A5051943368- Computational Fluid Dynamics and Aerodynamics
- Gas Dynamics and Kinetic Theory
- Fluid Dynamics and Turbulent Flows
- Plasma and Flow Control in Aerodynamics
- Aerodynamics and Acoustics in Jet Flows
- Laser-Plasma Interactions and Diagnostics
- Combustion and flame dynamics
- Meteorological Phenomena and Simulations
- Particle Dynamics in Fluid Flows
- Rocket and propulsion systems research
- Radiative Heat Transfer Studies
- Combustion and Detonation Processes
- Aquatic and Environmental Studies
- Wind and Air Flow Studies
- Acoustic Wave Phenomena Research
- Fluid Dynamics and Vibration Analysis
- Distributed and Parallel Computing Systems
- Laser-induced spectroscopy and plasma
- Astro and Planetary Science
Institute of Theoretical and Applied Mechanics
2015-2024
Novosibirsk State University
2014-2017
Russian Academy of Sciences
2001-2011
Siberian Branch of the Russian Academy of Sciences
2011
Tohoku University
2011
Université de Sherbrooke
2011
The theoretical study and experimental investigation of the reflection asymmetric shock waves in steady flows reported by Li et al. (1999) are complemented a numerical simulation. All findings both were also evident In addition to weak regular Mach wave configurations, strong inverse-Mach configurations recorded numerically. hysteresis phenomenon, which was hypothesized course then verified investigation, observed
The present paper describes HyCFS code, developed for numerical simulation of compressible high-speed flows on hybrid CPU/GPU (Central Processing Unit / Graphical Unit) computational clusters the basis full unsteady Navier-Stokes equations, using modern shock capturing high-order TVD (Total Variation Diminishing) and WENO (Weighted Essentially Non-Oscillatory) schemes general curvilinear structured grids. We discuss specific features architecture details program implementation results code...
Introduction TWO shock-wave-reection con gurations, regular re ection (RR) andMach (MR), are possible in steady ows.1 The RR and the MR consist of two three shock waves, respectively.Two extreme angles incidence associatedwith oblique a wave. They von Neumann A detachment AD (AD >AN ). For given ow Mach number, is smallest angle for which an theoretically possible, largest possible. Consequently, impossible . incident range ·A both andMR RR$MR transition could take place at any inside...
The influence of viscosity on the Mach reflection shock waves in a steady flow monatomic gas is studied by solving Navier–Stokes equations numerically. Based nested block grid refinement technique, near wave intersection simulated, and its behaviour with increasing Reynolds number studied. computations are performed for interaction both strong (free-stream $M_\infty = 4$ ) weak ( 1.7$ waves. In at all numbers examined range, it found that there exists small-size zone behind where parameters...
Experiments on the transition between steady regular and Mach reflections of shock waves have been performed in a low-noise wind tunnel. Owing to very low level free-stream disturbances inherent this facility, hysteresis phenomenon has observed close agreement with theoretical predictions results previous numerical simulations. When increasing incident wave angle, reflection persists most dual solution domain. Thus, detachment criterion can be considered as true one for from reflection, an...
The linear stability theory is used to investigate the emergence, in supersonic free shear flows such as mixing layers and fully expanded plane jets, of supersonically travelling instability waves, which do not vanish ambient space. It shown that, at convective Mach numbers, slow fast modes layer well sinuous mode jet should lead wave radiation. Direct numerical simulations are further study nonlinear stages development high-speed jets. They have that formation oblique shock waves attached...
The major points in the development of parallel multiplatform multipurpose numerical code solving full unsteady Navier–Stokes equations are presented. developed is primarily designed for running on multi-GPU computational devices but can also be used traditional multicore CPUs and even manycore processors such as Intel Xeon Phi. Physical models include calorically perfect inert gas, single- multi-temperature approaches chemically reactive flows an Euler–Euler model gas-particle suspensions....
The results of three-dimensional numerical simulations the interaction plane N-wave propagating at an angle to free stream in transverse direction with sharp and blunted leading edges plate a supersonic flow are presented. Interaction weak shock attached edge causes corrugation wave surface that propagates downstream. A steady pressure perturbation is also formed inside boundary layer close Mach angle. This curving streamlines generation quasi-steady vorticity disturbance. In case impinging...
Development of disturbances in the supersonic boundary layer on sharp and blunted cones is studied both experimentally theoretically. The experiments were conducted at Transit-M hypersonic wind tunnel Institute Theoretical Applied Mechanics. Linear stability calculations use basic flow profiles provided by numerical simulations performed solving Navier-Stokes equations with ANSYS Fluent in-house CFS3D code. Both global pseudospectral Chebyshev method local iteration procedure are employed to...