Physical Modeling of Supersonic Flow Over Bodies with Plane and Axisymmetric Shape

One of the major stages in methods development of internal ballistic performance calculation for propulsion (thrust, density impulse, the fuel burning rate, pressure-chamber, etc.) is a simulation of the structure and definition of the gas encircling flow parameters. During the operation of the engine by supersonic flowing, the verification of the developed mathematical models on the basis of a comparison with experimental data is required due to the complexity of the intra-chamber processes and changes in performance duct tract geometry. Field tests of the engines are conducted to obtain the necessary data on the main parameters of the process, but it is due to the high material costs. A comparative analysis of numerical and experimental data obtained by laboratory model tests is the most efficient way to obtain objective experimental data. This paper presents the results of an experimental study of one of the main parameters of supersonic air stream over bodies with plane and axisymmetric shape in the range of Mach number M=(2÷5).