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Investigation of flows in hypersonic nozzles in the framework of simplified Navier-Stokes equations

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Abstract

Simplified Navier-Stokes equations have found application as an alternative to the complete Navier-Stokes equations for the simulation of viscous gas flows in regions of large dimensions, when there is a predominant direction of the flow [1–4]. In the present paper, flows in wind tunnel nozzles are investigated on the basis of this model. Flows in conical and profiled axisymmetric hypersonic nozzles are calculated in a wide range of Mach and Reynolds numbers. Good agreement with the experiment is obtained. The important role of viscous-inviscid interaction in nozzles for large hypersonic Mach numbers is shown.

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Authors and Affiliations

  1. Novosibirsk

    M. I. Muchnaya

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  1. M. I. Muchnaya
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Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 6, pp. 20–26, November–December, 1986.

The representation of the nature of flows in hypersonic nozzles given here arose as a result of repeated discussions of the results of the calculations with my colleagues: V. N. Vetlutskii, V. L. Ganimedov, G. P. Klemenkov, Yu. G. Korobeinikov, and V. I. Pinchukov, for which the author is deeply grateful to them.

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Muchnaya, M.I. Investigation of flows in hypersonic nozzles in the framework of simplified Navier-Stokes equations. Fluid Dyn 21, 860–866 (1986). https://doi.org/10.1007/BF02628019

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  • DOI: https://doi.org/10.1007/BF02628019

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