Direct Numerical Simulation of Supersonic Turbulent Boundary Layer with Spanwise Wall Oscillation

Ni, Weidan; Lu, Lipeng; Ribault, Catherine; Jiang, Fang

doi:10.3390/en9030154

Cited by 12 publications

(10 citation statements)

References 52 publications

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“…It is different with the turbulent boundary layer case (Ni et al. 2016), where the effect of the Stokes layer on the mean temperature profiles is mainly limited to the near-wall region, as the time needed for diffusion along the wall direction, before the flow is advected downstream, is not available. Accordingly, under SWO, the mean density at the wall also increases, while is only slightly affected in the core region, where the compressible effect is rather weak.…”

Section: Spanwise Wall Oscillation Atmentioning

confidence: 92%

“…Under SWO, as a consequence of the dissipation of the Stokes layer, a significant increase of the mean temperature first occurs near the wall and then diffuses over the whole channel, particularly for cases with smaller T + (or larger ω + ), as expected. It is different with the turbulent boundary layer case (Ni et al 2016), where the effect of the Stokes layer on the mean temperature profiles is mainly limited to the near-wall region, as the time needed for diffusion along the wall direction, before the flow is advected downstream, is not available. Accordingly, under SWO, the mean density ρ at the wall also increases, while ρ is only slightly affected in the core region, where the compressible effect is rather weak.…”

Section: Mean Density and Temperature Profilesmentioning

confidence: 95%

“…Subsequently, Ni et al. (2016) conducted DNS of the supersonic turbulent boundary layer at a free-stream Mach number of under SWO where they found that, although the velocity and temperature statistics are disturbed differently, the Reynolds analogy is still preserved if the effect of the Stokes layer can be removed properly. Zhe et al.…”

Section: Introductionmentioning

confidence: 99%

“…Fang, Lu & Shao (2010) carried out a large-eddy simulation of CTCF under SWO at M b = 0.5, with emphasis on heat transport and its relationship with momentum transport. Subsequently, Ni et al (2016) conducted DNS of the supersonic turbulent boundary layer at a free-stream Mach number of 2.9 under SWO where they found that, although the velocity and temperature statistics are disturbed differently, the Reynolds analogy is still preserved if the effect of the Stokes layer can be removed properly. Zhe et al (2016) investigated the effects of uniform blowing or suction on the skin friction in hypersonic spatially developing turbulent boundary layers at a free-stream Mach number of 6.…”

Section: Introductionmentioning

confidence: 99%

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Supersonic turbulent boundary layer drag control using spanwise wall oscillation

Yao

Hussain

2019

J. Fluid Mech.

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Spanwise wall oscillation has been extensively studied to explore possible drag control methods, mechanisms and efficacy – particularly for incompressible flows. We performed direct numerical simulation for fully developed turbulent channel flow to establish how effective spanwise wall oscillation is when the flow is compressible and also to document its drag reduction (${\mathcal{D}}{\mathcal{R}}$) trend with Mach number. Drag reduction ${\mathcal{D}}{\mathcal{R}}$ is first investigated for three different bulk Mach numbers $M_{b}=0.3$, $0.8$ and $1.5$ at a fixed bulk Reynolds number $Re_{b}=3000$. At a given velocity amplitude $A^{+}$ ($=12$), ${\mathcal{D}}{\mathcal{R}}$ at $M_{b}=0.3$ agrees with the strictly incompressible case; at $M_{b}=0.8$, ${\mathcal{D}}{\mathcal{R}}$ exhibits a similar trend to that at $M_{b}=0.3$: ${\mathcal{D}}{\mathcal{R}}$ increases with the oscillation period $T^{+}$ to a maximum and then decreases gradually. However, at $M_{b}=1.5$, ${\mathcal{D}}{\mathcal{R}}$ monotonically increases with $T^{+}$. In addition, the maximum ${\mathcal{D}}{\mathcal{R}}$ is found to increase with $M_{b}$. For $M_{b}=1.5$, similar to the incompressible case, ${\mathcal{D}}{\mathcal{R}}$ increases with $A^{+}$, but the rate of increase decreases at larger $A^{+}$. Unlike the flow behaviour when incompressible, the flow surprisingly relaminarizes when it is supersonic (at $A^{+}=18$ and $T^{+}=300$) – this enigmatic behaviour requires further detailed studies for different domain sizes, $Re_{b}$ and $M_{b}$. The Reynolds number effect on ${\mathcal{D}}{\mathcal{R}}$ is also investigated. Although ${\mathcal{D}}{\mathcal{R}}$ generally decreases with $Re_{b}$, it is less affected at small $T^{+}$, but drops rapidly at large $T^{+}$. We introduce a simple scaling for the oscillation period as $T^{\ast }=T_{C}^{+}l_{I}^{+}/l_{C}^{+}$, with $l_{I}^{+}$ and $l_{C}^{+}$ denoting the mean streak spacing for incompressible and compressible cases, respectively. At the same semi-local Reynolds number $Re_{\unicode[STIX]{x1D70F}c}^{\ast }\equiv Re_{\unicode[STIX]{x1D70F}}\sqrt{\overline{\unicode[STIX]{x1D70C}}_{c}/\overline{\unicode[STIX]{x1D70C}}_{w}}/(\overline{\unicode[STIX]{x1D707}}_{c}/\overline{\unicode[STIX]{x1D707}}_{w})$ (subscripts $c$ and $w$ denote quantities at the channel centre and wall, respectively), ${\mathcal{D}}{\mathcal{R}}$ as a function of $T^{\ast }$ exhibits good agreement between the supersonic and strictly incompressible cases, with the optimal oscillation period becoming $M_{b}$-invariant as $T_{opt}^{\ast }\approx 100$.

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Section: Spanwise Wall Oscillation Atmentioning

confidence: 92%

Section: Mean Density and Temperature Profilesmentioning

confidence: 95%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Supersonic turbulent boundary layer drag control using spanwise wall oscillation

Yao

Hussain

2019

J. Fluid Mech.

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“…They reported performance benefits at the highest of their investigated Mach numbers,

M a = 1.5

, accompanied by a monotonic increase of drag reduction with the oscillation period, that partly vanished at a higher Reynolds number. Ni et al [29] applied spanwise wall oscillation to supersonic boundary layer flow via direct numerical simulation (DNS) at Mach number

M a = 2.9

and Reynolds number 16 000 based on values of the incoming free stream flow and the thickness of the turbulent boundary layer at the leading edge of the flat plate. They concluded, that the drag reducing effect of spanwise wall oscillations essentially holds true also for a supersonic boundary layer resulting in an equal suppression of both turbulent momentum and heat transport.…”

Section: Introductionmentioning

confidence: 99%

Active control of compressible channel flow up to Mab=3 using direct numerical simulations with spanwise velocity modulation at the walls

Ruby

Foysi

2022

GAMM-Mitteilungen

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Active turbulence control has been pursued continuously for the last decades, striving for an altered, energetically more favorable flow. In this article, our focus is on a promising method inducing a spanwise wall movement in order to reduce turbulence intensity and hence friction drag, investigated by means of direct numerical simulation. This approach transforms a previously time dependent oscillatory wall motion into a static spatial modulation with prescribed wavelength in the streamwise direction [48]. Most procedures related to turbulence control including the present one have been overwhelmingly applied to incompressible flow. This work is different and novel to the effect, that this control method is applied to compressible, supersonic channel flow up to a bulk Mach number of Ma=3. Due to substantial variations of viscosity, density, and temperature within the near‐wall region in supersonic flow, the impact of the control method is altered compared to solenoidal flow conditions. By creating a data set of different Mach‐/Reynolds numbers and control parameters, knowledge is gained in which way the effectiveness of oscillatory techniques and physical mechanisms change under the influence of compressibility. It is shown that the control method is able to effectively reduce turbulence levels and lead to large drag reduction levels in compressible supersonic flow. Variable property effects even enhance this behavior for the whole set of investigated parameters. Overall, the higher Mach number cases show a larger net power saving compared to the incompressible ones. Furthermore, we observe an increase of the optimum wavelength with increasing Mach number, which helps in guiding optimal implementations of such a control method.

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A High-Order Hybrid Numerical Scheme for Hypersonic Flow Over A Blunt Body

Chen

Fang

Moulinec

et al. 2022

Flow Turbulence Combust

Self Cite

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A hybrid scheme is developed for direct numerical simulations of hypersonic flows over a blunt body. The scheme switches to the first-order AUSMPW+ scheme near the bow shock to provide sufficient dissipation to handle the carbuncle phenomenon. In the smooth part of the computational domain, a sixth-order central scheme with an eighth-order low-pass filter is adopted to provide high spatial accuracy to resolve turbulence. The hybrid scheme is shown to be able to obtain smooth and accurate predictions of laminar hypersonic flows over a blunt body. Using the hybrid scheme, a direct numerical simulation of a Mach 6 hypersonic flow over a circular cylinder is conducted. The result shows the turbulent structures in the near-wall region are well resolved by the hybrid scheme, and the bow shock is also captured without introducing any numerical oscillations. With the boundary layer transition on the cylinder's surface, the simulation indicates that the heat flux peak shifts from the stagnation point to the transitional zone and its peak value is increased by 50%.

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Direct Numerical Simulation of Supersonic Turbulent Boundary Layer with Spanwise Wall Oscillation

Cited by 12 publications

References 52 publications

Supersonic turbulent boundary layer drag control using spanwise wall oscillation

Supersonic turbulent boundary layer drag control using spanwise wall oscillation

Active control of compressible channel flow up to Mab=3 using direct numerical simulations with spanwise velocity modulation at the walls

A High-Order Hybrid Numerical Scheme for Hypersonic Flow Over A Blunt Body

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