ДОСЛІДЖЕННЯ ПАРАМЕТРІВ І ХАРАКТЕРИСТИК ОСЕСИМЕТРИЧНОГО НАДЗВУКОВОГО ВХІДНОГО ПРИСТРОЮ ЗОВНІШНЬОГО СТИСНЕННЯ

<jats:p>The article presents the main results of research on the parameters and characteristics of an axisymmetric external compression supersonic inlet device, considering the processes occurring with increasing the Mach number. The subject of the study is the dependence of the total pressure conservation coefficient and the drag coefficient of the central body of an axisymmetric inlet device of external compression on the Mach number and the cone half-angle. The object of the study is an axisymmetric supersonic inlet device of external compression. The aim of the work is to improve the methodology for calculating the flow parameters over the conical surface of an axisymmetric inlet device and determine its main aerodynamic characteristics. To achieve this aim, the following tasks were addressed: the methodology for calculating the parameters of the supersonic flow over the conical surface of an axisymmetric inlet device of external compression was improved by solving the Taylor-McColl equation; the calculation of the total pressure recovery coefficient and drag coefficient was carried out, considering the change in the adiabatic coefficient from the Mach number in the supersonic part of the axisymmetric inlet device of external compression. The method of gas-hydraulic theory of compression jumps was used in the study. The study was conducted at a design altitude of 0 km, in the range of the Mach numbers from 2.0 to 10 with a change in the cone half-angle from 120 to 200. To assess the influence of the change in the adiabatic index on the total pressure conservation coefficient, the drag coefficient of the conical central body in the supersonic part of the external compression inlet device, considering the processes occurring with an increase in the Mach number, modeling was performed with a constant adiabatic index (1.4) and a variable one that depends on the Mach number at the inlet to the inlet device. The results obtained from modeling the flow in an axisymmetric supersonic external compression inlet device can be used to justify the choice of the cone half-angle for the design the Mach number when creating a preliminary model of the axisymmetric inlet device. The scientific novelty and practical significance of the research results lie in the fact that new data have been obtained on the coefficient of conservation of total pressure of the drag coefficient of the central conical body in the supersonic part of the supersonic input device of external compression, considering the change in the adiabatic coefficient depending on the Mach number</jats:p>