Using a conical nozzle as an example, the gas-dynamic and thrust characteristics of high-altitude nozzles are studied in a wide range of atmospheric pressures. A geometric model of the nozzle block and the computational domain is developed in a two-dimensional axisymmetric formulation. A calculation was carried out with setting the parameters of the standard atmosphere in the altitude range from 0 to 80 km. In one of the parts of this work, the most common shock-wave structures (triple configurations of shock waves) that arise during flights at supersonic and high supersonic speeds are considered, during jet outflows from propulsion systems. We also studied the influence of the extreme values of the discontinuities of the flow field parameters on the transmitted electromagnetic signals.

This paper covers the use of gas-permeable materials as the outer surface of a high-speed aircraft. The gas-dynamic structures of supersonic flows are compared in the presence of blowing from the body surface and in its absence. The influence of the blowing speed on the structure of the formed gas-dynamic discontinuities is determined.

The development of a reusable launch system is one of the most promising directions in the development of cosmonautics. World rocket companies are striving to create a space vehicle with improved tactical and technical characteristics. The main task is to ensure the most efficient flight mode of the reusable spacecraft from the point of view of the full load of the injection system. Since the main costs are spent on transporting the fuel of the rocket and its own design, the developers strive to fully load such a system not only when sending into orbit, but also when returning back. The implementation of the idea of a reusable spacecraft entails large energy losses, which suggests the idea of creating a single-stage reusable launch system.

Supersonic non-isobaric jet outflow was studied under conditions of interaction with the slipstream. Multilevel mathematical model was compiled making it possible to analyze structure of the gas-dynamic flow in the vicinity of the nozzle channel central body at the aircraft take-off path (0...10 km). Multilevel approach to calculating thrust parameters of the nozzle channel with central body requires development of a physical and mathematical model of the non-stationary interdependent processes that characterize operation of the “aircraft – nozzle cluster – jet” system as a whole. At the same time, it is necessary to form mathematical models of the processes for different degrees of the task detailing, i.e. within each scale of the task (micro-, meso- and macro-scale). Mathematical model includes calculation of the aircraft traction characteristics, study of the interaction features between the jet, the central body and the slipstream.

The problem of jet flow through the critical section of a nozzle with a central wedge-shaped body with subsequent interaction of the jet with the wall of the central body and the flow of co-current atmospheric air is considered. The structure of the gas-dynamic flow in the vicinity of the central body of the nozzle channel at the control points of the altitude range of the flight of the aircraft is investigated.