Abstract:
In supersonic aerodynamics, the interaction phenomena shock/shock and shock/boundary layer, impose
physical crucial problems in practical flow configurations. They are encountered in the intakes supersonic air,
nozzle Rocket engines and supersonic air inlets. In this work, several numerical calculations were made touching
directly the bottom of those interaction phenomena in the above mentioned configurations. They are based on
solving stationary Navier-Stokes equations and quasi-stationary compressible supersonic flows, laminar and
turbulent, using the FLUENT commercial. These numerical calculations were conducted for multiple
configurations at different Mach numbers and pressure and injection ratios (NPR and SPR respectively). These
parameters are directly affecting shock interaction phenomena. The results show different shock configurations
according to the parameters mentioned above. An interaction zone on a flat plate of overall large in laminar
calculation than in turbulent one and a set of shocks in the divergent nozzle with and without secondary injection
have been highlighted. These results are generally consistent with those found experimentally and numerically.
