Abstract
This flow is one of the classical cases for shock/turbulent boundary layer interactions. In the incoming boundary layer, effects of compressible turbulence are probably very weak. Therefore, the observed evolutions are relevant of incompressible turbulence subjected to a shock wave which causes the plate to separate, inducing a lamdba shock structure at the trailing edge of the profile as seen fig. 1. FIG. 1 — Interferogram in the interaction region
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References
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© 1998 Friedr. Vieweg & Sohn Verlagsgesellschaft mbH, Braunschweig/Wiesbaden
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Loyau, H., Vandromme, D. (1998). Test Case TC5: Two Dimensional Transonic Bump. In: Dervieux, A., Braza, M., Dussauge, JP. (eds) Computation and Comparison of Efficient Turbulence Models for Aeronautics — European Research Project ETMA. Notes on Numerical Fluid Mechanics (NNFM), vol 5. Vieweg+Teubner Verlag, Wiesbaden. https://doi.org/10.1007/978-3-322-89859-3_40
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DOI: https://doi.org/10.1007/978-3-322-89859-3_40
Publisher Name: Vieweg+Teubner Verlag, Wiesbaden
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Online ISBN: 978-3-322-89859-3
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