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JOURNALS // Teplofizika vysokikh temperatur // Archive

TVT, 2005 Volume 43, Issue 1, Pages 57–70 (Mi tvt1227)

This article is cited in 1 paper

Heat and Mass Transfer and Physical Gasdynamics

Shock-wave modes of flow at the inlet to the diffuser of a hypersonic scramjet engine: The effect of flight altitude and velocity

G. A. Tarnavskii

Institute of Theoretical and Applied Mechanics, Siberian Branch of the Russian Academy of Sciences, Novosibirsk

Abstract: Analytical methods are used to investigate shock-wave structures characterized by different types of interaction (Mach or regular) of pressure shocks arising in hypersonic flows. The method of effective adiabatic exponent is used to include the actual properties of the atmosphere. Computer codes are developed to determine the topology of shock-wave patterns and to calculate the gas- and thermodynamic parameters in different zones of flow between shock fronts in the flight altitude range from zero to $100$ km and in the flight velocity range from $2$ to $7$ km/s. The limits of “Mach-regular” reflection transition are obtained, and domains of dual solution are determined in which interaction of both types is possible.

UDC: 518.5:533.6

Received: 11.11.2003


 English version:
High Temperature, 2005, 43:1, 58–72


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