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Design of universal supersonic nozzles with conical flow

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Abstract

The problem of designing the supersonic part of nozzles creating “source” type flows self-similar with respect to the isentropic exponent is solved. A function that approximates the geometry of nozzle channels with cone angles up to 15° is derived. The results of solving the direct nozzle problem, which confirm the accuracy of the approximation obtained, are presented.

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Literature cited

  1. N. V. Drozdova, U. G. Pirumov, G. S. Roslyakov, and V. P. Sukhorukov, “Supersonic flows in conical nozzles,” in: Some Applications of the Method of Nets in Gas Dynamics, No. VI. Gas Flows in Nozzles and Jets [in Russian], Publishing House of Moscow State University, Moscow (1974), p. 129.

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  2. U. G. Pirumov, “Calculation of the flow in a Laval nozzle,” Izv. Akad. Nauk SSSR, Mekh. Zhidk. Gaza, No. 5, 10 (1967).

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  3. A. N. Ganzhelo, “Calculation of plane and axisymmetric supersonic inviscid gas flows by a second-order-accurate shock-capturing method,” Uch. Zap. TsAGI,17, 27 (1986).

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Authors and Affiliations

  1. Moscow

    I. S. Zorina, M. Yu. Kurshakov & N. V. Chirkov

Authors
  1. I. S. Zorina
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  2. M. Yu. Kurshakov
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  3. N. V. Chirkov
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Additional information

Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 4, pp. 183–186, July–August, 1989.

The authors are grateful to A. N. Ganzhelo for supplying the supersonic flow calculation programs.

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Zorina, I.S., Kurshakov, M.Y. & Chirkov, N.V. Design of universal supersonic nozzles with conical flow. Fluid Dyn 24, 649–652 (1989). https://doi.org/10.1007/BF01052437

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  • DOI: https://doi.org/10.1007/BF01052437

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