Three-dimensional hypersonic gas flow over wings

The results of the theory of three-dimensionai hypersonic flow over a wing based on the use of the thin shock layer method are reviewed.Based on paper read at the Seventh Congress on Theoretical and Applied Mechanics, Moscow, August 1991. Presented by V. Ya. Neiland.Translated from Izvestiya Rossiiskoi Akademii Nauk, Mekhanika Zhidkosti i Gaza, No.5, pp. 148–161, September–October, 1992.     

Rheology of rarefied gas flow in hypersonic shock and boundary layers

Using the Maxwell method, transfer equations describing molecular gas flows in viscous shock and hypersonic boundary layers are obtained. It is shown that, in contrast to the Navier-Stokes approximation, the kinetic model proposed makes it possible correctly to describe hypersonic flow around bodies under conditions of strong nonequilibrium of the internal and translational degrees of freedom of the gas particles.     

Investigation of hypersonic flow of rarefied gas past wings of infinite span

In the framework of the locally self-similar approximation of the Navier-Stokes equations an investigation is made of the flow of homogeneous gas in a hypersonic viscous shock layer, including the transition region through the shock wave, on wings of infinite span with rounded leading edge. The neighborhood of the stagnation line is considered. The boundary conditions, which take into account blowing or suction of gas, are specified on the surface of the body and in the undisturbed flow. A method of numerical solution of the problem proposed by Gershbein and Kolesnikov [1] and generalized to the case of flow past wings at different angles of slip is used. A solution to the problem is found in a wide range of variation of the Reynolds numbers, the blowing (suction) parameter, and the angle of slip. Flow past wings with rounded leading edge at different angles of slip has been investigated earlier only in the framework of the boundary layer equations (see, for example, [2], which gives a brief review of early studies) or a hypersonic viscous shock layer [3].Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 3, pp. 150–154, May–June, 1984.     

Relaxation processes in hypersonic rarefied binary gas mixture flow around a cylinder

Using the direct simulation Monte Carlo method, the hypersonic flow of a binary gas mixture around a cylinder is investigated over a wide rarefaction range: from an almost continuum regime (at the Knudsen number Kn = 0.01) to free-molecular flow. The effect of a small admixture of heavy diatomic particles in a light gas flow on the relaxation processes near the cylinder and the heat flux is studied.     

Influence of nonequilibrium radiation on rarefied gas flow around blunt bodies

The hypersonic nonequilibrium rarefied gas flow is investigated in the neighborhood of the stagnation streamline ahead of a blunt body by taking into account nonequilibrium radiation due to electron excitation for air and carbon dioxide. The analysis is on the basis of a numerical solution of the Navier—Stokes equations simplified under the assumption of local self-similarity of the flow with the Shockwave structure taken into account. It is shown that at low densities, when the shock wave and shock layer thicknesses are of the same order of magnitudes, the two-layer Cheng model becomes inapplicable in the presence of radiation. In this case, the governing process is diffusion of the electronically excited molecules from the shock layer into the forward part of the shock front. The mechanism of the formation of a second luminous plateau on the diagram of the nonequilibrium radiation intensity density is discussed. The combined influence of the limit in collisions and the diffusion transport processes on the intensity of molecular band radiation is considered.Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 6, pp. 81–87, November–December, 1974.The author is grateful to V. V. Lunev for discussion and remarks during performance of the research.     

Nonequilibrium hypersonic flow of carbon dioxide gas over blunt bodies

The Navier-Stokes equations are used to investigate hypersonic flow of carbon dioxide gas over blunt bodies with allowance for nonequilibrium development of chemical reactions and vibrational relaxation of the CO₂ molecules. The problem is solved by the method of stabilization by means of an implicit difference scheme that includes the use of Newton's iterative process. The results are given of calculations of the flow field, the convective heat flux, and the frictional stresses on the surface of blunt cones with spherical noses. The influence of admixtures on the flow field and the heat fluxes is investigated. The results of the calculations are compared with the locally self-similar solution for the neighborhood of the front stagnation point.Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 5, pp. 199–202, September–October, 1979.     

Asymptotic solutions of the thin viscous shock layer equations near the symmetry plane of blunt bodies in hypersonic rarefied gas flow

The hypersonic rarefied gas flow over blunt bodies near the symmetry plane is investigated for the regime transitional from continuum to free-molecular. Three rarefied gas flow regimes are considered depending on the relationship between the determining parameters of the problem. For all regimes, at small Reynolds numbers, asymptotic solutions of the thin viscous shock layer equations near the symmetry plane of blunt bodies are obtained in the form of simple analytical expressions for the heat transfer, skin friction and pressure coefficients as functions of the gas-dynamic parameters of the free-stream flow and the geometric parameters and temperature of the body. With decrease in the Reynolds number these coefficients approach their values in free-molecular flow (with the accommodation coefficient equal to unity). From comparison with the data calculated using the direct simulation Monte Carlo method, the accuracy and applicability limits of the analytical solution are estimated.     

Use of a three-component model to compute gas suspension flow and rarefied flow over bodies

Translated from Zhurnal Prikladnoi Mekhaniki i Tekhnicheskoi Fiziki, No. 1, pp. 39–42, January–February, 1991.     

Nonequilibrium ionization accompanying hypersonic flow of carbon dioxide gas over blunt bodies

A study is made of the nonequilibrium ionization in the shock layer when carbon dioxide gas flows over cones with spherical noses at velocity 4–7 km/sec, the density of the oncoming flow being 10^–8-10^–5 g/cm³. The influence of admixtures of nitrogen and sodium on the electron concentration is investigated.Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 1, pp. 183–186, January–February, 1981.     

Investigation of aerodynamic characteristics of a hypersonic flow around bodies of revolution with a permeable tip

Results of experimental investigations of aerodynamic characteristics of models of high-velocity flying vehicles consisting of a combination of a blunt cone, a cylinder, and a conical tail fin are presented. The model forebody is cooled by porous blowing. The choice of such a configuration is determined by the necessity of optimizing the arrangement of high-velocity flying vehicles on the launcher and their aerodynamic characteristics under conditions of intense surface mass transfer (decrease in drag and heat transfer and increase in static and dynamic stability). __________ Translated from Prikladnaya Mekhanika i Tekhnicheskaya Fizika, Vol. 48, No. 2, pp. 19–26, March–April, 2007.