Investigation of annular supersonic inlets with isentropic compression

V. M. Galkin, V. I. Zvegintsev, D. A. Vnuchkov

Research output: Contribution to journalArticle

2 Citations (Scopus)

Abstract

A technique for designing the supersonic annular inlets with isentropic deceleration surfaces is considered. The contour of an isentropic supersonic nozzle constructed by the method of characteristics for an inviscid gas flow with given uniform parameters at the inlet and at the outlet is used as the basic configuration of the inlet. The reversed flow of a viscous gas is computed with the aid of numerical techniques in the contour under consideration and the real operational characteristics of the obtained inlet of a fixed geometry are determined in the range of the conditions of its application. In the process of computations, the minimum cross-sectional sizes are selected, which ensure the inlet start without a detached bow shock at the entrance.

Original languageEnglish
Pages (from-to)645-655
Number of pages11
JournalThermophysics and Aeromechanics
Volume23
Issue number5
DOIs
Publication statusPublished - 1 Sep 2016

Fingerprint

supersonic inlets
reversed flow
supersonic nozzles
method of characteristics
bows
deceleration
outlets
entrances
gas flow
shock
geometry
configurations
gases

Keywords

  • axisymmetric supersonic flow
  • ideal gas
  • nozzle
  • reversed flow
  • the inlet start
  • the method of characteristics
  • viscous flow

ASJC Scopus subject areas

  • Radiation
  • Nuclear and High Energy Physics

Cite this

Investigation of annular supersonic inlets with isentropic compression. / Galkin, V. M.; Zvegintsev, V. I.; Vnuchkov, D. A.

In: Thermophysics and Aeromechanics, Vol. 23, No. 5, 01.09.2016, p. 645-655.

Research output: Contribution to journalArticle

Galkin, V. M. ; Zvegintsev, V. I. ; Vnuchkov, D. A. / Investigation of annular supersonic inlets with isentropic compression. In: Thermophysics and Aeromechanics. 2016 ; Vol. 23, No. 5. pp. 645-655.
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