DNS of a spatially evolving hypersonic turbulent boundary layer at Mach 8

Liang, Xian; Li, Xinliang

doi:10.1007/s11433-013-5102-9

Cited by 31 publications

(29 citation statements)

References 18 publications

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“…And when Mach number is up to 8, the compressibility effects increase with decreasing wall temperature, which has been partly discussed in reference [31].…”

Section: Discussionmentioning

confidence: 99%

“…It has been investigated from different angles [26,31,42]. It is closely related to noise, shocklet and heat flux in hypersonic shear turbulence.…”

Section: Compressibilitymentioning

confidence: 99%

“…Lagha et al [28,29] went further into this kind of research with wall temperature approaching recovery temperature by temporal evolution DNS. Liang [30,31] proposed the DNS results of the spatially evolving boundary layer at Mach 8 over the flat-plate boundary layer.…”

Section: Introductionmentioning

confidence: 99%

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Direct Numerical Simulation on Mach Number and Wall Temperature Effects in the Turbulent Flows of Flat-Plate Boundary Layer

Liang

2014

Commun. Comput. Phys.

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Abstract. In this paper, direct numerical simulation (DNS) is presented for spatially evolving turbulent boundary layer over an isothermal flat-plate at Ma ∞ = 2.25,5,6,8. When Ma ∞ = 8, two cases with the ratio of wall-to-reference temperature T w /T ∞ = 1.9 and 10.03 are considered respectively. The wall temperature approaches recovery temperatures for other cases. The characteristics of compressible turbulent boundary layer (CTBL) affected by freestream Mach number and wall temperature are investigated. It focuses on assessing compressibility effects and the validity of Morkovin's hypothesis through computing and analyzing the mean velocity profile, turbulent intensity, the strong Reynolds analogy (SRA) and possibility density function of dilatation term. The results show that, when the wall temperature approaches recovery temperature, the effects of Mach number on compressibility is insignificant. As a result, the compressibility effect is very weak and the Morkovin's hypothesis is still valid for Mach number even up to 8. However, when Mach number equal to 8, the wall temperature effect on the compressibility is sensitive. In this case, when T w /T ∞ = 1.9, the Morkovin's hypothesis is not fully valid. The validity of classical SRA depends on wall temperature directly. A new modified SRA is proposed to eliminate such negative factor in near wall region. Finally the effects of Mach number and wall temperature on streaks are also studied.

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“…And when Mach number is up to 8, the compressibility effects increase with decreasing wall temperature, which has been partly discussed in reference [31].…”

Section: Discussionmentioning

confidence: 99%

“…It has been investigated from different angles [26,31,42]. It is closely related to noise, shocklet and heat flux in hypersonic shear turbulence.…”

Section: Compressibilitymentioning

confidence: 99%

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Direct Numerical Simulation on Mach Number and Wall Temperature Effects in the Turbulent Flows of Flat-Plate Boundary Layer

Liang

2014

Commun. Comput. Phys.

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“…In the corner region, the streamwise grid spacing is much smaller than that in the upstream flat-plate region to resolve the small scales of STBLI and separation flows. This table shows that the grid resolution in the flat-plate region is fine enough for the simulation of nonseparated flat-plate boundary layer [15][16][17]. To trigger the transition, we impose the blow-and-suction perturbation [13,17,18] on the wall in −305 ≤ x ≤ −285 mm.…”

Section: A Numerical Simulation Setup and Computational Meshesmentioning

confidence: 99%

Numerical Study on Wall Temperature Effects on Shock Wave/Turbulent Boundary-Layer Interaction

Zhu¹,

Yu²,

Tong

et al. 2017

AIAA Journal

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The effect of wall temperature on the size of the separation bubble in the shock wave/turbulent boundary-layer interaction of a 24 deg compression ramp with Mach 2.9 is numerically investigated. The ratios of wall temperature to recovery temperature T w ∕T r are 0.6, 1.14, 1.4, and 2.0, respectively. To validate the simulation, the statistical results with T w ∕T r 1.14 are tested and the results show a good agreement with theoretical and experimental results. It is shown that wall temperature has a remarkable effect on the size of the separation bubble and the size increases significantly with the increase of wall temperature. Through theoretical analysis, combined with numerical results, we get a semitheoretical formula L∕δ ∝ T w ∕T r 0.85 , in which L and δ are the length of the separation bubble and the thickness of upstream boundary layer, respectively. The turbulent kinetic energy budgets are also analyzed based on the numerical data, and results show that turbulence kinetic energy is chiefly produced both in the buffer layer and near the shock wave, and turbulent dissipation is mainly in the center of the separation bubble as well as in the nearwall region. It is also shown that the intrinsic compressibility effect is not significant in all these cases. = separation point δ = upstream boundary-layer thickness μ = viscosity coefficient ρ = density

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“…DNS of supersonic turbulent channel flows have been performed at Mach 1.5 and 3 by Coleman et al (1995) and Huang et al (1995). In order to deeply understand the supersonic turbulence flow, the effect of wall temperature [13][14][15][16], Mach number [17], and high enthalpy [18][19] …”

Section: Introductionmentioning

confidence: 99%

The Effects of Air Vitiation on the Supersonic Turbulent Channel flow using Direct Numerical Simulation

Chen¹,

Li²,

Dou³

2016

52nd AIAA/SAE/ASEE Joint Propulsion Conference

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DNS of a spatially evolving hypersonic turbulent boundary layer at Mach 8

Cited by 31 publications

References 18 publications

Direct Numerical Simulation on Mach Number and Wall Temperature Effects in the Turbulent Flows of Flat-Plate Boundary Layer

Direct Numerical Simulation on Mach Number and Wall Temperature Effects in the Turbulent Flows of Flat-Plate Boundary Layer

Numerical Study on Wall Temperature Effects on Shock Wave/Turbulent Boundary-Layer Interaction

The Effects of Air Vitiation on the Supersonic Turbulent Channel flow using Direct Numerical Simulation

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