Abstract
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.
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