Abstract
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 α0 = 10 and 16° are presented.
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References
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Original Russian Text © I.V. Kolin, V.G. Markov, V.L. Sukhanov, T.I. Trifonova, D.V. Shukhovtsov, 2009, published in Izvestiya Rossiiskoi Akademii Nauk, Mekhanika Zhidkosti i Gaza, 2009, Vol. 44, No. 5, pp. 60–67.
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Kolin, I.V., Markov, V.G., Sukhanov, V.L. et al. Investigation of the development of unsteady flow separation from a model swept wing. Fluid Dyn 44, 680–686 (2009). https://doi.org/10.1134/S0015462809050068
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DOI: https://doi.org/10.1134/S0015462809050068