Abstract
Velocity measurements and flow visualization were obtained in a specially prepared 32% model of the Space Shuttle main engine (SSME) main injector bowl. Refractive-index-matching techniques were used to obtain three components of mean and fluctuating velocities throughout the flow without the usual restrictions associated with multiple solid-liquid boundaries and complex surface curvature, Measurements of mean-flow and turbulence normal stresses were obtained to quantify flow characteristics in the inlet ducts, entrance region, racetrack, LOX postbundle, and exit nozzle. Measured velocity distributions show the upstream effect of the injector bowl in the transfer ducts, the plenum effect of the racetrack and LOX postbundle, and the nonuniform distribution of the flow into the main exit nozzle.
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