Effect of Mach Number on Stability of Boundary Layer Over a Rotating Cone in Hypersonic Flow
Spinning vehicles achieve gyroscopic effects by rotating around their axis. However, transition significantly influences the stability of flight. In this work, a study of instability on the unstable modes in boundary layers over a rotating cone in hypersonic flows was presented with linear stability...
Saved in:
| Main Authors: | , , , |
|---|---|
| Format: | Article |
| Language: | zho |
| Published: |
China Astronautic Publishing CO., LTD. ; Editorial Office of Physics of Gases
2025-05-01
|
| Series: | 气体物理 |
| Subjects: | |
| Online Access: | http://qtwl.xml-journal.net/cn/article/doi/10.19527/j.cnki.2096-1642.1121 |
| Tags: |
Add Tag
No Tags, Be the first to tag this record!
|
| Summary: | Spinning vehicles achieve gyroscopic effects by rotating around their axis. However, transition significantly influences the stability of flight. In this work, a study of instability on the unstable modes in boundary layers over a rotating cone in hypersonic flows was presented with linear stability theory (LST). To quantify the effect of Mach number, Mach numbers 5~10 were considered, and a higher rotational velocity was considered for analysis of centrifugal mode. The influence of Mach number on different stability modes varies, which was confirmed with LST analysis. Modified Mack mode, cross-flow mode and centrifugal mode shift towards low frequency, low streamwise and circumferential wavenumbers. Also, maximum amplification rate of modified Mack mode, cross-flow mode and centrifugal mode decrease with Mach number. Meanwhile, oblique wave instinct of second mode is uncovered, and wave angle of second mode decreases with Mach number. |
|---|---|
| ISSN: | 2096-1642 |