In this paper, the effects of freestream Mach number on the statistics and large-scale structures in compressible turbulent boundary layers are investigated using direct numerical simulations (DNS). DNS of turbulent boundary layers with nominal freestream Mach number ranging from 3 to 8 are performed. The validity of Morkovin's scaling, strong Reynolds analogy, and Walz's equation are assessed. We find that many of the scaling relations used to express compressible boundary layer statistics in terms of incompressible boundary layers still hold for the range of freestream Mach number considered. Compressibility effects are enhanced with increasing freestream Mach number but remain insignificant, and the turbulence dissipation remains primarily solenoidal. Moreover, the variation of near-wall streaks, iso-surface of the swirl strength, and hairpin packets with freestream Mach numbers demonstrates that increasing freestream Mach number decreases the coherency of turbulent structures. © 2010 by L. Duan, I. Beekman and P.M. Marin.
L. Duan et al., "Direct Numerical Simulation Of Hypersonic Turbulent Boundary Layers With Varying Freestream Mach Number," 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, article no. 2010-0353, American Institute of Aeronautics and Astronautics, Jan 2010.
The definitive version is available at https://doi.org/10.2514/6.2010-353
Mechanical and Aerospace Engineering
International Standard Book Number (ISBN)
Article - Conference proceedings
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01 Jan 2010