Large-scale motions in a supersonic turbulent boundary layer

By Bharathram Ganapathisubramani, N. Clemens, D. Dolling. Journal of Fluid Mechanics, 2006

187 citations recorded by the source corpus.

Subfields: Computational Mechanics, Environmental Engineering, Ocean Engineering

View Paper: https://www.semanticscholar.org/paper/df759b0aaeb8480cfe4ab6602c52e91f04e4a4bf

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Citations in the corpus

Direct numerical simulation of supersonic turbulent boundary layer over a compression ramp (2007, background): “[37] have shown evidence of the existence of very long structures in supersonic boundary layers.”
Reynolds and Mach number effects in compressible turbulent channel flow (2016, background): “[34] at M = 2 seem to suggest substantial increase of the eddy size in both the streamwise and in the spanwise direction with the Mach number, whereas recent DNS [12] at M = 2 support insensitivity on the Mach number, at least for adiabatic boundary layers.”
Flow physics and RANS modelling of oblique shock/turbulent boundary layer interaction (2013, methodology): “By comparison, the same length scale computed by Ganapathisubramani et al. (2006) at y/δ0 = 0.16 was found to be ∼1.51δ0.”
Some physical aspects of shock wave/boundary layer interactions (2009, background): “Structures of very long size have been put in evidence by Adrian et al. [29], Ganapathisubramani et al. [30] in subsonic boundary layers, and by Ganapathisubramani et al. [ 31 ] in supersonic flows.”
Effects of upstream boundary layer on the unsteadiness of shock-induced separation (2006, methodology): “Hou (2003) discusses in detail the measurement of the response time of the PIV seed particles used in this study.”
Three-dimensional instantaneous structure of a shock wave/turbulent boundary layer interaction (2009, methodology): “These results are also consistent with what has been reported in other supersonic boundary layers, such as the range 0.25–0.5δ reported by Ganapathisubramani et al. (2006) at z/δ = 0.16, the range 0.4–0.5δ reported by Spina, Donovan & Smits (1991) using two-point correlations, as well as the DNS…”
Direct numerical simulation of hypersonic turbulent boundary layers. Part 2. Effect of wall temperature (2010, unknown): “For example, Guarini et al. (2000) and Pirozzoli, Grasso & Gatski (2004) performed direct numerical simulations (DNS) of supersonic turbulent boundary layers at Mach 2.”
Low-frequency dynamics of shock-induced separation in a compression ramp interaction (2009, methodology): “These measurements were performed to qualify the upstream boundary layer and to characterize the long coherent structures that were observed in a previous study using low-framing rate PIV (Ganapathisubramani et al. 2006).”
Turbulence in supersonic boundary layers at moderate Reynolds number (2011, background): “Recent measurements of correlations in supersonic boundary layers have been performed at M∞ = 2, Reτ = 5600 by Ganapathisubramani et al. (2006), who analysed velocity signals from probes placed in the outer layer, finding an increasing trend with the wall distance of both the streamwise and the…”
Three-dimensional conditional structure of a high-Reynolds-number turbulent boundary layer (2011, methodology): “patterns of relatively low- and high-speed velocity regions in the logarithmic region of wall-bounded turbulent flows over a wide range of Reynolds and Mach numbers (Ganapathisubramani et al. 2006; Monty et al. 2007; Hutchins & Marusic 2007a).”
High Reynolds number effects in wall turbulence (2010, background): “…of spanwise alternating positive and negative u fluctuations that have been observed in the log and wake regions of wall-bounded turbulent flows (so-called superstructures or VLSM, e.g. Kim & Adrian, 1999; Ganapathisubramani et al., 2006; Hutchins & Marusic, 2007a; Monty et al., 2007, 2009).”