Abstract
Experiments and numerical simulations have been performed on a novel method of shock wave/boundary layer interaction control. A series of thin flaps, termed mesoflaps, were placed over a cavity directly beneath the impingement point of an oblique shock wave in Mach 2.5 supersonic flow. The passive system produced a significant degree of control of the SBLI including improved stagnation pressure recovery and boundary layer properties downstream of the interaction. The aeroelastic fully viscous numerical simulation of the experimental configuration confirmed general observed trends and also specific improvements in boundary layer properties downstream of the interaction.
| Original language | English (US) |
|---|---|
| State | Published - 2000 |
| Event | Fluids 2000 Conference and Exhibit - Denver, CO, United States Duration: Jun 19 2000 → Jun 22 2000 |
Other
| Other | Fluids 2000 Conference and Exhibit |
|---|---|
| Country/Territory | United States |
| City | Denver, CO |
| Period | 6/19/00 → 6/22/00 |
ASJC Scopus subject areas
- Fluid Flow and Transfer Processes
- Energy Engineering and Power Technology
- Aerospace Engineering
- Mechanical Engineering