An experiment on a swept cylinder with 68°-sweep angle at Mach number M = 2.5 is described. The flow attachment line was disturbed by two weak shock waves. Shock waves were generated by a two-dimensional surface inhomogeneity on the wall of the test section of wind tunnel. It was found that the laminar-turbulent transition on the attachment-line of the cylinder is accompanied by an uneven growth of pulsations. Influence of Mach waves on the transition when their fall on the cylinder far away from domain of measuring is not observed. The laminar-turbulent transition occurs at a much lower unit Reynolds numbers in the case when a pair of waves falling on the attachment-line near the measurement field.
Experimental study of the effects of couple weak waves on laminar-turbulent transition on attachment-line of a swept cylinder
INTERNATIONAL CONFERENCE ON THE METHODS OF AEROPHYSICAL RESEARCH (ICMAR 2016): Proceedings of the 18th International Conference on the Methods of Aerophysical Research ; 2016 ; Perm, Russia
AIP Conference Proceedings ; 1770 , 1
2016-10-13
8 pages
Conference paper
Electronic Resource
English
Laminar-turbulent transition of the incompressible swept attachment-line
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