Abstract
Despite the enormous increase in computational capabilities and use of computational fluid dynamics as a design tool in the aircraft industry, the correct prediction of complex hypersonic turbulent flows involving shock wave boundary layer interaction (SWBLI) is still a challenge [1]. Well assessed turbulence models that are known to perform properly at lower speed, cannot be used in hypervelocity flows without a proper validation. In this paper the use of a differential Reynolds Stress Model for the prediction of SWBLI on a compression corner is presented and the results are discussed for attached and separated boundary layers.
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© 2012 Springer-Verlag Berlin Heidelberg
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Bosco, A., Reinartz, B., Müller, S., Brown, L., Boyce, R. (2012). Reynolds Stress Modeling for Hypersonic Flows. In: Oberlack, M., Peinke, J., Talamelli, A., Castillo, L., Hölling, M. (eds) Progress in Turbulence and Wind Energy IV. Springer Proceedings in Physics, vol 141. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-28968-2_23
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DOI: https://doi.org/10.1007/978-3-642-28968-2_23
Publisher Name: Springer, Berlin, Heidelberg
Print ISBN: 978-3-642-28967-5
Online ISBN: 978-3-642-28968-2
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