the starting behavior of a supersonic axisymmetric mixed compression air intake was numerically investigated. the code solves reynolds-averaged navier–stokes equations using an explicit finite volume method in a structured grid by the roe flux difference splitting scheme. further, it uses the baldwin–lomax algebraic model to compute the turbulent viscosity coefficient. the correct method of sur...

This paper proposes an effective numerical methodology to analyze the mechanism of the separation of an inserted type of solid rocket booster from a supersonic air breathing engine vehicle having a conical intake. Unlike the previous computational fluid dynamic (CFD) approach, present work constructs a compacted model capable to reduce the computational time definitely. The dynamics of vehicle ...

Szcrnmavy.-The available theoretical and experimental information on condensation of water vapour in the supersonic flow of air is reviewed and the influence of condensation on operation of supersonic tunnels is considered. The mechanism of condensation in supersonic flow is of molecular nature and does not depend on the presence of solid condensation nuclei in the air. As estimated by Oswatits...

The analytical and experimental studies of the aircraft’s supersonic air intakes have been carried out. An integrated approach to gas-dynamic designing that eliminates scale effect problem a wind tunnel with small-sized testing area is proposed. accelerates development process reduces resource intensity due rational distribution tasks between numerical physical experiments. results unique tests...

High speed wind tunnels are widely used in the study of fluid flow behavior around various objects. The air flow in the starting step of supersonic wind tunnels is transient including strong shock waves caused by the interaction of the tunnel main stream and the boundary layer at walls. To arrive in running step, the tunnel must be designed so as these waves leave immediately the test section. ...