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50 results on '"Mazhul', I. I."'

9. Asymmetry of a Flow Which is Due to the Interaction of a Compression Shock with the Boundary Layer on a Longitudinally Ribbed Surface.

Author

Mazhul', I. I.

Subjects
*BOUNDARY layer (Aerodynamics), *MACH number, *NAVIER-Stokes equations, *FLUID flow, *FLOW velocity, *FLUID-structure interaction, *COMPRESSION loads
Abstract

Numerical investigations of the asymmetry of a fluid flow in the channel of an air intake which is due to the interaction of a compression shock, generated by the shell ring of the air-intake channel, with the boundary layer on the longitudinally ribbed lower surface of this channel have been performed on the basis of the Reynolds-averaged Navier–Stokes equations and the SST k–ω model of turbulence. Data on the structure of the fluid flow in such a channel with a narrowing inlet part and a next part of constant cross section, the limiting flow lines on the longitudinally ribbed lower surface of the channel, and the profiles of the velocity of the flow and the total pressure in the boundary layer in the channel have been obtained for the case where the Mach number of the fluid flow incoming to the channel is M = 4. [ABSTRACT FROM AUTHOR]

Published
2023
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37. Numerical modeling of three-dimensional separated flow at the initial section of a rectangular air inlet.

Author

Mazhul, I. I., Fomin, Vasily, and Shiplyuk, Alexander

Subjects
*FLOW separation, *THREE-dimensional flow, *MACH number, *SUPERSONIC flow, *NAVIER-Stokes equations, *BOUNDARY layer equations, *TURBULENT boundary layer
Abstract

Basing on the solution of the Navier-Stokes equations and using the k-ω SST turbulence model, a numerical simulation of the supersonic flow in an air intake with an internal channel of a rectangular cross section was performed for the case when the shock wave generated by the inlet cowl interacted with the turbulent boundary layer on the inner surfaces of the channel. The three-dimensional configuration consisted of a convergent entrance section and a throat of a constant cross-sectional area is considered. Flow parameters at the entrance of the air intake were set taking into account the boundary layer developing on a pre-compression surface of an aircraft in front of the inlet. Two variants of the internal channel geometry were considered: firstly, when the lower surface of the channel was plane and, secondly, when this surface was arranged with longitudinal ribs. Numerical simulation of the three-dimensional flow was performed at the free-stream Mach number M = 4. [ABSTRACT FROM AUTHOR]

Published
2020
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43. Gasdynamic and Turbulent Features of Flows with a Pseudo-Shock Wave in Axisymmetric Ducts.

Author

Gounko, Yu. P. and Mazhul, I. I.

Abstract

Numerical computations for studying the supersonic flows with a pseudo-shock wave were fulfilled. There was considered an axisymmetric duct including a funnel-shaped inlet, a throat section, a lengthened diffuser, and an outlet throttling section; the freestream flow with a Mach number M = 6 in front of the inlet was preset. There were applied the solvers including the Reynolds-averaged Navier-Stokes code and k-ω SST turbulence model for axisymmetric flows. The main subject of the investigation was determination of effects of the diffuser opening angle θd and the throttling level on forming the flow, gasdynamic and turbulent characteristics of the pseudo-shock wave. Data on variation of the turbulence viscosity along the duct length have shown the possibility of determination of the pseudo-shock wave termination in the diverging ducts instead of the usual method of determination of the pseudo-shock wave length by the distribution of the static pressure along the duct wall which is suitable just only for the non-diverging ducts. [ABSTRACT FROM AUTHOR]

Published
2018
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