Summary
Several versions of the k — ω two-equation turbulence model are investigated for super-and hypersonic flows. Furthermore, in order to account for compressibility effects on turbulence, various compressibility corrections are considered in conjunction with the k — ω model. The models are applied to boundary layer flows up to a Mach number of 10, and to a hypersonic compression corner. Finally, the turbulent flow over the X-38 reentry vehicle at a Mach number of 6 and an angle of attack of 40° is investigated. Computed heat loads are compared with experimental data from the Langley Research Center.
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© 2002 Springer-Verlag Berlin Heidelberg
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Weber, C., Behr, R., Weiland, C. (2002). Turbulence Modeling for Reentry-Vehicles. In: Wagner, S., Rist, U., Heinemann, HJ., Hilbig, R. (eds) New Results in Numerical and Experimental Fluid Mechanics III. Notes on Numerical Fluid Mechanics (NNFM), vol 77. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-540-45466-3_14
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DOI: https://doi.org/10.1007/978-3-540-45466-3_14
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