Abstract
A variation of conventional passive normal shock/boundary layer interaction control termed Mesoflaps for Aeroelastic Transpiration (MAT) has been investigated in a planar Mach 1.37 wind tunnel. Qualitative analysis of the MAT devices investigated was achieved with spark shadowgraph visualizations and oil-streak surface-flow visualizations, while quantitative analysis was accomplished by measuring surface pressure distributions and boundary layer velocity profiles. Eight different MAT arrays were tested, in addition to the solid-wall reference case. It was found that flap thickness, and therefore transpiration rate, had a demonstrable effect on static and total pressure recovery, in addition to boundary layer integral properties. Furthermore, one particular flap array was found to have significantly higher static and total pressure recoveries than the reference case, while simultaneously maintaining the same boundary layer displacement thickness but reduced momentum thickness.
| Original language | English (US) |
|---|---|
| State | Published - 2001 |
| Externally published | Yes |
| Event | 39th Aerospace Sciences Meeting and Exhibit 2001 - Reno, NV, United States Duration: Jan 8 2001 → Jan 11 2001 |
Other
| Other | 39th Aerospace Sciences Meeting and Exhibit 2001 |
|---|---|
| Country/Territory | United States |
| City | Reno, NV |
| Period | 1/8/01 → 1/11/01 |
ASJC Scopus subject areas
- Space and Planetary Science
- Aerospace Engineering