Direct numerical simulation of a supersonic turbulent boundary layer at Mach 2.5

By S. Guarini, Robert D. Moser, Karim Shariff, Alan A. Wray. Journal of Fluid Mechanics, 2000

317 citations recorded by the source corpus.

Subfields: Aerospace Engineering, Computational Mechanics

View Paper: https://www.semanticscholar.org/paper/a07a6f376ba1f01742dc37329c75ce1bd3b94ff8

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Citations in the corpus

Turbulence in supersonic boundary layers at moderate Reynolds number (2011, methodology): “…numerical studies performed in the supersonic regime are based on simplifying assumptions to relate the spatial growth of the boundary layer with its temporal growth in the presence of streamwise periodic boundary conditions (Guarini et al. 2000; Maeder, Adams & Kleiser 2001; Martı́n 2007).”
A generalized Reynolds analogy for compressible wall-bounded turbulent flows (2013, methodology): “Morkovin (1962) assumed that (ρv)′T ′t is much smaller than (ρv) ′T ′ , found to be only approximately valid near the wall (Guarini et al. 2000).”
Characterization of coherent vortical structures in a supersonic turbulent boundary layer (2008, background): “Recent studies include the ‘extended temporal’ simulation of Maeder, Adams & Kleiser (2001), the quasi-periodic simulation of Guarini et al. (2000), and the fully spatial DNS of Pirozzoli, Grasso & Gatski (2004).”
Direct simulation of turbulent supersonic boundary layers by an extended temporal approach (2001, methodology): “Following Guarini et al. (2000), the reference length δc is defined as the lowest z-location at which the van Driest transformed mean velocity ūc (z = δc) is equal to the free-stream value uc∞ , see equation (3.”
Direct numerical simulation of hypersonic turbulent boundary layers. Part 3. Effect of Mach number (2011, methodology): “The check for validity of Morkovin’s hypothesis consists primarily of experiments and numerical simulations at moderate Mach numbers (Fernholz & Finley 1980; Guarini et al. 2000; Pirozzoli, Grasso & Gatski 2004).”
Direct numerical simulation of hypersonic turbulent boundary layers. Part 1. Initialization and comparison with experiments (2007, methodology): “For example, Guarini et al. (2000) perform a DNS of a Mach 2.5 boundary layer at Reθ = 1577; Adams (2000) performs a DNS of the turbulent boundary layer over a compression ramp at Mach 3 and Reθ = 1685; Martin & Candler (2001) perform DNS of turbulent boundary layers at Mach 4 and Reθ = 7225 and 9”
Direct numerical simulation of hypersonic turbulent boundary layers. Part 2. Effect of wall temperature (2010, methodology): “6 for case M5T5, consistent with the DNS of adiabatic turbulent boundary layers given by Guarini et al. (2000) and Martin (2007). Several ‘modified’ forms of the SRA have been proposed to take the heat flux at the wall into account and remove wall-temperature dependence. For example, Cebeci & Smith ”
Large-eddy simulation of low-frequency unsteadiness in a turbulent shock-induced separation bubble (2009, background): “’s DNS [23], we know that the above equation is wrong in general.”
Direct numerical simulation of compressible turbulent channel flow between adiabatic and isothermal walls (2004, methodology): “And Guarini et al. (2000) performed a DNS of the boundary layer flow on an adiabatic wall, using the DNS algorithm based on the B-spline Galerkin method.”
Physics and Measurement of Aero-Optical Effects: Past and Present (2017, background): “…the dominant cause of the aero-optical distortions, numerous experimental (Spina et al. 1994, Smits & Dussauge 1996) and numerical (Gaviglio 1987, Guarini et al. 2000, Duan et al. 2010, Wang & Wang 2013) studies in boundary layers have shown that the time-averaged pressure fluctuations are…”
Direct numerical simulation of transonic shock/boundary layer interaction under conditions of incipient separation (2010, unknown): “…z, t) = v (y) + v′ (0, y, z, t), w (0, y, z, t) = w′ (0, y, z, t), p (0, y, z, t) = p∞, ⎫⎪⎪⎪⎪⎬ ⎪⎪⎪⎪⎭ (2.4) where the mean velocity distribution is prescribed as suggested by Guarini et al. (2000), the pressure is assumed to be uniform and the mean density is determined from the Crocco–Busemann…”