Hypersonic flow past a supersonic two-phase source

The interaction of a uniform hypersonic gas flow with a supersonic two-phase gas-particle source is considered. In the symmetry-axis neighborhood between the bow and termination shock waves, an approximate analytical solution for the carrier-phase parameters is found. On the basis of parametric numerical calculations, the behavior of the particle trajectories and the concentration distribution in the shock layers are studied for both continuum and free-molecule flow regimes around the particles. The appearance of regions with multiple intersections of the particle trajectories and the formation of "layer structures" in the particle concentration distributions (particle accumulation regions near the envelopes of the particle trajectories) are indicated. The dependence of the number of the high concentration layers on the governing parameters is studied. Moscow. Translated from Izvestiya Rossiiskoi Akademii Nauk, Mekhanika Zhidkosti i Gaza, No. 3, pp. 134–147, May–June, 1998. The work received financial support from the Russian Foundation for Basic Research (project No. 96-01-00313) and the National Foundation for Natural Sciences of China (joint RFBR-NFNS grant No.96-01-00017c).     

Hypersonic flow past conical bodies

In [1, 2] Gonor considered the problem of imperfect inviscid gas flow about conical bodies at high supersonic speeds. The method of expansion in terms of a small parameter was used to obtain the solution. The small parameter used was the ratio of the densities in the free stream and behind the shock wave. However, this solution does not enable one to determine the velocity field in the vicinity of the cone surface.In the present paper, this problem is solved by the method described in [3], based on the use of the Poincaré-Lighthill-Ho method. The zero approximation is obtained, which is suitable throughout the entire flow region including the vortical layer. Outside of this layer, the solution transforms to the Gonor solution [1, 2].The author wishes to thank B. M. Bulakha for discussing the paper.     

Base pressure of bodies of revolution when gas is blown through their surface into a supersonic flow

One of the most important problems of high-velocity aerodynamics is the investigation of the base pressure and the wake flow behind bodies of revolution under the conditions of surface mass transfer. The present paper reports careful experimental investigations of the flow past bodies of revolution in the presence on their surface of a transverse mass flux, especially at a low blowing intensity. These investigations have yielded new data on the dependence of the base pressure on the main determining parameters, extending and making more accurate the modern picture of the mechanism by which surface mass transfer influences the base pressure and its connection with the state of the boundary layer.     

Hypersonic flow past a plate of finite length

Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 5, pp. 66–73, September–October, 1991.     

Hypersonic flow past a flat-plate/beveled-whistle system

The results of an experimental and numerical investigation of unsteady hypersonic nitrogen flow (M_∞ = 21 and the unit Reynolds number Re_∞1 = 6×10⁵ m^?1) past an integrated flat-plate/beveled whistle model are presented. The calculations using the ANSYS Fluent package are carried out for different geometries of the whistle cavity and angles of incidence of the model. The conditions under which fluctuations occur in the whistle are determined and the fields of the mean flow and fluctuations in the shock layer on the plate are obtained. In the experiments performed in the T-327A hypersonic nitrogen wind tunnel of the Institute of Theoretical and Applied Mechanics of the Siberian Branch of the Russian Academy of Sciences the dependence of the pressure fluctuations on the plate surface on the angle of attack of the model are obtained. The calculated and measured results are compared.     

Hypersonic flow past blunt-edged delta wings

A method is proposed for calculating hypersonic ideal-gas flow past blunt-edged delta wings with aspect ratios = 100–200. Systematic wing flow calculations are carried out on the intervals 6 M 20, 0 20, 60 80; the results are analyzed in terms of hypersonic similarity parameters.Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 5, pp. 175–179, September–October, 1990.     

Hypersonic flow past conical V-shaped wings

Hypersonic flow past delta wings with a V-shaped cross-section has been investigated both theoretically and experimentally. Much attention is given to the examination and classification of possible conical flow patterns in the vicinity of the windward surface using the thin shock layer method. Solutions for shocks both attached to and detached from the leading edges them are obtained. It is shown that qualitatively new flow patterns can appear in the flow past V-shaped wings as compared with the case of a planar wing.Moscow. Translated from Izvestiya Rossiiskoi Akademii Nauk, Mekhanika Zhidkosti i Gaza, No. 5, pp. 170–178, September–October, 1996.     

Slow visco-elastic flow past a cylinder in a rectangular channel

This paper is concerned with the flow of a visco-elastic liquid through a rectangular channel containing a cylindrical obstruction placed either in a symmetric or asymmetric position with respect to the centre of the channel. Numerical predictions of the flow are obtained using a well established finite element Galerkin mixed formulation. The influence of elasticity on the streamline pattern is found to be negligible, and one only observes changes due to different geometries, i.e. relative positions of cylinder and channel. However, both elasticity and a variable viscosity are found to have significant effects on the forces exerted on the cylinder.     

Hypersonic flow past ducted blunt bodies of revolution

Chernyi [1, 2] has examined the problem of hypersonic flow past a ducted cone with sharp leading edge. In the following we present an analysis of the characteristic features of this problem in the case of a blunt leading edge. We use hypersonic theory for flow past slender bodies with nose blunting of relatively small dimensions [1, 3, 4], based on replacing the nose by a concentrated force and use of the nonsteady analogy. It has been shown in [4, 5] that within the framework of this theory the effect of the violation of the law of plane sections and also the effect of the chemical and physical transformations of the gas in the high-entropy layer is qualitatively equivalent to a change in the drag coefficient of the nose. This approach makes it possible to establish useful similarity laws. The development of these ideas in the direction of the study of the flow structure behind the bow shock wave and analysis of the parameters defining this structure is given in [6–8] in which, in particular, the role of the entropy distribution with respect to the streamlines in the transitional section between the nose and the side surface was clarified and the important practical empirical result was established that this distribution is universal for noses of any form for given flow conditions. In the following these results are extended to blunt bodies of revolution with a duct in the nose. We examine the flow region which is external to the duct under the assumption that the external flow regime corresponds to maximum flow rate through the duct. A characteristic feature of the problem is associated with the additional characteristic linear dimension r₀, which determines the gas mass lost through the duct.     

Blowing coefficient with arbitrary variation of the mass flow rate of the blown gas past a body around which flows a stream with an exponential change in the velocity

Formulas are derived permitting calculation of the linear corrections to the friction and heat-transfer coefficients with the blowing into the boundary layer of different gases, in small amounts but with a mass flow rate varying arbitrarily along the body. The case of a Mach number equal to zero and a temperature factor equal to unity was studied. Here it is postulated that bringing the relative heat-transfer coefficient down to a dependence on the dimensionless blowing renders possible, as with blowing which permits a self-similar solution, the use of the results obtained for arbitrary values of these parameters [1]. The proposed method of solution is based on the application, in the linear approximation, of a Duhamel integral for an arbitrary law of change in the mass flow rate along the body, if a solution is known with a discontinuous change in the mass flow rate. For a discontinuous change in the mass flow rate, the solution is sought using a Laplace transform; in this sense, the proposed method is similar to the method of [5].Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 4, pp. 55–63, July–August, 1970.