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Aerodynamic wind tunnels the one of the widely used tools for aerophysics research. The wind-tunnel test technique allows the results of experiments transferred on full-scale objects. In view of the complexity of recording in supersonic flows, the numerical simulation affords opportunity to make more full description of process and to obtain distribution of gas-dynamic parameters. The purpose of the research is mathematical simulation of gas movement in internal volume of an impulse aerodynamic wind tunnel. For mathematical description of process Unsteady Reynolds averaged Navier-Stokes equations are used. The initial and boundary conditions are chosen according to aerodynamic experiments. By the numerical calculation a gas-dynamic parameters in steady supersonic flow on the edge of axisymmetric nozzle are obtained. Results of simulation corresponds with quasisteady flow regime in real aerodynamic tests. Obtained data can be used to solve a wide range of problems, theoretical and engineering analysis of experimental results. [ABSTRACT FROM AUTHOR]

Investigation of supersonic flows in internal channels of various geometries is widely problem of aerospace. Nowadays, the ramjet engine with supersonic combustion is an advance engine for hypersonic aircrafts and space vehicles. The study of operating principle and mechanics of ramjet can be simplify to study of supersonic flow in a profiled internal duct simulates a section of a working path or fuel chamber. The aim of study is an experimental and computational study of supersonic flow in an internal axisymmetric internal channel with sudden expansion at case of oncoming flow velocity of M = 5 and M = 6. The proposed devices for pressure and temperature on wall of duct recording are described. The comparison of results of measurements in aerodynamic tests and corresponding numerical calculation is presented. Close agreement for experimental and numerical calculation obtained. Based on correlation of aerodynamic tests and simulation results verification of previously proposed approach for solve problem of flow around model in test section of aerodynamic wind tunnel presented. [ABSTRACT FROM AUTHOR]