The phenomenon of turbulent boundary layer separations from the wall of the channel (nozzle) in the supersonic viscous gas flow is numerically investigated. Computational research is used for studying the conditions of realization of restricted shock separation and free shock separation in nozzles, and hysteresis when changing the type of separation in the phases of increasing and reducing the pressure drop across the nozzle. The issues of control of separation in the nozzle are considered; in particular, we study the impact of the implementation of this or that type of separation. A numerical simulation of turbulent flows in plane nozzles with small geometric expansion is performed. Symmetrical and asymmetrical flow separations from the walls in the supersonic part of the nozzle are investigated.
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