Simulation and Modeling of Cold-Wall Hypersonic Turbulent Boundary Layers on Flat Plate

Huang, Juan; Nicholson, Gary L.; Duan, Lian; Choudhari, Meelan M.; Bowersox, Rodney D. W.

doi:10.2514/6.2020-0571

Cited by 24 publications

(14 citation statements)

References 26 publications

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“…The change of sign in v T generates a singularity in the turbulent Prandtl number at the wall-normal location where the peak mean temperature is attained. The value of the turbulent Prandtl number becomes close to 0.50 below the wall-normal location of the singularity, as also observed in recent simulations of hypersonic boundary layers at much lower stagnation enthalpies (Huang et al 2020).…”

Section: Temperature and Density Statisticssupporting

confidence: 85%

Direct numerical simulation of a hypersonic transitional boundary layer at suborbital enthalpies

Renzo

Urzay

2021

J. Fluid Mech.

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Section: Temperature and Density Statisticssupporting

confidence: 85%

Direct numerical simulation of a hypersonic transitional boundary layer at suborbital enthalpies

Renzo

Urzay

2021

J. Fluid Mech.

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“…Furthermore, the domain of application for this assumption has been extended to the hypersonic Mach number regime recently by Duan et al (29). Another recent study by Huang et al (30) suggests that density fluctuations become more significant in high Mach number conditions citing the differences between Reynolds averaged and Favre averaged turbulent shear stress.…”

Section: Density Fluctuation In Compressible Boundary Layermentioning

confidence: 99%

Compressible Boundary Layer Velocity Transformation Based on a Generalized Form of the Total Stress

Lee¹,

Martin²,

Williams³

2021

Preprint

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A new mean velocity transformation for compressible boundary layer flow is derived. We identify the effects of density fluctuations and integrate these effects into the derivation of the transformation. Indepth analysis of compressibility effects from density fluctuations is enabled by direct numerical simulation data existing in the literature and from the CRoCCo laboratory. The compressible and incompressible flow data include wall-cooling, semi-local Reynolds numbers ranging from 800 to 34000 and Mach numbers ranging from subsonic to 12. The role, significance and physical mechanisms connecting density fluctuations to the momentum balance and to the viscous, turbulent and total stresses are presented. Density-fluctuation corrected formulations are derived from these insights. We identify the significant properties that thus-far are neglected in the derivation of velocity transformations: (1) the Mach-invariance of the nearwall momentum balance of the density-fluctuation-corrected total stress, and (2) the Mach-invariance of the relative contributions by the density-fluctuation-corrected viscous and Reynolds stresses to the total stress. The proposed velocity transformation integrates both properties into a single transformation equation and successfully demonstrates a collapsing of all currently considered compressible cases onto to the incompressible law of the wall. Analyses of the log-layer intercept and the slope demonstrate that the transformation parameters are well within the bounds reported for incompressible data. Based on the physics embedded in the two scaling properties, the success of the newly proposed transformation is attributed to considering the effect of the viscous stress, Reynolds stress, mean density and, lastly, density fluctuations, in a single transformation form.

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“…( 4) still shows some disagreements from the ideal universal profiles, as reported in Refs. [27,30,31]. Huang et al [30] performed cooled-wall hypersonic Ma ∞ = 11, 14 turbulent boundary layer simulations and reported an upwards shift of the transformed velocity profiles in the inertial sublayer, compared with that of quasi-adiabatic-wall supersonic boundary layers.…”

Section: Introductionmentioning

confidence: 99%

“…[27,30,31]. Huang et al [30] performed cooled-wall hypersonic Ma ∞ = 11, 14 turbulent boundary layer simulations and reported an upwards shift of the transformed velocity profiles in the inertial sublayer, compared with that of quasi-adiabatic-wall supersonic boundary layers. Volpiani et al [31] also reported the upwards shift in the inertial sublayer of heated-wall hypersonic Ma ∞ = 5 turbulent boundary layers.…”

Section: Introductionmentioning

confidence: 99%

Effects of the semi-local Reynolds number in scaling turbulent statistics for wall heated/cooled supersonic turbulent boundary layers

2021

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Simulation and Modeling of Cold-Wall Hypersonic Turbulent Boundary Layers on Flat Plate

Cited by 24 publications

References 26 publications

Direct numerical simulation of a hypersonic transitional boundary layer at suborbital enthalpies

Direct numerical simulation of a hypersonic transitional boundary layer at suborbital enthalpies

Compressible Boundary Layer Velocity Transformation Based on a Generalized Form of the Total Stress

Effects of the semi-local Reynolds number in scaling turbulent statistics for wall heated/cooled supersonic turbulent boundary layers

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