  Base pressure control is often employed on drag reduction design, but the
interaction of the jet with the base region flow topology can generate
undesired or uncontrolled flow configurations. The ejected flow can drive
pressure bifurcations at the trailing edge, that without a correct optimization
can affect the aerodynamic performance of the system. The purpose of this work
is to fully understand the physical mechanisms related with the use of injected
base bleed employing global stability analysis and adjoint methodologies.
Moreover, the results of the sensitivity analysis are used to identify the
regions more receptive to passive and active flow control methodologies. This
work has a particular relevance in turbine research, where coolant flow is
ejected at the trailing edge to ensure an adequate thermal protection of the
blade and the downstream turbine stages.
