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Supersonic flow deceleration in plane and axisymmetric channels

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Abstract

Supersonic perfect gas flow in plane and axisymmetric channels with the same duct contour is studied on the basis of a numerical solution of the two-dimensional Navier-Stokes and Euler equations. The calculations were carried out at an inlet Mach number M∞=4 for various Reynolds numbers and “bell-mouth“ half-angles. The effect of these parameters, as well as that of the flow three-dimensionality, on the flow pattern is demonstrated. In particular, the existence of viscous flow regimes providing the most effective supersonic flow deceleration and a higher degree of total pressure recovery as compared with the inviscid flow is established.

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References

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Authors
  1. V. A. Bashkin
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  2. I. V. Egorov
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  3. D. V. Ivanov
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Additional information

Moscow. Translated from Izvestiya Rossiiskoi Akademii Nauk, Mekhanika Zhidkosti i Gaza, No. 2, pp. 143–152, March–April, 1998.

The study was carried out with the support of the Russian Foundation for Fundamental Research (project No. 95-01-01129a).

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Bashkin, V.A., Egorov, I.V. & Ivanov, D.V. Supersonic flow deceleration in plane and axisymmetric channels. Fluid Dyn 33, 272–279 (1998). https://doi.org/10.1007/BF02698712

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  • DOI: https://doi.org/10.1007/BF02698712

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