Abstract
Unsteady characteristics of shock wave oscillations are one of the most prevalent phenomena occurring in a supersonic diffuser. In such oscillations, significant boundary layer separation leads to a highly unsteady flow field resulting in inlet instability, aircraft buffeting, and aero-structure fatigue. From an engineering point of view, this phenomenon can have a significant impact on performance of supersonic diffusers operating near critical mass flow because of the complex interaction between the boundary layer and many shock waves. This includes a shock-wave/turbulent boundary-layer interaction (SBLI) followed by a subsonic region with an adverse pressure gradient and rapidly thickening boundary layer.
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Prabakar, S.M., Srikanth, C., Muruganandam, T.M. (2017). Effect of Mach Number on Shock Oscillations in Supersonic Diffusers. In: Ben-Dor, G., Sadot, O., Igra, O. (eds) 30th International Symposium on Shock Waves 1. Springer, Cham. https://doi.org/10.1007/978-3-319-46213-4_42
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DOI: https://doi.org/10.1007/978-3-319-46213-4_42
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