摘要
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.
| 原文 | English |
|---|---|
| 頁（從 - 到） | 797-799 |
| 頁數 | 3 |
| 期刊 | Journal of Aircraft |
| 卷 | 40 |
| 發行號 | 4 |
| DOIs | |
| 出版狀態 | Published - 2003 |
All Science Journal Classification (ASJC) codes
- 航空工程