INFLUENCE OF FLOW ANGULARITIES IN A HYPERSONIC RAMJET 
DIFFUSER ON THE FORMATION OF THE
SHOCK-WAVE STRUCTURE OF THE REAL GAS FLOW

G. A. Tarnavskii

UDC 518.8:533.6

We have investigated the shock-wave structures arising 
at the entrance to the engine section of hypersonic aircraft and the 
influence on the process of their formation of the flow angularity 
after oblique shock fronts incident inside the diffuser with a different 
type of interaction (Mach or regular). To take into account the real 
properties of the atmosphere, we used the effective adiabatic exponent 
method permitting determination of the topology of shock-wave patterns 
and calculation of the gas- and thermodynamic parameters in various 
flow zones between the shock fronts in a wide range of diagnostic 
variables for the Earth's atmosphere.

Institute of Theoretical and Applied Mechanics, Siberian 
Branch of the Russian Academy of Sciences, 4/1 Institutskaya Str., 
Novosibirsk, 630090, Russia; email: tarnav@itam.nsc.ru. Translated 
from Inzhenerno-Fizicheskii Zhurnal, Vol. 77, No. 3, pp. 155-164, 
May-June, 2004. Original article submitted November 3, 2003.