Abstract
Wall pressure fluctuations have been measured in the reattachment region of a supersonic free shear layer. The free shear layer was formed by the separation of a Mach 2.9 turbulent boundary layer from a backward facing step. Reattachment occurred on a 20° ramp. By adjusting the position of the ramp, the base pressure was set equal to the free stream pressure, and the free shear layer formed in the absence of a separation shock. An array of flush-mounted, miniature, high-frequency pressure transducers was used to make multichannel measurements of the fluctuating wall pressure in the vicinity of the reattachment region. Contrary to previous observations of this flow, the reattachment region was found to be highly unsteady, and the pressure fluctuations were found to be significant. The overall behavior of the wall pressure loading is similar in scale and magnitude to the unsteadiness of the wall pressure field in compression ramp flows at the same Mach number. Rayleigh scattering was used to visualize the instantaneous shock structure in the streamwise and spanwlse direction. Spanwise “wrinkles” on the order of half the boundary layer thickness were observed.
| Original language | English (US) |
|---|---|
| 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 |
All Science Journal Classification (ASJC) codes
- Aerospace Engineering
- Condensed Matter Physics
- Electrical and Electronic Engineering
- Engineering (miscellaneous)