Shock-wave boundary-layer interactions with bleed through rows of holes

Computations were performed to investigate three-dimensional, shock-wave/boundary-layer interactions on a flat plate with bleed through four staggered rows of circular holes that discharge into the same plenum. The focus of the computations was to examine holy bleed through rows of holes affect bleed rate and the pressure and Mach number distributions. The effects of the following parameters on the flow were investigated: 1) with and without shock-wave impingement on the boundary layer and 2) spacings between bleed holes in the streamwise and spanwise directions. Results show that just two rows of bleed holes arranged in a staggered fashion placed upstream of the incident shock are adequate in blocking the shock-induced adverse pressure gradient from propagating further upstream. Results also show that the spacings between the centers of holes can exceed the hole diameter not just in the streamwise direction, but also in the spanwise direction, and still be able to control shock-induced flow separation. This study is based on the ensemble-averaged, ''full compressible'' Navier-Stokes (N-S) equations closed by the Baldwin-Lomax algebraic turbulence model. Solutions to the ensemble-averaged N-S equations were obtained by an implicit, partially split, two-factored algorithm with flux-vector splitting in the streamwise direction on a chimera overlapping grid.