Direct simulation of the turbulent boundary layer along a compression ramp at M = 3 and Reθ = 1685

By Nikolaus A. Adams. Journal of Fluid Mechanics, 2000

284 citations recorded by the source corpus.

Subfields: Aerospace Engineering, Computational Mechanics

View Paper: https://www.semanticscholar.org/paper/4e5ea6b993e1ca8b5b28a4ac5037f578270cf318

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In Aerospace Engineering

In Computational Mechanics

Citations in the corpus

Direct numerical simulation of hypersonic turbulent boundary layers. Part 1. Initialization and comparison with experiments (2007, methodology): “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 9480 with different wall temperatures; Xu & Martin (2003, 2004) s”
Direct numerical simulation of transonic shock/boundary layer interaction under conditions of incipient separation (2010, background): “…amplification of Reynolds stresses in the APG region, especially in the mixing layer, where the shedding of vortical structures occurs, as also found by Délery (1983), and for supersonic interactions by Adams (2000), Pirozzoli & Grasso (2006), Wu & Martin (2007) and Touber & Sandham (2009).”
Advances in CFD prediction of shock wave turbulent boundary layer interactions (2003, methodology): “Table 5: Details of Computations Reference Type Grid SA TA Adams[90, 91, 44] DNS 1000×180×80 5th 3rd Rizzetta et al[92] DNS 421×151×81 6th 2nd LES-S 421×151×81 6th 2nd LES-D 421×151×81 6th 2nd Stolz et al [93] LES 334× 91× 31 6th 3rd Advances in CFD Prediction of Shock Wave Turbulent Boundary Layer ”
Critical Hypersonic Aerothermodynamic Phenomena (2006, background): “However, the computer requirements for such a simulation over realistic vehicles at flight Reynolds numbers make DNS impractical for the foreseeable future, although DNS predictions for simplified geometries are being carried out currently (see, for example, Adams 2000 and Martin 2004).”
Analysis of unsteady behaviour in shockwave turbulent boundary layer interaction (2012, background): “In accordance with previous numerical studies (Adams 2000; Loginov et al. 2006; Wu & Martin 2007), the interaction of the shock with the boundary layer produces an amplification of the Reynolds stresses past the interaction zone, which can be associated with the generation of a mixing layer above…”
Formulation of the k-w Turbulence Model Revisited (2008, background): “Adams [55] found this oscillation in a direct numerical simulation of a Mach 3 compression-corner flow.”
Large-eddy simulation of low-frequency unsteadiness in a turbulent shock-induced separation bubble (2009, methodology): “Similarly, for his compression-ramp DNS, Adams [2] used a precursor flat plate DNS where a bypasstransition technique was used.”
Unsteady effects of strong shock-wave/boundary-layer interaction at high Reynolds number (2017, methodology): “In contrast to previous low Reynolds numerical studies (Adams 2000; Touber & Sandham 2009; Priebe & Martín 2012; Pasquariello et al. 2014), our filtered signal shows the well-known intermittent character typically observed in high Reynolds number experiments, that is, the wall-pressure jumps from…”
Numerical Methods for High-Speed Flows (2011, methodology): “In the original formulation of Godunov (1959), piece-wise constant reconstructions were assumed, leading to the general first-order flux f̂j+1/2 = R(vj , vj+1).”
Large-eddy simulation of shock-wave/turbulent-boundary-layer interaction (2006, methodology): “No agreement was found with the results of Adams (2000) in terms of skin-friction and surface-pressure distributions in the interaction area.”