Heat transport mechanisms of low Mach number turbulent channel flow with spanwise wall oscillation

Fang, Jian; Lü, Lei; Shao, Lei

doi:10.1007/s10409-010-0343-6

Cited by 8 publications

(4 citation statements)

References 28 publications

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Section: Introductionmentioning

confidence: 99%

“…Gomez, Flutet & Sagaut (2009), by extending the FIK identity (Fukagata, Iwamoto & Kasagi 2002) to compressible flow, demonstrated that the dominant contributor to the skin friction is still the Reynolds shear stress and that the small difference from the incompressible flow comes from the variable dynamic viscosity. 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.…”

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: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Supersonic turbulent boundary layer drag control using spanwise wall oscillation

Yao

Hussain

2019

J. Fluid Mech.

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“…Consequently, Case P150A20, although the maximum DR is realized, has the WHF increased by nearly 250% due to the massive dissipation induced by the spanwise Stokes shear layer. However, for the cases with lower frequency and smaller amplitude (T`ě 100 and Wm ď 3), a reduction of WHF can still be acquired, mainly because of the combined effects of the suppression of turbulence transport and the reduction of the shear of streamwise velocity [18,19]. About 2% maximum WHF reduction can be attained for tò sc " 150 and Wm " 3 comparing with 5% WHF reduction obtained in the Mach = 0.5 channel flow [18].…”

Section: Drag and Wall Heat Fluxmentioning

confidence: 92%

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

Ribault

et al. 2016

Energies

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Direct numerical simulations (DNS) of Mach = 2.9 supersonic turbulent boundary layers with spanwise wall oscillation (SWO) are conducted to investigate the turbulent heat transport mechanism and its relation with the turbulent momentum transport. The turbulent coherent structures are suppressed by SWO and the drag is reduced. Although the velocity and temperature statistics are disturbed by SWO differently, the turbulence transports of momentum and heat are simultaneously suppressed. The Reynolds analogy and the strong Reynolds analogy are also preserved in all the controlled flows, proving the consistent mechanisms of momentum transport and heat transport in the turbulent boundary layer with SWO. Despite the extra dissipation and heat induced by SWO, a net wall heat flux reduction can be achieved with the proper selected SWO parameters. The consistent mechanism of momentum and heat transports supports the application of turbulent drag reduction technologies to wall heat flux controls in high-speed vehicles.

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“…Research showed that through appropriate parameter optimization, partial active deformation can improve the aerodynamic characteristics of airfoil. Based on direct numerical simulation, Huang et al (2004) studied the turbulent channel flow on the wall with spanwise periodic motion. The studies showed that by changing the amplitude and vibration period, the wall friction resistance can be reduced obviously.…”

Section: Introductionmentioning

confidence: 99%

Numerical analysis of shock characteristics control based on bump

Wang

et al. 2023

Fluid Dyn. Res.

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The effects of bump control on shock aerodynamic characteristics have been investigated by simulations. A bump control that based on the changes of local upper surface of 2D airfoil or 3D wing model has been used to affect the shock intensity and position. The simulation results are close of other experiment when the calculate parameters are the same. The simulations show that the drag and lift characteristics can be improved with the bump control, and the results of improvement strongly depend on control parameters. For the two-dimensional RAE2822 airfoil, the optimal control position of the bump control must be close to the position of the shock wave. The 3D local bump that located on 80% wing span wise and closed to tip can acquire a batter control results for the 3D RAE2822 wing model.

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Heat transport mechanisms of low Mach number turbulent channel flow with spanwise wall oscillation

Cited by 8 publications

References 28 publications

Supersonic turbulent boundary layer drag control using spanwise wall oscillation

Supersonic turbulent boundary layer drag control using spanwise wall oscillation

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

Numerical analysis of shock characteristics control based on bump

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