000013918 001__ 13918
000013918 005__ 20161115094005.0
000013918 04107 $$aeng
000013918 046__ $$k2016-08-21
000013918 100__ $$aPanina, Alexandra
000013918 24500 $$aNonlinear disturbance evolution in supersonic boundary layers on the swept wing

000013918 24630 $$n24.$$p24th International Congress of Theoretical and Applied Mechanics - Book of Papers
000013918 260__ $$bInternational Union of Theoretical and Applied Mechanics, 2016
000013918 506__ $$arestricted
000013918 520__ $$2eng$$aThe paper presented the results on the generation and development of the wave train in uniform and spanwise modulated boundary layer at Mach 2. A swept-wing model was used in the experiments. In 3D boundary layer the oblique breakdown mechanism is detected, which previously observed only in a supersonic boundary layer on flat plate. It was obtained that in the spanwise modulated boundary layer the oblique breakdown mechanism occurs at lower values of the longitudinal coordinate x.

000013918 540__ $$aText je chráněný podle autorského zákona č. 121/2000 Sb.
000013918 653__ $$a

000013918 7112_ $$a24th International Congress of Theoretical and Applied Mechanics$$cMontreal (CA)$$d2016-08-21 / 2016-08-26$$gICTAM2016
000013918 720__ $$aPanina, Alexandra
000013918 8560_ $$ffischerc@itam.cas.cz
000013918 8564_ $$s636766$$uhttps://invenio.itam.cas.cz/record/13918/files/PO.FM07-1.11.127.pdf$$yOriginal version of the author's contribution as presented on CD, XMLout( page 1005, code PO.FM07-1.11.127).
000013918 962__ $$r13812
000013918 980__ $$aPAPER