SHOCK-WAVE FLOW REGIMES AT ENTRY INTO THE DIFFUSER OF A HYPERSONIC
RAMJET ENGINE: INFLUENCE OF PHYSICAL PROPERTIES OF THE GAS MEDIUM

G. A. Tarnavskii

UDC 518.5:533.6

The physical aspects of the effective-adiabatic-exponent 
model making it possible to decompose the total problem on modeling 
of high-velocity gas flows into individual subproblems ("physicochemical 
processes" and "aeromechanics"), which ensures the creation of a universal 
and efficient computer complex divided into a number of independent 
units, have been analyzed. Shock-wave structures appearing at entry 
into the duct of a hypersonic aircraft have been investigated based 
on this methodology, and the influence of the physical properties 
of the gas medium in a wide range of variations of the effective adiabatic 
exponent has been studied.

Institute of Computational Mathematics and Mathematical 
Geophysics, Siberian Branch of the Russian Academy of Sciences, 6 
Akad. Lavrent'ev Ave., Novosibirsk, 630090, Russia; email: Gennady@Tarnavsky.ru. 
Translated from Inzhenerno-Fizicheskii Zhurnal, Vol. 79, No. 4, pp. 
69-80, July-August, 2006. Original article submitted January 11, 2005.