The application of flow control to shock wave / boundary layer interactions (SBLIs) has been widely studied in recent decades. Two important practical applications for shock control technology are transonic wings (Fig. 1) and supersonic engine inlets (Fig. 2). In both cases the overall performance is significantly affected by shock wave / boundary layer interactions and it is hoped that flow control can provide considerable benefits.
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Babinsky, H., Ogawa, H. (2009). SBLI control for wings and inlets. In: Hannemann, K., Seiler, F. (eds) Shock Waves. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-540-85168-4_7
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DOI: https://doi.org/10.1007/978-3-540-85168-4_7
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