Summary
A new flow model is proposed for describing quasi two-dimensional flows with shock-induced separation on wings of modest sweep. Correlations of the main features of the flow model over a wide range of Reynolds number have been deduced from wind-tunnel tests on wings and aerofoils. These correlations have successfully been used as a basis for simulating ‘full-scale’ flows over wings in the wind tunnel.
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References
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© 1986 Springer-Verlag Berlin, Heidelberg
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Fulker, J.L., Ashill, P.R. (1986). A Model of the Flow over Swept Wings with Shock Induced Separation. In: Délery, J. (eds) Turbulent Shear-Layer/Shock-Wave Interactions. International Union of Theoretical and Applied Mechanics. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-82770-9_19
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DOI: https://doi.org/10.1007/978-3-642-82770-9_19
Publisher Name: Springer, Berlin, Heidelberg
Print ISBN: 978-3-642-82772-3
Online ISBN: 978-3-642-82770-9
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