The influence of moderate angle-of-attack variation on disturbances evolution and transition to turbulence in supersonic boundary layer on swept wing

Research output: Contribution to journal › Article › peer-review

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	https://doi.org/10.1177/0954410019852804
Publication status	Published - 1 Jan 2020

angle of attack, experiment, hot-wire measurements, Supersonic boundary layer, swept wing, NUMBER, STABILITY

ID: 20655805