Add to ORKGAbstract: The results of numerical simulation of supersonic flow in the wing wake and its interaction with shock waves investigation are presented. The system of couple counter wedges with a sharp edge has been used for the formation of shock waves of varying intensity. Investigation of regular and Mach interaction of shock waves has been performed. Calculations have been performed on a multiprocessor computer system K-100 in KIAM RAS. Experiments were carried out in a supersonic wind tunnel T–325 (ITAM SB RAS) at the Mach number 3.Note: Research direction:Mathematical modelling in actual problems of science and technic
The general purpose of this study is the development of a numerical simulation model of the reflecti...
Wave drag and shock induced boundary layer separation are important issues of flows around transonic...
Abstract:- The work to be presented herein is a Computational Fluid Dynamics analysis of flow over a...
This paper examines the Shock/Shock Interactions (SSI) between the body and wing of aircraft in supe...
Abstract: The structure of a supersonic vortex and its features depending on the Mach numb...
Abstract: In this paper we present a wingtip vortex numerical study in the supersonic regi...
Abstract: A series of numerical and experimental studies was performed to reveal the flow ...
This work is motivated by the need of the development of improved numerical tools to investigate the...
The desire to reduce or eliminate the operational restrictions of supersonic aircraft over populated...
The supersonic biplane is well known for the airfoil which has zero wave drag at the supersonic spee...
This study investigates the flowfield patterns and distributions of surface heat flux due to interac...
Supersonic flow around the system of bodies (lattice wings, a wing near the shielding surface, blade...
With the help of mathematical modeling methods we studied the evolution of whirl structures moving i...
During flights at high velocities, locally, a supersonic flow regime is formed above wings. The supe...
The interaction of a concentrated vortex with a shock wave may occur in many instances in the operat...
The general purpose of this study is the development of a numerical simulation model of the reflecti...
Wave drag and shock induced boundary layer separation are important issues of flows around transonic...
Abstract:- The work to be presented herein is a Computational Fluid Dynamics analysis of flow over a...
This paper examines the Shock/Shock Interactions (SSI) between the body and wing of aircraft in supe...
Abstract: The structure of a supersonic vortex and its features depending on the Mach numb...
Abstract: In this paper we present a wingtip vortex numerical study in the supersonic regi...
Abstract: A series of numerical and experimental studies was performed to reveal the flow ...
This work is motivated by the need of the development of improved numerical tools to investigate the...
The desire to reduce or eliminate the operational restrictions of supersonic aircraft over populated...
The supersonic biplane is well known for the airfoil which has zero wave drag at the supersonic spee...
This study investigates the flowfield patterns and distributions of surface heat flux due to interac...
Supersonic flow around the system of bodies (lattice wings, a wing near the shielding surface, blade...
With the help of mathematical modeling methods we studied the evolution of whirl structures moving i...
During flights at high velocities, locally, a supersonic flow regime is formed above wings. The supe...
The interaction of a concentrated vortex with a shock wave may occur in many instances in the operat...
The general purpose of this study is the development of a numerical simulation model of the reflecti...
Wave drag and shock induced boundary layer separation are important issues of flows around transonic...
Abstract:- The work to be presented herein is a Computational Fluid Dynamics analysis of flow over a...