Direct simulation of turbulent supersonic boundary layers by an extended temporal approach

By T. Maeder, Nikolaus A. Adams, L. Kleiser. Journal of Fluid Mechanics, 2001

168 citations recorded by the source corpus.

Subfields: Atmospheric Science, Computational Mechanics

View Paper: https://www.semanticscholar.org/paper/c24c1f2175558792294fbc3bfa6ea2b3b7247544

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Citations in the corpus

Direct numerical simulation of complete transition to turbulence via oblique breakdown at Mach 3 (2011, background): “The TDNS of Maeder et al. (2001), although at the same Mach number, approximates the flow with a considerably higher momentum thickness, i.e. a location farther downstream than in simulations presented in this paper.”
Large-eddy simulation of shock-wave/turbulent-boundary-layer interaction (2006, methodology): “A similar technique called extended temporal direct numerical simulation (ETDNS) is used by Maeder et al. (2001) to investigate turbulent boundary layers at different Mach numbers of M∞ = 3; 4.”
Characterization of coherent vortical structures in a supersonic turbulent boundary layer (2008, background): “The structural features of supersonic wall turbulence were investigated in the studies of Maeder et al. (2001) (at M = 3, 4.5, 6, Reθ ≈ 3000) and Pirozzoli et al. (2004) (at M = 2.”
Direct numerical simulation of compressible turbulent channel flow between adiabatic and isothermal walls (2004, methodology): “The detailed DNS algorithm was presented in Morinishi et al. (2003), and the validity of the present code was proved by comparing our results with those of existing DNS of compressible turbulent channel flow (Coleman et al.”
Direct simulation of the turbulent boundary layer along a compression ramp at M = 3 and Reθ = 1685 (2000, methodology): “A comparable value of Mt has been found in flat-plate boundary layers at M∞ = 4.5 and M∞ = 6 (Maeder et al. 2000).”
A generalized Reynolds analogy for compressible wall-bounded turbulent flows (2013, methodology): “In the literature, |Ru′T ′ | in quasi-adiabatic flows is found to Generalized Reynolds analogy for compressible wall-bounded turbulent flows 413 be approximately 0.6 ∼ 0.9, significantly deviating from unity (Guarini et al. 2000; Maeder et al. 2001; Pirozzoli et al. 2004; Duan et al. 2011).”
Direct numerical simulation of a supersonic turbulent boundary layer at Mach 2.5 (2000, background): “Guo & Adams (1994) and Adams et al. (1998) simulate boundary layers at three Mach numbers M = 3, 4.5 and 6.”
Direct numerical simulation of hypersonic turbulent boundary layers. Part 3. Effect of Mach number (2011, methodology): “(4.4) The improved performance of Huang’s version of the modified Reynolds analogy is also demonstrated by the simulations of Guarini et al. (2000) and Maeder et al. (2001).”
Direct numerical simulation of hypersonic turbulent boundary layers. Part 2. Effect of wall temperature (2010, methodology): “However, in the study of flat-plate boundary layers with Mach numbers 3, 4.5, 6, Maeder et al. (2001) showed that the intrinsic compressibility effects remain small for boundary layers with Mt significantly greater than the threshold.”