Summary
The experimental studies presented in this paper were obtained in T2 wind tunnel on two models equipped with LC 100 D profiles:
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an airfoil with a large chord (C = 400 mm) placed near the lower wall of the test section,
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a swept wing (C = 100 mm; φ = 30° and φ = 45°). Pressure measurements, boundary layer probings and wall visualizations around the separation conditions of the turbulent boundary layer interaction with the shock wave have been done. The turbulent boundary layer separation occurs when the upstream local Mach number, normal to the shock, reaches approximately 1.3.
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References
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© 1986 Springer-Verlag Berlin, Heidelberg
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Mignosi, A., Dor, J.B., Seraudie, A. (1986). Experimental Study of the Boundary-Layer Separation Conditions through a Shock-Wave on Airfoil and Swept Wing. 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_18
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DOI: https://doi.org/10.1007/978-3-642-82770-9_18
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