Abstract
An experimental investigation of a Mach 1.61 multiple normal shock wave/turbulent boundary layer interaction in a rectangular, nearly constant area duct is discussed with an emphasis on the turbulence phenomena. The two-component LDV measurements reveal a large amplification of the turbulence kinetic energy and Reynolds stress through the interaction. The leading shock in the multiple shock pattern causes a significant distortion of the turbulent stress tensor. Partial recovery occurs immediately downstream of the first shock. The trailing shocks in the system are much weaker than the first shock and tend to maintain the nonequilibrium turbulence structure, with complete recovery occurring well downstream of the interaction.
| Original language | English (US) |
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| State | Published - 1990 |
| Event | AIAA 21st Fluid Dynamics, Plasma Dynamics and Lasers Conference, 1990 - Seattle, United States Duration: Jun 18 1990 → Jun 20 1990 |
Other
| Other | AIAA 21st Fluid Dynamics, Plasma Dynamics and Lasers Conference, 1990 |
|---|---|
| Country/Territory | United States |
| City | Seattle |
| Period | 6/18/90 → 6/20/90 |
ASJC Scopus subject areas
- Aerospace Engineering
- Condensed Matter Physics
- Electrical and Electronic Engineering
- Engineering (miscellaneous)