Shock/Boundary-Layer Interaction Effects on Transverse Jets in Crossflow over a Flat Plate

This study examines the near-field mean flow structure of a transverse jet in subsonic and supersonic crossflows using computational fluid dynamics. The results show the shock/boundary-layer interaction present in supersonic crossflow alters the mean flow in the near field of a transverse jet compared to subsonic crossflow. The interaction bifurcates the phase portrait of the separation topology through the addition of saddle points, nodes, and separation lines. In subsonic crossflow at a nozzle pressure ratio of 5, the near-field, mean flow structure includes horn vortices, near-field wake vortices, and far-field wake vortices. In supersonic crossflow, at the same pressure ratio, the bifurcation resulting from the shock/boundary-layer interaction eliminates the near-field and far-field wake vortices leaving only the horn vortices. The shock/boundary-layer interaction also generated another set of global separation lines within which a set of horseshoe vortices formed. These global separation lines did not converge, allowing the horseshoe vortices to affect the mean flow along the entire length of the plate downstream of the jet. Alteration of the mean flow in the near field affected the surface pressure distribution and ultimately the jet interaction performance coefficients. [PUBLISHER ABSTRACT]