Characterization of base bleed effects on subsonic trailing edge flows

Trailing edge injection enables control of the detached and unsteady flow within base region. The interaction jet with region alters topology causing pressure bifurcations at trailing that affect aerodynamic performance system modify vortex patterns downstream body. purpose this work is to fully characterize physical effects related use bleed on an airfoil subsonic conditions. Defining a non-dimensional rate Cb=m˙/ρ∞U∞h, wide range from Cb=0 Cb=1 applied simplified model turbine blade. influence geometry shape also evaluated, showing rounded geometries have potential minimize undesirable injection. Vortex shedding neutralized when (non-dimensional) ejected mass exceeds value Cb=0.8 Cb=0.55 for straight geometries, respectively. Additionally, neutralization occurs relatively low rates, often accompanied by onset non-symmetrical configuration edge. This has particular relevance in aerothermal gas design, where coolant may be ensure adequate thermal protection airfoils.