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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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