Modeling of controlled shock-wave/boundary-layer interactions in transonic channel flow

The importance of systems aimed at controlling shock-wave/boundary-layer interactions appears for transport aircraft in the domain of transonic external flows and for supersonic air intakes in the domain of internal flows. The calibration of these systems requires powerful predictive calculation methods and therefore improvements in the modeling of complex turbulent interactions. The need for validation of numerical methods and turbulence models for this field of applications has motivated experiments aimed at producing exhaustive sets of experimental data on two-dimensional configurations. These kinds of experimental cases are very useful for model testing because they permit numerous parametrical numerical studies. This program has been completed in its experimental and theoretical part for the case of a passive control device, which consists of a feedback of the external flow through a cavity, covered by a perforated plate located in interaction region. The main results are presented, and the legitimacy of modeling injection by Poll's law is confirmed. The recently defined k-sigma turbulence model is validated, and its results are compared with those given by the Chien and Launder-Sharma versions of the k-epsilon model. The new model, primarily tested in the case of supersonic backward-facing step separations, has given satisfactory results too in simulating these transonic internal flows.