Influence of small attack angles on the transition on the wing with the subsonic leading edge at M=2

The paper is devoted to an experimental study of laminar-turbulent transition in supersonic boundary layers on swept wings. The experiments were fulfilled in the low nose supersonic wind tunnel T-325 of Khristianovich Institute of Theoretical and Applied Mechanics on the models of a swept wing with...

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Bibliographische Detailangaben

Hauptverfasser:	Semionov, N. V., Kosinov, A. D., Yermolaev, Yu. G., Kocharin, V. L., Shipul, S. A., Yatskikh, A. A.
Format:	Tagungsbericht
Sprache:	eng
Schlagworte:	Angle of attack Boundary layer transition Computational fluid dynamics Laminar flow Supersonic boundary layers Supersonic wind tunnels Swept wings Transition points Turbulent boundary layer Turbulent flow
Online-Zugang:	Volltext
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