Abstract
Experiments were carried out to study the characteristics of compressible concave-corner flows. The surface-pressure distributions show similar characteristics for all of the test cases. It was found that the flows decelerate upstream of the corner and accelerate downstream of the corner. Stronger upstream compression and downstream expansion were observed with increasing Mach number of concave-corner angle.
| Original language | English |
|---|---|
| Pages (from-to) | 797-799 |
| Number of pages | 3 |
| Journal | Journal of Aircraft |
| Volume | 40 |
| Issue number | 4 |
| DOIs | |
| Publication status | Published - 2003 |
All Science Journal Classification (ASJC) codes
- Aerospace Engineering