Upstream Mixing Cavity Coupled with a Downstream Flameholding Cavity Behavior in Supersonic Flow (Postprint)
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH DEPT OF AERONAUTICS AND ASTRONAUTICS
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Experimental investigations of the flowfield associated with three upstream direct injection acoustic resonance cavities coupled with a previously designed downstream combustion cavity in a non-reacting flow are described. All of the upstream mixing cavities were acoustically open shear layer reattachment on the downstream wall of the cavity with the length-to-depth ratio LD on the order of 1. The previously established downstream combustion cavity had an LD of 4.7 and an aft ramp angle of 22.5 degrees. The three upstream mixing cavities were characterized in Mach 2 freestream flow with injection at three locations upstream wall, center, downstream wall within each cavity. Injection at the upstream wall of the cavity provided greater penetration height into the freestream as well as faster mixing with the freestream compared with injection at the center or downstream wall of the cavity. Injection at the center of the cavity resulted in the injectant diffusing laterally in the cavity before being ejected into the freestream. Injection at the downstream cavity wall displayed characteristics of both injection at the upstream wall and center of the cavity.
- Fluid Mechanics
- Combustion and Ignition
- Test Facilities, Equipment and Methods