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Lipatov I.I.,Zhukovskii Central Institute of Aerohydrodynamics | Liapidevskii V.Y.,Russian Academy of Sciences | Chesnokov A.A.,Russian Academy of Sciences
Doklady Physics | Year: 2016

A mathematical unsteady pseudoshock model describing the continuous transition from supersonic to subsonic flow is constructed for a barotropic gas flow in a long flat channel or a nozzle. The model is based on a two-layer scheme of flow with mass transfer including a potential supersonic core and a turbulent boundary layer. © 2016, Pleiades Publishing, Ltd.


Kashevarov A.V.,Zhukovskii Central Institute of Aerohydrodynamics
High Temperature | Year: 2012

The characteristics of a spherical probe have been calculated in collisional plasma at rest where the ionization of atoms of an alkali additive and recombination of generated charged particles with consider-ation for the instability of plasma temperature around the probe occur. The results evidence a strong reduc-tion of the probe current and impairment of agreement between the probe and the spectral measurements of concentration of charged particles. It is concluded that it is necessary to analyze the detailed chemical kinet-ics of the multicomponent gaseous mixture around the probe. © Pleiades Publishing, Ltd., 2012.


Egorov I.V.,Zhukovskii Central Institute of Aerohydrodynamics | Pal'chekovskaya N.V.,Zhukovskii Central Institute of Aerohydrodynamics | Shvedchenko V.V.,Zhukovskii Central Institute of Aerohydrodynamics
High Temperature | Year: 2015

The dependence of perturbations of pressure and heat flux to the surface of blunt bodies (cylinder, ellipse, and sphere) on the period of spatial perturbations of a supersonic flow has been studied numerically for different Reynolds numbers. It is shown that small perturbations of velocity, temperature, or density of the incoming flow can lead to significant perturbations of the heat flux to the surface of the body while the pressure perturbations remain insignificant. With an increase in the Reynolds number and radius of curvature (i.e., for blunter bodies), the level of heat flux perturbations significantly increases. © 2015, Pleiades Publishing, Ltd.


Kiselev A.F.,Zhukovskii Central Institute of Aerohydrodynamics | Sboev D.S.,Zhukovskii Central Institute of Aerohydrodynamics | Chernyshev S.L.,Zhukovskii Central Institute of Aerohydrodynamics
Doklady Physics | Year: 2014

The problem of description of the laminar-turbulent transition in a three dimensional boundary layer, for example, in the boundary layer on swept wings, is of great applied importance for the perfection of aviation technical equipment. Tests in industrial wind tunnels (WT) are usually carried out at a degree of turbulence of incident flow exceeding that in atmosphere. The observed features of the laminar-turbulent transition under conditions of the increased degree of external turbulence on a swept wing are also explained by the presence of disturbances of different types at the boundary layer in addition to the unstable crossflow disturbances. These are the so-called streaky structures excited by the localized vortex disturbances of the external flow in both the two-dimensional and three-dimensional boundary layers.


Golikov A.A.,Zhukovskii Central Institute of Aerohydrodynamics | Demeshkina V.V.,Zhukovskii Central Institute of Aerohydrodynamics | Leutin A.P.,Zhukovskii Central Institute of Aerohydrodynamics | Filat'Ev A.S.,Zhukovskii Central Institute of Aerohydrodynamics
Doklady Physics | Year: 2010

The structure of unguided spatial reentry with sub-circular velocities, which determines ground impact points, was investigated. Peculiarities of unguided reentry with subcircular velocities are theoretically studied by the averaging method. The body motion equation set is used in the form for the direction cosine matrix with the optimal correction by normalization conditions. Simulation results with various simplifications including an analytical evaluation and the Runge method with different integration steps were compared to control the accuracy. In an effort to improve the method, the calculations were fulfilled for a typical body of the axisymmetric cylindrical layout with the length-to-diameter ratio of 9, a conic dulled nose, and a nozzle in the tail. The physical nature of the phenomenon suggests possible directions of NSGIP reduction by means of aerodynamic destabilization of angular motion up to the ground impact and the change of the initial trajectory conditions.

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