Gas flow in cylindrical capillaries under intermediate conditions

At present, there are sufficient solutions of the problem of free-molecular gas flow through a short cylindrical channel, for example, [1–3]. In intermediate flow conditions, for Knudsen number Kn 1, solutions have been obtained for the limiting cases: an infinitely long channel [4] and a channel of zero length (an aperture) [5]. However, no solution is known for short channels for Kn 1. The present work reports a calculation by the Monte Carlo method of the macroscopic characteristics of the gas flow through a short cylindrical channel (for various length—radius ratios), taking into account intermolecular collisions.Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 1, pp. 187–190, January–February, 1977.     

Investigation of isothermal flow of a mixture of gas and particles in a channel of variable section

Isothermal flow of a gas with particles is investigated analytically, which makes it possible to analyze all possible flow regimes in channels of different shapes. It is shown that in a channel of constant section there are two possibilities: either an equilibrium regime is established with constant flow parameters, or the gas reaches the velocity of sound, and then further flow in the channel is impossible (blocking of the channel). In a contracting nozzle, blocking also occurs if the channel is sufficiently long. In an expanding nozzle when there are particles in the gas with a velocity lower than the gas velocity, it is possible to have flow regimes with transition through the velocity of sound: a subsonic flow goes over into a supersonic flow and, conversely, it is also possible to have a flow in which there is blocking of the channel, which is quite different from the flow of a pure gas in an expanding nozzle and is due to the influence of interphase friction on the flow. The variation of the pressure along the flow can be nonmonotonic with points of local maximum or minimum which do not coincide with the singular point at which the gas velocity reaches the velocity of sound. In the case of nonequilibrium gas flows with particles in a Laval nozzle, the velocity of the gas may become equal to the isothermal velocity of sound not only in the exit section of the nozzle or in its expanding part, as noted in [4–6], but also at the minimal section, since it is possible to have flows for which the velocities of the phases are equalized at this section.Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 6, pp. 61–68, October–December, 1981.     

Calculations of subsonic inviscid flows in axisymmetric channels with division of the flow

The flow of gas in a channel with division of the flow by a longitudinal baffle is characterized by the ratio m of the flow rates in the exterior (G_e) and interior (G_i) parts of the channel: m = G_e/G_i. For example, flow in a channel with a wall screen forming a narrow annular slit with the channel wall corresponds to m 1. In the case of a gas extraction pipe in the channel m 1. In two-profile gas turbine engines m is of the order of unity or several units [1]. Flow in a channel with a baffle is characterized by the presence of a liquid boundary between the flows up to the start of the baffle. For given shape of the channel and baffle, the position of the separating stream surface depends on the conditions of the problem. In the present paper, the influence of the flow rate ratio m on the flow pattern in such a channel is investigated numerically.Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 4, pp. 154–156, July–August, 1981.     

Optimal blunt-nosed figures of revolution in a gas of different rarefactions

Many studies have been made of the optimization of the shape of bodies in a gas stream. However, the majority of these have been made for supersonic and hypersonic flow in the limiting case of a continuum [1], and only a few studies have been made [1–3] for the case of flow over a body of a rarefied gas (mainly a free molecular stream). In the present paper, the problem of shape optimization is considered for hypersonic flow of a gas of different rarefactions over a body. Numerical methods are used to investigate the influence of the Reynolds number on the shape and drag of optimal figures of revolution.Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 3, pp. 158–161, May–June, 1980.     

Unsteady flows of an erosion plasma in irradiation of solid targets by annular beams

In recent times high-pressure physics has made ever wider application of constructions which use convergent shock waves [1–8]. The study of gas dynamic flows with convergent shock waves imposes the need for more careful calculation of the motions of a gas in regions whose dimensions are much less than the characteristic dimensions of the flow. In the present study the numerical method is used to study the gas dynamic phenomena accompanying the irradiation of solid obstacles by annular beams of monochromatic radiation.Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 6, pp. 179–182, November–December, 1988.In conclusion we note that at very short durations t t_k the solution to the problem is similar to the flow during separation of a gaseous toroid [19].     

Heat transfer in subsonic high-temperature gas flow through three-dimensional curved channels

The heat transfer in subsonic high-temperature (T 2000°K) gas flow through a curved channel of rectangular cross section has been experimentally investigated. The local heat flow into the channel wall was measured by the modified gradient method, which consists in subdividing the walls by means of thin annular thermally-insulating partitions, measuring the temperature in the upper (gas) and lower (coolant) sections of the modules thus formed, and using these measurements to determine the local heat flux q_w on the assumption that the thermal field in the module is homogeneous. The soundness of this method has been demonstrated theoretically and experimentally and the expediency of using it in the intensive wall cooling regime has been confirmed. The method is employed to find the local heat flux fields over the- entire surface of the channel. The integrated fluxes q_w coincide to within 5% with the independently determined total increase in the enthalpy of the water in the cooling channels. A distinguishing feature of the investigation is the high relative curvature of the bend in the channel, which leads to the formation of a zone of intense separation on the convex (inner) wall. Three types of channel are examined. These differ with respect to the section beyond the bend which is either long or short or short with a contraction. A close correlation between the characteristics of the q_w fields and the hydrodynamic effects is detected and explained. These effects comprise: separation and reattachment of the flow, secondary effects in the bend, the formation of an unclosed separation zone in the short outlet section, the localization of this zone when the outlet section includes a contraction, and specific gas dynamic effects near the intersection of the surfaces.Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 3, pp. 93–99, May–June, 1989.     

Acoustic resonance associated with vibrations of an array of plates in a subsonic flow

The acoustic resonance effect occurring in the vibrations of an array of profiles (cascade) in a gas flow has been studied by a number of authors [1–8]. Relying on assumptions of a heuristic nature [1, 2, 7, 8] and using rather crude models [4, 6], they have derived criteria governing the acoustic resonance regimes and given the effect a certain physical interpretation. However, many problems of a physical bearing with regard to the quantitative and qualitative principles of the effect have been left unresolved. For a more complete and rigorous solution of the problem the author has previously [9, 10] analyzed the natural modes of a gas flowing past an array of plates It was determined that in the array domain the vibrational modes of the gas are localized in the vicinity, of the array and the eigenvalues are determined by the characteristic dimensions of the interstitial channel (as an open resonator). Also, the eigenfrequences were determined for the gas in the flow plane with the array absent [9]. Under spatial periodic conditions, such that the flow in the plane can be considered as a certain model of flow in an annular duct, these eigenfrequencies concurred with those obtained earlier in [1, 2, 4–6]. The results of [9, 10] are used in the present study as a basis for investigating certain laws and relations governing the unsteady aerodynamic characteristics of arrayed profiles in or close to regimes such that the gas can execute natural vibrations in the array domain and in an annular duct in the absence of the array.Novosibirsk. Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 5, pp. 139–144, September–October, 1972.     

Acoustic,entropy, and vorticity perturbations in a channel of variable cross section

A study is made of the problem of the propagation of infinitesimally small perturbations in a gas stream moving in a channel of variable cross section when the flow cannot be regarded as isentropic and irrotational. The solution is found in the framework of the linear theory of the flow of an ideal gas and the quasi-one-dimensional hydraulic approximation for the steady regime. For irrotational and isentropic perturbations in a nozzle, this problem was considered in [1–4]. In [1], the problem is generalized to take into account entropy perturbations in the nozzle for the case of longitudinal oscillations. The present paper treats arbitrary modes in a nozzle and takes into account not only entropy but also vorticity perturbations in the moving stream. For each of the three perturbation types — acoustic, entropy, and vorticity — the solutions are expanded in series in cylindrical functions. It is shown that in the considered approximation each oscillation mode can be analyzed independently of the others. In the special case of flow in a Laval nozzle, the concept of impedance (admittance), which is widely used in acoustics, is generalized to take into account entropy and vorticity perturbations. The contribution to the flow dynamics of the acoustic, entropy, and vorticity perturbations is estimated numerically for longitudinal and transverse modes.Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 1, pp. 91–98, January–February, 1982.     

Experimental investigation of the recovery of the total pressure in a hypersonic wind tunnel with conical and profiled nozzles

Measurements have been made of the coefficient of recovery of the total pressure of a gas flow exhausting from axisymmetric and conical profiled hypersonic nozzles into a cylindrical channel of diameter equal to or greater than the nozzle exit and also in the presence of an Eiffel chamber. The experiments were made at Mach numbers M = 4.83–12.4 in the isentropic core. It is shown that the values of differ slightly (by 5%) from the corresponding value for a normal shock wave at the number M determined for a onedimensional flow by the ratio of the area of the cylindrical channel to the area of the critical section of the nozzle.Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 1, pp. 170–173, January–February, 1984.     

Flow of a conductive gas in a circular tube in a strong axiosymmetric magnetic field

The flow of a conductive gas along a channel in an external axiosymmetric magnetic field with a finite value of the magnetogasodynamic parameter N is examined. Numerical flow calculations are performed for a circular tube in such a field. Gas dynamic parameter fields, total pressure losses, and electric current intensities with the presence of transsonic zones and highly compressed regions are determined. Through comparison of the results obtained with linear theory data, the range of applicability of the latter is determined. Of the works dedicated to study of flow in external magnetic fields with N1, we should take note of [1], in which the process of entry of the gas into a transverse magnetic field was examined; [2], which studied one-dimensional transient motion with shock waves; and [3], where mixed flow in a Laval nozzle with an axiosymmetric homogeneous magnetic field was studied. Flow in a circular tube was examined in [4]; but the analysis performed by the characteristic method permitted calculation of only the initial supersonic flow zone. Motion in circular tubes in the presence of an axiosymmetric, magnetic field was studied in the linear formulation in [4, 5].Moscow. Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 5, pp. 145–155, September–October, 1972.     

Laminar boundary layer in axisymmetric swirling ducted gas flow

Several studies have been published [1–3] in which the authors solve the problem of the laminar boundary layer in an incompressible fluid on the walls of an axisymmetric duct in the presence of swirl in the outer flow. In [3], Loitsyanskii's parametric method of [4, 5], generalized to the case of three-dimensional flow, is used to solve this problem.In this article the parametric method for integrating the universal equations is extended to the solution of the problem of the laminar boundary layer on the wall of an axisymmetric channel in the case of swirling gas flow.     

Self-similar solution of the Navier-Stokes equations governing gas flows in rotary logarithmically spiral two-dimensional channels

A self-similar solution of the Navier-Stokes equations governing gas flows with constant transport coefficients in rotary log-spiral two-dimensional channels is obtained and analyzed. The solution and its existence depend on the following dimensionless parameters: the Reynolds number Re; the parameterM _o characterizing the channel rotation; the self-similarity parameters and responsible for the channel shape; the direction of channel rotation; and, finally, the wall temperature ratio. A numerical solution of the system of second-order ordinary differential equations gives the ranges of the governing parameters on which self-similar solutions for the gas flow in a rotary channel can exist.Perm'-Moscow. Translated from Izvestiya Rossiiskoi Akademii Nauk, Mekhanika Zhidkosti i Gaza, No. 6, pp. 44–50, November–December, 1995.     

Gas flow in a channel in the presence of distributed injection of the gas or of a combustible gas mixture from its walls

The distributed injection of gas or of a combustible gas mixture from the walls of a plane or an axisymmetric channel into a stream of inert gas flowing through the channel is analyzed. This problem is solved using models of an ideal incompressible liquid and an ideal gas to describe the motion in the injected gas and in the oncoming stream. Integral equations are obtained in the approximation of thin-layer equations without allowance for transverse pressure gradients, for the pressure in the channel, and in the case of injection without heat release; these are solved analytically by methods of operational calculus, while in the case of combustion of the injected mixture they are solved numerically. This allows one to find the appropriate form of the contact surface separating the injection region from the oncoming stream, the position of the flame front, and the distribution of the gasdynamic parameters. It turns out that with allowance for the compressibility of the gas of the oncoming stream or of the injected gas the flow can exist only over a finite section of the channel.Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 6, pp. 137–144, November–December, 1977.The author is grateful to V. A. Levin for constant attention to the work and helpful comments.     

Asymptotic solution to the problem of hypersonic flow over bodies in the neighborhood of the separation point of a thin shock layer

A study is made of the problem of hypersonic flow of an inviscid perfect gas over a convex body with continuously varying curvature. The solution is sought in the framework of the asymptotic theory of a strongly compressed gas [1–4] in the limit M when the specific heat ratio tends to 1. Under these assumptions, the disturbed flow is situated in a thin shock layer between the body and the shock wave. At the point where the pressure found by the Newton-Buseman formula vanishes there is separation of the flow and formation of a free layer next to the shock wave [1–4]. The singularity of the asymptotic expansions with respect to the parameter ₁ = ( –1)/( + 1) associated with separation of the strongly compressed layer has been investigated previously by various methods [3–9]. Local solutions to the problem valid in the neighborhood of the singularity have been obtained for some simple bodies [3–7]. Other solutions [7, 9] eliminate the singularity but do not give the transition solution entirely. In the present paper, an asymptotic solution describing the transition from the attached to the free layer is constructed for a fairly large class of flows.Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 1, pp. 99–105, January–February, 1982.     

Theoretical and experimental study of the structure of the wake behind a sphere in a supersonic gas flow at small reynolds numbers

Supersonic flow around a sphere by a viscous gas has been the subject of numerous articles [1–7]. In most of them, however, it is the behavior of the gasdynamic variables on the windward side of the sphere which has been studied. Here the main subject is the structure of the wake behind the body in a supersonic gas flow at small Reynolds numbers. Of existing experimental work on this subject we may note [7]. Theoretical calculations of the wake flow have been done in [4, 6], for example. Here we present the results of a combined theoretical and experimental investigation which allows us to evaluate the agreement between a solution of the complete Navier-Stokes system of equations and a real supersonic flow at Re 10².Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 4, pp. 46–51, July–August, 1978.In conclusion, the authors thank V. V. Lunev for useful discussion of the results.     

The turbulent boundary layer of dissociated gas in the initial section of a tube

Many theoretical and experimental papers [1–4] have been devoted to investigating the turbulent boundary layer in the initial section of a channel. For the most part, however, the flow of an incompressible fluid with constant parameters is considered. There are many practical cases in which it is of interest to treat the development of the turbulent boundary layer of gas in the initial section of a pipe when conditions are strongly nonisothermal. A solution of a problem of this type, based on the theory of limit laws, is given in paper [1]. The present article extends this solution to the case of the flow of a high-enthalpy gas when the effect of gas dissociation on the turbulent boundary layer characteristics must be taken into account. We shall consider the flow of a mixture of i gases which is in a frozen state inside the boundary layer, and in an equilibrium state on its boundaries. Formulas are derived for the laws of friction and heat exchange, and a solution is given for the turbulent boundary layer equations in the initial section of the pipe when the wall temperature is constant and the gas flows at a subsonic velocity.Finally the authors are grateful to S. S. Kutateladze for discussing the paper.     

Blowing into a supersonic stream through a permeable surface

Distributed blowing of gas into a supersonic stream from flat surfaces using an inviscid flow model was studied in [1–9]. A characteristic feature of flows of this type is the influence of the conditions specified on the trailing edge of the body on the complete upstream flow field [3–5]. This occurs because the pressure gradient that arises on the flat surface is induced by a blowing layer whose thickness in turn depends on the pressure distribution on the surface. The assumption of a thin blowing layer makes it possible to ignore the transverse pressure gradient in the layer and describe the flow of the blown gas by the approximate thin-layer equations [1–5]. In addition, at moderate Mach numbers of the exterior stream the flow in the blowing layer can be assumed to be incompressible [3]. In [7, 8] a solution was found to the problem of strong blowing of gas into a supersonic stream from the surface of a flat plate when the blowing velocity is constant along the length of the plate. In the present paper, a different blowing law is considered, in accordance with which the flow rate of the blown gas depends on the difference between the pressures on the surface over which the flow occurs and in the reservoir from which the gas is supplied. As in [8, 9], the solution is obtained analytically in the form of universal formulas applicable for any pressure specified on the trailing edge of the plate.Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 5, pp. 108–114, September–October, 1980.I thank V. A. Levin for suggesting the problem and assistance in the work.     

Nonisothermal flow of plasma in a plane MHD-channel

There is a large number of published papers (see the references given in the review [1]) in which various cases of the steady-state laminar flow of a conducting medium in a plane channel in the presence of a transverse magnetic field are considered. However, it has always been assumed that the transport coefficients were constants independent of the flow parameters such as the temperature. As a result, the dynamic and thermal problems were separable, and me temperature distribution had no effect on the dynamic flow parameters.In a low-temperature dense plasma, the conductivity is a very rapidly increasing function of temperature (it is approximately given by e^–A/T or T^10–13). It is clear that, in this case, it is necessary to take into account the fact that the transport coefficients are not constants, and the dynamic and thermal problems are not separable even for an incompressible fluid. We shall refer to such flows as nonisothermal, and contrast them with flows for which the transport coefficients are constants, and which we shall refer to as isothermal. for the sake of brevity.The importance of effects due to the nonisothermal nature of a flow was demonstrated in [2, 3], Hysteresis effects in friction and heat transfer, which were found in these papers, were discussed qualitatively in [4], Finally, the flow of a fluid with temperature-dependent conductivity in an MHD-channel was considered in [5] where it was. noted that the nonisothermal nature of the flow must be taken into account. In particular, the appearance of nonmonotonic velocity profiles with points of inflection was demonstrated [5], However, the latter paper included a number of conflicting assumptions. For example, when the propagation of heat was considered along the flow, it was assumed that the conductivity varied only across the channel. The temperature dependence of the conductivity used [5] was quite unrealistic, while the temperature dependence of viscosity and thermal conductivity was not taken into account at all.In the present paper we investigate the flow of plasma in a plane MHD-channel in the absence of a longitudinal flow of heat but with allowance for the temperature dependence of the transport coefficients. We shall use a more realistic form of the temperature dependence for the above parameters, and will take viscous energy dissipation into account.The authors are deeply indebted to M. V. Maslennikov and Yu. S. Sigov for valuable advice in connection with the numerical method of solution.     

Flow structure in motion of a spherical drop in a fluid medium at intermediate Reynolds numbers

The problem of flow of a viscous fluid around a spherical drop has been examined for the limiting case of small and large Reynolds numbers in several investigations (see [1–3], for instance; there is a detailed review of various approximate solutions in [4]). For the intermediate range of Reynolds numbers (approximately 1Re100), where numerical integration of the complete Navier-Stokes equations is necessary, there are solutions of special cases of the problem —flow of air around a solid sphere [5–7], a gas bubble [8, 9], and water drops [10]. The present paper deals with flow around a spherical drop at intermediate Reynolds numbers up to Re=200 for arbitrary values of the ratio of dynamic viscosities =₁/₂ inside and outside the drop. It is shown that a return flow can arise behind the drop in flow without separation. In such conditions the circulatory flow inside the drop breaks up. An approximate formula for the drag coefficient of the drop is given.Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 1, pp. 8–15, January–February, 1976.We thank L. A. Galin, G. I. Petrov, L. A. Chudov, and participants in the seminars led by them for useful discussions.     

Underexpanded wall jet in a cocurrent flow

The flow of a two-dimensional underexpanded wall jet flowing out of a sonic nozzle along a channel wall has been experimentally investigated. The dependence of the dimension of the first barrel of the jet on the underexpansion is obtained. It is shown that the flow of the jet in the channel is associated with a significant axial pressure gradient on the initial interval of the induced cocurrent flow and that this leads to a substantial change in the geometric dimensions of the jet.Translated from Izvestiya Rossiiskoi Akademii Nauk, Mekhanika Zhidkosti i Gaza, No. 1, pp. 196–199, January–February, 1993.