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Numerical investigation of supersonic turbulent boundary layers with high wall temperature

Author:
Guo, Y.
Published:
Dec 1, 1994.
Physical Description:
1 electronic document
Additional Creators:
Adams, N. A.
Online Version

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Summary:
A 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.
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Collection:
NASA Technical Reports Server (NTRS) Collection.
Note:
Document ID: 19950014633.
Accession ID: 95N21050.
Stanford Univ., Studying Turbulence Using Numerical Simulation Databases. 5: Proceedings of the 1994 Summer Program; p 245-267.
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No Copyright.
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