Abstract
The article gives the results of an investigation of flows in supersonic axisymmetric conical nozzles with the presence of shock waves in the flow. The method of straight-through calculation [1] and the method of small perturbations [2] are used. An investigation is made of the effect of various geometric parameters and of the adiabatic index on the flow of a gas in conical nozzles. A comparison is made with experimental data.
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G. S. Roslyakov and V. P. Sukhrukov, “Difference method for calculating flows of gas with discontinuities,” in: Computational Methods and Programming [in Russian], No. 19, Izd. MGU, Moscow (1972).
I. S. Zhiguleva and U. G. Pirumov, Investigation of the Propagation of Small Perturbations in Supersonic Conical Nozzles [in Russian], Izd. Oborongiz, Moscow (1959).
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U. G. Pirumov, “Investigation of flow in sub- and transonic regions of a Laval nozzle,” Izv. Akad. Nauk SSSR, Mekhan. Zhidk. Gaza, No. 1 (1970).
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Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 3, pp. 101–107, May–June, 1974.
In conclusion, the authors thank N. V. Drozdov for his participation in carrying out the calculations.
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Pirumov, U.G., Roslyakov, G.S. & Sukhorukov, V.P. Investigation of supersonic flows in conical nozzles. Fluid Dyn 9, 415–420 (1974). https://doi.org/10.1007/BF01025525
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DOI: https://doi.org/10.1007/BF01025525