Математическое моделирование газодинамических процессов в импульсной аэродинамической установке и расчет некоторых параметров потока в рабочей части

Abstract

Описывается математическое моделирование газодинамических процессов, протекающих в основных функциональных частях импульсной аэродинамической установки. Осуществляется расчет локальных и интегральных параметров обтекания модели конуса, расположенной в рабочей части установки. Приводится качественное и количественное сравнение результатов математического и физического моделирования. Purpose.The aim of this paper is the mathematical modelling of gasdynamic processes and the incoming airflow around the model fixed in the test chamber of the main functional elements of a pulsed aerodynamic facility. Methodology.Physical and mathematical modelling methods are jointly used for comprehensive description of the processes under study. The experimentally obtained results of drainage and balance measurements combined with visualization of the flow around the model using the shadow method are used to validate the numerical solution of the problem. System of unsteady Reynolds averaged NavierStokes (RANS) equations and SST turbulence model are used for mathematical description of the movement of working gas flow from prechamber through the nozzle to the test chamber where the body was fixed. Finite elements method implemented in Ansys Fluent computational complex is used for the numerical solution. Findings.Mathematical modelling of the flow around the cone model by the incoming flow with Mach numbers M 2...5 was carried out. The distribution fields of gasdynamic parameters (,P,T,M) over the entire internal volume of the pulsed aerodynamic facility (prechamber, axisymmetric nozzles set, test chamber) are obtained. The values of static pressure at the model surface and Mach number at nozzle exit are calculated for each velocity. Relative error between numerical calculation and experimental data is obtained to be of the order of 10 and 3, respectively. For flow structure near the model we obtain a qualitative agreement that the density distribution field is identical to the shadowgraph flow visualization pattern. Value.A numerical method for calculation of local and integral parameters of supersonic and hypersonic flow around models in test chamber of aerodynamic facility was implemented. Information about the gasdynamic flow parameters at the nozzle exit allowing the study of the flow around the model for the cases with more complex geometry using mathematical modelling based on the results of experiments.