Abstract
High-speed schlieren imaging was implemented to monitor the shock structure and quantify the flow dynamics of a cylinder-induced shock-wave–boundary-layer interaction (SBLI) as the state of the interaction was brought through transition by use of boundary-layer trips and Reynolds number regulation. Measurements were acquired at sampling rates ranging from 500 to 240,000 frames per second. As the SBLI was cycled toward a turbulent state, the mean shock structure atrophied, and the separation shock intermittent distance was reduced. The primary separation shock within the transitional SBLI structure followed a clear cycle, characterized by outboard travel, stall, disappearance, and replacement. The shock structure and supersonic jet were observed to be dominated by low-frequency fluctuations (500–1500 Hz). Higher-frequency peaks were observed at the base of the cylinder (20–25 kHz) and above the supersonic jet, just upstream of the cylinder (15–30 kHz).
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