Influence of a Normal Slot Boundary Layer Suction System onto a Shock Train

摘要: The recompression of supersonic gas flow is a very common phenomenon in modern aerodynamics and occurs great number applications for instance ramjet or scramjet inlets, internal diffusers ejectors. Under certain conditions even one more shocks can appear downstream the first shock. This series so called shock train. In contrast to other systems decelerated at through system followed by mixing region as shown Fig. 1. For whole interaction Crocco et al. [1] have coined term pseudo-shock. structure length train depends much on confinement level which ratio boundary layer thickness δ half height nozzle h. was investigated thoroughly Carroll [2] Om [3]. case train, due occurrence successive pressure recovery along extends greatly deviates form gradient that would occur single normal shock, [4]. However, short best leads high temperature gradients, provides interesting opportunities various dynamic applications. order reduce thereby increasing must be exposed higher back pressure. under this lead relocation farther upstream, because only withstand level. ability overcome strong limited, velocity hence impulse drops zero near wall. remove parts with small suction slot 1.5 mm wide placed upstream see