Results of a complex experiment-calculated investigation of the structure of a nonstationary gas flow in the working path of a hypersonic ramjet engine are presented. Methods of experimental determining the pressure and temperature distributions over the wall of an axisymmetric channel of complex geometry with a sudden widening are proposed and described. The problem on the gas flow over a ramjet engine positioned in a wind tunnel was solved.
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Translated from Inzhenerno-Fizicheskii Zhurnal, Vol. 94, No. 2, pp. 466–473, March–April, 2021.
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Ishchenko, A.N., Maslov, E.A., Skibina, N.P. et al. Complex Investigation of Nonstationary Flow with Shock Waves in the Working Path of a Hypersonic Ramjet Engine. J Eng Phys Thermophy 94, 450–457 (2021). https://doi.org/10.1007/s10891-021-02315-8
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DOI: https://doi.org/10.1007/s10891-021-02315-8