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Numerical simulation of gas dynamics of the inflow into a channel located behind a conical or plane shock wave

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Thermophysics and Aeromechanics Aims and scope

Abstract

The paper presents the results of a numerical study of gas dynamics and integral parameters of the flow at the channel entrance located behind a conical or plane shock wave. The freestream Mach number range is M = 2–4 and the range of the angles of the compression surfaces of the wedge and cone is δ= 10–90°. Data on the flow structure at the channel entrance, mass-averaged Mach numbers, total pressure loss coefficient, and flow rate coefficients are obtained. A comparative analysis of these parameters is performed, and the advantages and drawbacks of the channel entrance positions in various types of the flow are noted.

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Authors and Affiliations

  1. Khristianovich Institute of Theoretical and Applied Mechanics SB RAS, Novosibirsk, Russia

    V. I. Zvegintsev & I. I. Mazhul

Authors
  1. V. I. Zvegintsev
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  2. I. I. Mazhul
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Corresponding authors

Correspondence to V. I. Zvegintsev or I. I. Mazhul.

Additional information

This study was performed within the framework of the State Contract (State Registration Number 121030500158-0).

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Zvegintsev, V.I., Mazhul, I.I. Numerical simulation of gas dynamics of the inflow into a channel located behind a conical or plane shock wave. Thermophys. Aeromech. 30, 1013–1020 (2023). https://doi.org/10.1134/S0869864323060045

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  • DOI: https://doi.org/10.1134/S0869864323060045

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