Introduction
The three-shock configuration is quite typical for the aircraft internal and external aerodynamics. For example, it appears at supersonic steady free-stream conditions in intakes (Fig. 1, left) and unsteady shock wave reflection from 2D wedges (Fig. 1, right). In the latter case the resulting flow is experimentally proven to be pseudo-stationary, and the triple point trajectory makes the constant angle χ with respect to the 2D wedge surface.
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Gvozdeva, L.G., Borsch, V.L., Gavrenkov, S.A. (2012). Analytical and Numerical Study of Three Shock Configurations with Negative Reflection Angle. In: Kontis, K. (eds) 28th International Symposium on Shock Waves. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-25685-1_89
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DOI: https://doi.org/10.1007/978-3-642-25685-1_89
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