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

摘要

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.