Abstract
The interaction between a normal shock wave and a turbulent boundary layer is of great importance for the flow around transonic airfoils because the limits of their performance are influenced by this local occurence very strongly. Often a shock causes flow separation and thereby produces global disturbances of the flow field (e.g. rapid drag rise and buffet onset). Recently, in order to counteract the separation, endeavours were taken to weaken the shock by suction or ventilation. Some of the experimental results are summarized in [1].
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References
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© 1986 Springer-Verlag Berlin, Heidelberg
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Bohning, R., Zierep, J. (1986). Calculation of 2D Turbulent Shock/Boundary-Layer Interaction at Curved Surfaces with Suction and Blowing. 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_9
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DOI: https://doi.org/10.1007/978-3-642-82770-9_9
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