Investigation of the development of unsteady flow separation from a model swept wing

The results of an experimental wind-tunnel investigation of the flow patterns on the swept wing of a model aircraft realized for pitching oscillations with an amplitude A α = 5° with respect to setup angles of attack α 0 = 10 and 16° are presented.

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Bibliographische Detailangaben
Veröffentlicht in:	Fluid dynamics 2009-10, Vol.44 (5), p.680-686
Hauptverfasser:	Kolin, I. V., Markov, V. G., Sukhanov, V. L., Trifonova, T. I., Shukhovtsov, D. V.
Format:	Artikel
Sprache:	eng
Schlagworte:	Aircraft Amplitudes Angle of attack Classical and Continuum Physics Classical Mechanics Computational fluid dynamics Engineering Fluid Dynamics Fluid- and Aerodynamics Oscillations Physics Physics and Astronomy Swept wings Unsteady flow Wind tunnels
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Beschreibung
Zusammenfassung:	The results of an experimental wind-tunnel investigation of the flow patterns on the swept wing of a model aircraft realized for pitching oscillations with an amplitude A α = 5° with respect to setup angles of attack α 0 = 10 and 16° are presented.
ISSN:	0015-4628 1573-8507
DOI:	10.1134/S0015462809050068