Abstract
The mixing processes in supersonic flows are visualized by the Schlieren method. A gaseous nitrogen jet is injected normally into the external flow through a traverse slot nozzle mounted on the flat plate model. Experiments are conducted under the conditions of freestream Mach number of 3.81, total pressure of 1.2 MPa, Reynolds number of 1.0×107. Sonic nozzles, whose width are 0.5, 1.0 and 2.0 mm, are used. In the experiments the total pressure ratio of the secondary flow to the freestream is varied from 0.1 to 0.5.
The results show that the bow shock wave/turbulent boundary layer interaction induces the boundary layer separation in front of the injection. In the interacting flow, barrel shock waves and Mach disk are observed clearly. As the total preesure ratio is increased, the separation region, the extent of the interaction region and shock structures becomes larger.
