Рассмотрены тройные конфигурации скачков уплотнения в сверхзвуковых потоках невязкого совершенного газа. Теоретически исследованы границы области существования ударно-волновых структур нового вида (тройных конфигураций с отрицательным углом наклона отраженного скачка, или отрицательных тройных конфигураций) на множестве параметров течения.

A parametric study of the features of the flow field of a plane and axisymmetric overexpanded ideal gas jet in the vicinity of the nozzle edge has been conducted over the entire theoretically admissible range of determining parameters (nozzle divergence angles, exhaust Mach numbers, jet incalculabilities, and gas adiabat indicators). The exhaust parameters that correspond to the extremes of the differential characteristics of a shockwave falling (descending) from the edge and the flow field behind it have been revealed. A significant difference in the character of changes in the characteristics of the shockwave and the flow field behind it depending on the type of symmetry of the gas jet has been found and studied.