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Numerical investigation of supersonic turbulent boundary layers with high wall temperatureA direct numerical approach has been developed to simulate supersonic turbulent boundary layers. The mean flow quantities are obtained by solving the parabolized Reynolds-averaged Navier-Stokes equations (globally). Fluctuating quantities are computed locally with a temporal direct numerical simulation approach, in which nonparallel effects of boundary layers are partially modeled. Preliminary numerical results obtained at the free-stream Mach numbers 3, 4.5, and 6 with hot-wall conditions are presented. Approximately 5 million grid points are used in all three cases. The numerical results indicate that compressibility effects on turbulent kinetic energy, in terms of dilatational dissipation and pressure-dilatation correlation, are small. Due to the hot-wall conditions the results show significant low Reynolds number effects and large streamwise streaks. Further simulations with a bigger computational box or a cold-wall condition are desirable.
Document ID
19950014633
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Guo, Y. (Deutsche Forschungsanstalt fuer Luft- und Raumfahrt Brunswick, Germany)
Adams, N. A. (Stanford Univ. CA., United States)
Date Acquired
September 6, 2013
Publication Date
December 1, 1994
Publication Information
Publication: Stanford Univ., Studying Turbulence Using Numerical Simulation Databases. 5: Proceedings of the 1994 Summer Program
Subject Category
Fluid Mechanics And Heat Transfer
Accession Number
95N21050
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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