Two-dimensional unsteady leading-edge separation on a pitching airfoil

The intial stages of two-dimensional unsteady leading-edge boundary-layer separation of laminar subsonic flow over a pitching NACA-0012 airfoil were studied. Results show the emergence of a primary clockwise-rotating recirculating region near the leading edge.

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Bibliographische Detailangaben
Veröffentlicht in:	AIAA journal 1994-04, Vol.32 (4), p.673-681
Hauptverfasser:	Choudhuri, P. Ghosh, Knight, D. D, Visbal, M. R
Format:	Artikel
Sprache:	eng
Schlagworte:	Aerodynamics Aircraft Applied fluid mechanics Exact sciences and technology Fluid dynamics Fundamental areas of phenomenology (including applications) Physics
Online-Zugang:	Volltext
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Beschreibung
Zusammenfassung:	The intial stages of two-dimensional unsteady leading-edge boundary-layer separation of laminar subsonic flow over a pitching NACA-0012 airfoil were studied. Results show the emergence of a primary clockwise-rotating recirculating region near the leading edge.
ISSN:	0001-1452 1533-385X
DOI:	10.2514/3.12040