Quasi-periodic relaxation to a steady flow regime after pulsed energy input into the incoming stream

This paper is devoted to development of acoustic methods for the investigation of the dynamics of structural changes in iron-based alloys, which are associated with phase transitions, processes of recrystallization and relaxation, and physical stimulation of various types. Samples of Armco iron are used to obtain the temperature dependences of the velocity and attenuation of ultrasound in the range from 20 to 1040 °C. The acoustic properties of 08Kh14AN4MDB high-strength corrosion-resistant martensitic steel are measured in the same temperature range. The obtained data on the propagation velocity of sound are used to calculate the values of the elastic modulus of Armco iron and 08Kh14AN4MDB steel in the range from 20 to 950 °C.

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

Tarnavskii

2005

High Temp

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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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Quasi-periodic relaxation to a steady flow regime after pulsed energy input into the incoming stream

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

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

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

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

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