic investigation is carried out using the Newtonian passage to the limit in which the specific heat ratio tends to unity and the Mach and Reynolds numbers to infinity. Possible flow regimes are classified for various wing aspect ratios. For determining the supercritical-subcritical flow transition line an analytic expression, correct to the second approximation, is obtained for flow past a cold wing with a fairly large aspect ratio in which the transverse boundary-layer flows are insignificant.     

Magnetohydrodynamic control of supersonic flow past bodies: Possibilities and undesirable effects

Basic problems of super-and hypersonic magnetohydrodynamics (MHD) associated with the determination of the integral characteristics of bodies and vehicles inside which there are systems generating a uniform magnetic field are considered. Three classes of flows, namely, flow in a hypersonic multimode fixed-geometry air-intake; internal and external flow in a model of a hypersonic vehicle containing an air-intake with an MHD generator, a combustion chamber, and a supersonic nozzle; and hypersonic flow past a blunt cone are studied using numerical simulation and theoretical analysis (on the basis of the complete averaged system of Navier-Stokes equations and the electrodynamic equations). Attention is concentrated on the presence of an additionalmagnetic force acting on the system generating themagnetic field and, consequently, on the body and initiating an additional drag (in the case of a vehicle-reducing its thrust). Attractive possibilities for MHD flow control, namely, an increase in the degree of flow compression in the air-intake, a reduction in the ignition length in the combustion chamber, and a decrease in the heat flux to the nose of the body, are noted, as well as negative effects associated with the action of the magnetic force on the bodies considered.     

Numerical Calculation of the Hypersonic Rarefied Transverse Flow Past a Cold Flat Plate

The hypersonic rarefied transverse flow past a flat plate is considered over a wide Knudsen number range. The problem is formulated for a model kinetic equation and solved using an implicit finite-difference second-order method. The results presented demonstrate the Knudsen and Mach number effect on the aerodynamic characteristics of the plate and the flow pattern.     

Effect of Spherical Recesses on the Characteristics of Coanda Flow

Sub- and supersonic flows past curvilinear surfaces with spherical recesses are investigated. The Coanda flow was created by a jet flowing out from a plane convergent nozzle into a submerged space along the tangent to a circular cylinder. The forces exerted on the cylinder and the total and static pressure profiles in Coanda jet cross-sections were measured. It is shown that the spherical recesses increase the friction drag at both sub- and supersonic velocities.     

Supersonic transverse rarefied gas flow past a strip

The supersonic flow of a monatomic gas consisting of hard spherical particles past a flat strip normal to the flow is investigated using the direct simulation Monte-Carlo (DSMC) method. The calculations are performed over the Knudsen and Mach number ranges 0.015–5 and 1.8–15, respectively. The structure of the compressed layer and the aerodynamic characteristics are systematically studied for the Mach number 5 and various Knudsen numbers. The dependences of the compressed-layer thickness in molecular free paths are found. The nonequilibrium processes in the neighborhood of the strip are described on the basis of the data on the temperature anisotropy with respect to three coordinates.__________Translated from Izvestiya Rossiiskoi Academii Nauk, Mekhanika Zhidkosti i Gaza, No. 1, 2005, pp. 159–167. Original Russian Text Copyright © 2005 by Maltsev and Rebrov.     

Three-Dimensional Interaction of a Blunt Cone with a Hot Region in a Supersonic Flow in the Presence of Surface Injection

The problem of the interaction of a blunt cone placed at zero incidence in a supersonic flow with a spherical hot region in the incident flow is considered for the case in which the hot region center is displaced relative to the axis of symmetry of the body. Two cases are studied: (1) the interaction of temperature inhomogeneity with an impermeable conical surface and (2) interaction in the presence of intense surface injection localized on the spherical bluntness of the body. It is shown that strong surface injection considerably improves the flow pattern and the aerodynamic characteristics of the body.     

Distinctive Features of the Lateral Flow for a Convergent Air-Intake with a Convergent Nose Compression Surface

The results of numerical and experimental studies of a model configuration of a hypersonic vehicle realizing the principle of compression convergence of the entire jet captured by an air-intake from the oncoming stream are presented. The external flow past a convergent air-intake integrated with a transversely-concave nose compression surface is investigated over the freestream Mach number range from 2 to 6. The salient features of the flow pattern near air-intakes with sidewalls of different length are established and the influence of a limitation on the lateral flow near the external compression wedge on the flow rate characteristics of the air-intake is established. The numerical calculations are performed within the framework of the inviscid gas model using higher-order TVD schemes; the calculated and experimental results are compared.     

Jet Flow Past a Plate with a Spoiler in the Presence of a Stagnation Zone

An exact analytical solution of the problem of the jet flow past a flat plate with a spoiler is obtained for the case in which there is a stagnation zone near the spoiler. The Chaplygin method of singular points and the theory of elliptic theta-functions are used to construct the solution. The pressure in the stagnation zone is determined from the Brillouin-Villat condition of smooth separation. It is found that the lift and drag coefficients, considered as functions of the stagnation zone length, have extrema at points corresponding to the smooth separation condition.     

Stability of the Hypersonic Shock Layer on a Flat Plate

The stability of hypersonic viscous gas flow in a shock layer in the neighborhood of a flat plate is considered. The stability of the velocity, temperature, density, and pressure profiles calculated on the basis of the complete viscous shock layer equations is investigated within the framework of the linear stability theory with allowance for the shock wave relations. The calculated perturbation growth rates and phase velocities are compared with the experimental data obtained by means of electron-beam fluorescence.     

Features of internal and external flows in high-speed vehicles with a magnetohydrodynamic air-intake

The features of the internal and external flows in high-speed vehicles with a magnetohydrodynamic air-intake ensuring additional deceleration of the supersonic flow are considered. Preliminary investigations carried out earlier showed that this MHD flow control makes it possible significantly to increase the gasdynamic component of the vehicle thrust. However, there are significant negative effects, mainly the development of an additional vehicle drag force associated with the magnetic field. Thus, there arises a complex of interrelated problems with opposite effects on the resulting characteristics of the vehicle. In the present study these questions are investigated both on the basis of developed physicomathematical models and numerical methods and by means of the combined optimization of the internal duct profile and the external configuration of the vehicle. It is shown that a strategy for improving the vehicle characteristics can only be chosen by simultaneously analyzing the features of the internal (magnetohydrodynamic) and external (gasdynamic) flows.     

用LDV系统测量转盘萃取塔内流场

本文应用激光多普勒测速仪对二种转盘萃取塔模型进行切向速度、轴向速度和湍流度测量。实验结果表明，在ＲＤＣ是切向速度比较大，因而有较大的搅拌效果，它的内部流场比较均匀稳定，有利于传质，所以ＲＤＣ是广泛应用于化学工业中的一种液－液萃取设备。     

Effect of a Dispersed Admixture on the Flow Pattern and Heat Transfer in a Supersonic Dusty-Gas Flow Around a Cylinder

A mathematical model of two-phase (gas-solid particle) flow which takes into account particle-particle collisions and the feedback effect of the admixture on the gas parameters is proposed. The dispersed phase is described by a kinetic equation of the Boltzmann type and the carrier gas by modified Navier-Stokes equations. Using this model, a supersonic uniform dusty-gas flow past a cylinder is calculated. The fields of the macroparameters of the admixture and the carrier medium are obtained. The dependence of the heat transfer at the stagnation point on the relative particle size and the free-stream admixture concentration is studied in detail. The ranges of these parameters on which particle collisions and the feedback effect of the admixture on the carrier-gas flow are important are found.     

Hypersonic flow past a plane magnetic dipole with parallel orientation of the magnetic moment and free-stream velocity vectors for moderate magnetic Reynolds numbers

The two-dimensional problem of hypersonic flow past a cylindrical body with a plane magnetic dipole in the presence of an external magnetic field is considered. The magnetic moment of the dipole is parallel to the free-stream velocity. The flow parameters correspond to a velocity of 7000 m/s at an altitude of approximately 65 km in the Earth’s atmosphere. The system of MHD equations (the Euler equations with volume MHD momentumand energy sources and the magnetic induction equation) was solved using the stabilization method. The calculations were carried out for two magnetic Reynolds numbers: (Re_m)₁ = 0.18 (corresponds to the parameters of the equilibrium ionized plasma in the shock layer) and (Re_m)₂ = 1.8 (the plasma conductivity increases by a factor of 10). The solutions obtained are analyzed, the effect of Re_m on the flow characteristics, namely, the shock wave stand-off from the body, the configuration of the vortex structures, and the aerodynamic and ponderomotive components of the body drag, is determined.     

On the Electric Potential Induced by a Homogeneous Magnetic Field in a Turbulent Pipe Flow

In this paper we study a turbulent pipe flow of a weakly electrical conducting fluid subjected to a homogeneous magnetic field which is applied perpendicular to the flow. This configuration forms the basis of a so-called electromagnetic induction flow meter. When the Hartmann number is small so that modification of flow by the Lorenz force can be neglected, the influence of the magnetic field results only in a spatially and temporally varying electric potential. The magnitude of the potential difference across the pipe is then proportional to the flow rate and this constitutes the principle of the flow meter. In this study the flow and electric potential are computed with help of a numerical flow simulation called Large-Eddy Simulation (LES) to which we have added an equation for the electrical potential. The results of the LES have been compared with experiments in which the electric potential is measured as a function of time at several positions on the circumference of the pipe. Both the experimental and numerical results for the mean potential at the pipe wall agree very well with an exact solution that can be obtained in this particular case of a homogeneous magnetic field. Furthermore, it is found that fluctuations in the electric potential due to the turbulence, are small compared to the velocity fluctuations. Based on the results we conclude that electrical-magnetic effects in pipe flow can be accurately computed with LES.     

Rayleigh–Taylor Instability of Rotating Oldroydian Viscoelastic Fluids in Porous Medium in Presence of a Variable Magnetic Field

The instability of the plane interface between two oldroydian viscoelastic superposed fluids in the presence of uniform rotation and variable magnetic field in porous medium is considered. For potentially stable configuration, the system is found to be stable for disturbances of all wave numbers. The magnetic field succeeds in stabilizing certain wave-number range, which were unstable in the absence of magnetic field and rotation for the potentially unstable configuration. Sub cases of magnetic free and rotation free configurations are also considered, separately.     

Numerical Simulation of Plasma Dynamics in a Nonuniform Magnetic Field

An efficient algorithm is proposed enabling numerical simulations of plasma dynamics in a nonuniform magnetic field. The present numerical data are in good agreement with experimental data obtained in a GOL-3 setup and with previous simulations. The experimentally observed effect of fast transfer of energy to ions is confirmed. __________ Translated from Prikladnaya Mekhanika i Tekhnicheskaya Fizika, Vol. 47, No. 1, pp. 35–45, January–February, 2006.     

Nonlinear Responses of a Magnetoelastic Beam in a Step-Pulsed Magnetic Field

A theoretical study is carried out on the dynamics of a magnetoelastic beam being in a step-pulsed magnetic field. For this aim, the magnetic potential and elastic energies are determined for the beam and partial differential equations are established according to Hamilton's principle. It is proven that the magnetoelastic beam can give a variety of complex behavior in the case of step-pulsed field excitations. An intermediate regime of two-well chaos is observed. Theoretical findings were found to be in a good agreement with the experimental results for the specific system parameters. On leave from Institute of Physics, University of Bayreuth, 65440 Bayreuth, Germany An erratum to this article is available at .     

On the Role of Vibrational Excitation in Hypersonic Flow Computations

Abstract. The paper investigates the influence of the thermochemical modeling on the flow-field properties for both compressing and expanding flows. For the nitrogen hypersonic flow over a cylinder a comparison between a model neglecting vibrational energy and two-temperature Park's nonequilibrium model has been performed in a wide variety of experimental and free flight conditions. It is shown that the differences are confined in a thin layer behind the bow shock while the overall flow properties are slightly affected. For the expanding air flows inside hypersonic facilities, besides the two models mentioned above, vibrational equilibrium and CVDV model have been compared. It was found that vibrational nonequilibrium can not be disregarded but no discernible differences have been observed between Park's and CVDV model results, unless the enthalpy is very large.Sommario. L'articolo analizza l'influenza della modellizzazione termochimica sul campo fluidodinamico nel caso di flussi ipersonici sia in compressione che in espansione. Per il flusso di azoto attorno ad un cilindro è stato effettuato un confronto fra un modello che trascura l'energia vibrazionale ed il modello di non-equilibrio a due temperature di Park. L'analisi è stata condotta per un ampio intervallo di variazione dei parametri caratteristici comprendente condizioni sia di volo che di prove in laboratorio. Il confronto ha mostrato che l'effetto del non-equilibrio vibrazionale è sempre limitato ad una regione molto sottile dietro l'onda d'urto e che l'influenza sulle proprietà generali del flusso è in ogni caso modesta. Per il caso dei flussi in espansione in gallerie ipersoniche si è invece assunto come gas l'aria ed oltre ai due modelli già menzionati sono stati utilizzati anche il modello di equilibrio vibrazionale ed il modello CVDV. Si è osservato che per i flussi in espansione il non-equilibrio vibrazionale non può essere trascurato ma che comunque i modelli di Park e CVDV sono sostanzialmente equivalenti tranne nei casi di valori molto elevati dell'entalpia totale.