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.
|Number of pages||6|
|Journal||Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering|
|Publication status||Published - 1 Jan 2020|
- angle of attack
- hot-wire measurements
- Supersonic boundary layer
- swept wing