Abstract
The paper is devoted to an experimental and theoretical study of effect of moderate angle-of-attack variation on disturbances evolution and laminar-turbulent transition in a supersonic boundary layer on swept wing at Mach 2. Monotonous growth of the transition Reynolds numbers with angle of attack increasing from −2° to 2.7° is confirmed. For the same conditions, calculations based on linear stability theory are performed. The experimental and computational results show a favourable comparison.
Original language | English |
---|---|
Pages (from-to) | 96-101 |
Number of pages | 6 |
Journal | Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering |
Volume | 234 |
Issue number | 1 |
DOIs | |
Publication status | Published - 1 Jan 2020 |
Keywords
- angle of attack
- experiment
- hot-wire measurements
- Supersonic boundary layer
- swept wing
- NUMBER
- STABILITY
OECD FOS+WOS
- 2.11 OTHER ENGINEERING AND TECHNOLOGIES