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)

FLAT NOZZLE, SHOCK-WAVE STRUCTURES, AERODYNAMIC CHARACTERISTICS, HYSTERESIS, FLOW STRUCTURE CONTROL


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.


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Максимов Ф.А. Численное моделирование гистерезиса при обтекании плоского сопла. Математическое моделирование и численные методы, 2023, № 4,с. 27–46.



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