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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Bibliographic Details
Published in:Fluid dynamics 2009-10, Vol.44 (5), p.680-686
Main Authors: Kolin, I. V., Markov, V. G., Sukhanov, V. L., Trifonova, T. I., Shukhovtsov, D. V.
Format: Article
Language:English
Subjects:
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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Description
Summary: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