F. A. Maksimov (Institute for Computer Aided Design of the Russian Academy of Sciences) :
Articles:
Maksimov F. A. (Institute for Computer Aided Design of the Russian Academy of Sciences)
doi: 10.18698/2309-3684-2025-1-5779
The results of calculations of the flow around two bodies located along the flow direction are presented. The results of experimental studies of the aerodynamic characteristics of the load-brake system are known. One of the interesting phenomena in this problem is the hysteresis of characteristics when the distance between the bodies changes. Multi-block computing technology is used using local curvilinear meshes adapted to the surface of bodies, having finite areas of overlap with a global rectangular mesh for the entire computational area. Viscous boundary layers are resolved on local grids using the Navier-Stokes equations, and the effects of aerodynamic interference of accompanying shock wave structures are described in terms of the Euler equations. In areas of mesh overlap, function interpolation is applied to the transition boundaries from one mesh to another. With the sequential displacement of one of the bodies with an increase or decrease in the distance between the bodies, a qualitative restructuring of the flow structure was discovered. The implemented flow pattern depends not only on the distance, but also on the flow regime in which the system was before changing the distance. The possibility of numerical modeling of the hysteresis of the aerodynamic properties of a system of two bodies depending on the distance between them is shown.
Максимов Ф.А. Численное моделирование гистерезиса при обтекании системы двух тел. Математическое моделирование и численные методы, 2025, № 1, с. 57–79.
533.6.011.5:533.6.011.72:519.6 Numerical simulation of hysteresis around a flat nozzle
Maksimov F. A. (Institute for Computer Aided Design of the Russian Academy of Sciences)
doi: 10.18698/2309-3684-2023-4-2746
The results of numerical simulation of two-dimensional plane laminar flows near two inclined plates forming a constricting nozzle along the velocity vector of an incoming supersonic perfect gas flow are presented. A multi-block computational technology is applied with the use of local curvilinear grids adapted to the surface of bodies, which have finite areas of overlap with a global rectangular grid for the entire computational domain. Viscous boundary layers are resolved on local grids using the Navier-Stokes equations, and the effects of aerodynamic interference of accompanying shock-wave structures are described in terms of the Euler equations. In areas of grid overlap, function interpolation is applied up to the boundaries of the transition from one grid to another. With a successive increase or decrease in the Mach number of the oncoming supersonic flow, a qualitative rearrangement of the flow structure near the nozzle is detected - either a detached shock wave and a subsonic flow zone in front of the nozzle, or oblique shocks near inclined plates are formed. A hysteresis is revealed, which is expressed in the fact that in a certain range of Mach numbers, the flow structure and the aerodynamic load on the nozzle depend not only on the value, but also on the prehistory of the change in the Mach number. The possibility of changing the flow structure by introducing a density inhomogeneity into the oncoming flow is shown.
Максимов Ф.А. Численное моделирование гистерезиса при обтекании плоского сопла. Математическое моделирование и численные методы, 2023, № 4,с. 27–46.
Maksimov F. A. (Institute for Computer Aided Design of the Russian Academy of Sciences), Syzranova N. G. (Institute for Computer Aided Design of the Russian Academy of Sciences), Andrushchenko V. A. (Institute for Computer Aided Design of the Russian Academy of Sciences)
doi: 10.18698/2309-3684-2024-4-93110
Using methods of mathematical modeling and numerical calculations, the features of the motion of small space bodies – meteoroids during their flight in dense layers of the atmosphere, when they oscillate around their center of mass even with a slight deviation of their shape from the "correct" one, are studied. The influence of oscillatory motion on trajectory parameters is studied: velocity, angle of inclination of the trajectory to the Earth's surface, velocity pressure, etc. Options are also considered for cases where the center of mass of the meteoroid does not coincide with its geometric center. Previously, similar studies on asymmetric flow were conducted for descent spacecraft (landers), but for meteoroids, much larger irregularly shaped objects falling in the atmosphere at super-hypersonic speeds, unlike artificial structures with very different densities of their materials, such calculations were not carried out.
Максимов Ф.А., Сызранова Н.Г., Андрущенко В.А. Моделирование полета метеороидов в атмосфере Земли, сопровождаемого их колебательным движением. Математическое моделирование и численные методы, 2024, № 4, с. 93–110.
5 Problem solution of aerodynamic design using multiprocessor computers
Bratchev A. V., Dubrovina A. Y., Kotenev V. P. (Bauman Moscow State Technical University), Maksimov F. A. (Institute for Computer Aided Design of the Russian Academy of Sciences), Shevelev Y. D. (Institute for Computer Aided Design of the Russian Academy of Sciences)
doi: 10.18698/2309-3684-2015-1-1730
The article discusses a method for constructing an aircraft geometric shape for computing the parameters of aerogasdynamic flow as well as a method of meshing near the model to simulate the flow within the Navier–Stokes equations in the thin layer approximation. The results of the flow simulation are given. The calculations were performed on a multiprocessor computer system.
Bratchev A., Dubrovina A., Kotenev V., Maksimov F., Shevelev Y. Problem solution of aerodynamic design using multiprocessor computers. Маthematical Modeling and Coтputational Methods, 2015, №1 (5), pp. 17-30
533.6.07 Supersonic flow in axisymmetric channel
Maksimov F. A. (Institute for Computer Aided Design of the Russian Academy of Sciences)
doi: 10.18698/2309-3684-2015-1-109120
The supersonic flows are implemented in an axisymmetric channel in many technical devices. These flows are in an expanding part of the nozzle or in the working part of supersonic wind tunnel. The method of supersonic flow calculation in an axisymmetric channel is developed. The method is based on the construction of multi-block axisymmetric grid and linearization of boundary conditions on the aerodynamic surfaces. Testing the method has showed good agreement with known experimental data. The method allows predicting the aerodynamic properties of the aerodynamic form, depending on its location in the channel, as well as the effect of the aerodynamic form on the channel walls in the channel.
Maksimov F. Supersonic flow in axisymmetric channel. Маthematical Modeling and Coтputational Methods, 2015, №1 (5), pp. 109-120