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

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.

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“…5). A wide spectrum of the investigations of the shockwave flow patterns arising at the hypersonic scramjet engine inlet was done in the works [3,4] with regard for the variation of the gaseous medium properties on shocks. The configuration of shocks, the type of their interaction (the Mach and/or regular type) and the flow parameters between the shock fronts under the variation of the flight altitude in the Earth atmosphere from 0 to 100 km, the flight velocities from 1.5 to 7 km/s, the diffuser angles from 0 to 50 degrees were determined.…”

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