Abstract
The chapter presents the results of numerical simulation of two-dimensional laminar flows near a regular system of cylinders, forming a plane lattice perpendicular to the velocity vector of the oncoming supersonic flow. A multiblock computing technology is applied using local curvilinear grids adapted to the surface of bodies and having finite areas of overlap with a global rectangular grid. The viscous boundary layers are resolved on the local grids using Navier–Stokes equations. The interaction of shock-wave structures and aerodynamic wakes behind the elements of the lattice is described within Euler equations. With a sequential increase and decrease in Mach number of the oncoming flow, several rearrangements of the flow structure near the grid are found. A multiple hysteresis was revealed, which is expressed in the fact that the flow structure and aerodynamic loads on the lattice elements depend not only on Mach number but also on the history of its change.
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