Abstract
Multiple shock wave/turbulent boundary layer interactions in a rectangular duct have been investigated using wall pressure measurements, surface oil flow visualization, and spark Schlieren photography. At Mach 2.45 the shock structure was a neutrally stable pattern of oblique shocks followed by repeated normal shocks with the level of flow confinement having only a small effect on the interaction. At Mach 1.6 the pattern consisted of a bifurcated normal shock followed by weaker unbifurcated normal shocks. At this lower Mach number the interaction was much steadier with the length of the interaction scaling directly with the level of flow confinement.
| Original language | English (US) |
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| State | Published - 1988 |
| Event | 1st National Fluid Dynamics Conference, 1988 - Cincinnati, United States Duration: Jul 25 1988 → Jul 28 1988 |
Other
| Other | 1st National Fluid Dynamics Conference, 1988 |
|---|---|
| Country/Territory | United States |
| City | Cincinnati |
| Period | 7/25/88 → 7/28/88 |
ASJC Scopus subject areas
- Aerospace Engineering
- Engineering (miscellaneous)