Direct numerical simulation of hypersonic turbulent boundary layers. Part 1. Initialization and comparison with experiments

By B. M. P. Martin. Journal of Fluid Mechanics, 2007

226 citations recorded by the source corpus.

Subfields: Applied Mathematics, Computational Mechanics

View Paper: https://www.semanticscholar.org/paper/19cacdf6884d8f5b2390be9adc6e493ba63050c7

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In Applied Mathematics

In Computational Mechanics

Citations in the corpus

Three-dimensional vortex organization in a high-Reynolds-number supersonic turbulent boundary layer (2010, background): “The complete three-dimensional structure of supersonic boundary layers is starting to become available from direct numerical simulation (Martin 2007).”
Coherent structures in direct numerical simulation of turbulent boundary layers at Mach 3 (2007, methodology): “Details regarding the numerical method are provided in Martı́n (2007), which also describes the accuracy of the DNS statistics as compared to theory and experiments.”
Large-eddy simulation of low-frequency unsteadiness in a turbulent shock-induced separation bubble (2009, methodology): “Recently, Martin [ 34 ] obtained good results using the SRA as a mean to initialize the flow in a DNS.”
Breakdown mechanisms and heat transfer overshoot in hypersonic zero pressure gradient boundary layers (2013, methodology): “For the Mach number under study herein, the temporal DNS computations in the work of Martin (2007) and Duan, Beekman & Martin (2010, 2011) are most relevant.”
Direct numerical simulation of hypersonic turbulent boundary layers. Part 3. Effect of Mach number (2011, background): “An essential part of the study of compressible turbulent boundary layers is to check the validity of Morkovin’s hypothesis.”
Direct numerical simulation of complete transition to turbulence via oblique breakdown at Mach 3 (2011, background): “…or early nonlinear stages (Fasel et al. 1993; Chang & Malik 1994; Sandham, Adams & Kleiser 1995; Eissler & Bestek 1996; Fezer & Kloker 1999) or the fully developed turbulent flow (Guarini et al. 2000; Maeder, Adams & Kleiser 2001; Pirozzoli, Grasso & Gatski 2004; Martin 2007; Maekawa et al. 2007).”
Direct numerical simulation of hypersonic turbulent boundary layers. Part 2. Effect of wall temperature (2010, methodology): “Simulation parameters Following Martin (2007), the computational domain size and grid resolution are determined based on the characteristic large length scale δ, and the characteristic small near-wall length scale zτ , respectively.”