Direct numerical simulations of a supersonic turbulent boundary layer subject to velocity-temperature coupled control

Liu, Qiang; Luo, Zhenbing; Tu, Guohua; Deng, Xiong; Cheng, Pan; Zhang, Panfeng

doi:10.1103/physrevfluids.6.044603

Cited by 8 publications

(7 citation statements)

References 45 publications

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“…(2021), and similarly to the FIK relation, has been used to quantify the effects of control methodologies on skin friction generation in supersonic turbulent boundary layers by Liu et al. (2021). The RD relation was also used as an explanation to relate enhanced turbulent energy production during transition to the increase in skin friction above the turbulent correlation in the region populated by turbulent spots (Marxen & Zaki 2019).…”

Section: Introductionmentioning

confidence: 99%

“…The RD relation has been extended to compressible flows by Li et al (2019), and has been used to analyse skin friction dynamical contributions in both incompressible and compressible zero-pressure-gradient (ZPG) turbulent boundary layers (Fan, Li & Pirozzoli 2019), as well as incompressible adverse-pressure-gradient turbulent boundary layers (Fan et al 2020). Furthermore, the RD relation was used to quantify the effects of finite-rate chemistry in hypersonic turbulent boundary layers by Passiatore et al (2021), and similarly to the FIK relation, has been used to quantify the effects of control methodologies on skin friction generation in supersonic turbulent boundary layers by Liu et al (2021). The RD relation was also used as an explanation to relate enhanced turbulent energy production during transition to the increase in skin friction above the turbulent correlation in the region populated by turbulent spots (Marxen & Zaki 2019).…”

Section: Introductionmentioning

confidence: 99%

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On the enhancement of boundary layer skin friction by turbulence: an angular momentum approach

Elnahhas

Johnson

2022

J. Fluid Mech.

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Turbulence enhances the wall shear stress in boundary layers, significantly increasing the drag on streamlined bodies. Other flow features such as free stream pressure gradients and streamwise boundary layer growth also strongly influence the local skin friction. In this paper, an angular momentum integral (AMI) equation is introduced to quantify these effects by representing them as torques that alter the shape of the mean velocity profile. This approach uniquely isolates the skin friction of a Blasius boundary layer in a single term that depends only on the Reynolds number most relevant to the flow's engineering context, so that other torques are interpreted as augmentations relative to the laminar case having the same Reynolds number. The AMI equation for external flows shares this key property with the so-called FIK relation for internal flows (Fukagata et al., Phys. Fluids, vol. 14, 2002, pp. L73–L76). Without a geometrically imposed boundary layer thickness, the length scale in the Reynolds number for the AMI equation may be chosen freely. After a brief demonstration using Falkner–Skan boundary layers, the AMI equation is applied as a diagnostic tool on four transitional and turbulent boundary layer direct numerical simulation datasets. Regions of negative wall-normal velocity are shown to play a key role in limiting the peak skin friction during the late stages of transition, and the relative strengths of terms in the AMI equation become independent of the transition mechanism a very short distance into the fully turbulent regime. The AMI equation establishes an intuitive, extensible framework for interpreting the impact of turbulence and flow control strategies on boundary layer skin friction.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

On the enhancement of boundary layer skin friction by turbulence: an angular momentum approach

Elnahhas

Johnson

2022

J. Fluid Mech.

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“…than that of wall blowing, indicating that the control efficiency of heated wall blowing is not as good as that of simple wall blowing, which is different with the conclusions in reference [27]. This may be because, under the condition of hypersonic incoming flow and high wall temperature ratio, the energy consumption required to achieve the heated wall blowing is much higher than that under the supersonic condition.…”

Section: Effect On Skin Friction Coefficientsmentioning

confidence: 57%

“…Similarly, the turbulence intensities in the three directions all increase to varying degrees, indicating that the turbulence amplification effect still exists in the controlled flow field. The maximum turbulence intensities in the streamwise, wall-normal and spanwise directions in B1H1 are increased by 4.06%, 11.02% and 10.25%, respectively, all lower than the growth amplitude under supersonic flow conditions [27]. This means that under the condition of hypersonic flow, the turbulence amplification effect caused by the flow control method is lower than that under the condition of supersonic freestream, for which the compressibility effect in the hypersonic flow field is stronger.…”

Section: Turbulence Statistics Characteristicsmentioning

confidence: 87%

“…To achieve a better drag reduction effect, breaking through the defects of a single flow control technique and developing a new turbulence drag reduction method combining multiple means will become a research hotspot. Recently, the author proposed a novel velocity-temperature coupled control method using wall heating blowing, which had been applied on supersonic TBLs [26,27]. This method couples the advantages of traditional wall blowing and wall heating control.…”

Section: Introductionmentioning

confidence: 99%

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On the drag reduction mechanism of hypersonic turbulent boundary layers subject to heated wall blowing

et al. 2023

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Turbulence drag reduction is of great significance for the range increase of hypersonic flight vehicles. The proposed velocity-temperature coupling control method (Liu et al, Phys Rev Fluids 6:044603, 2021) is further extended to the hypersonic turbulent boundary layer. Direct numerical simulation results of four comparative cases show that the heated wall blowing achieves a drag reduction rate of 10.58%, which is about the sum of wall blowing (5.27%) and wall heating (6.35%). By evaluating the control efficiency, however, it is found that heated wall blowing is not as good as wall blowing and cannot obtain net energy saving rate. The modified FIK decompositions of skin friction coefficient indicate that the cliffy decrease of the mean convection term is the primary contribution for the drag reduction. Effects of the proposed control measure on turbulence statistics and coherent structures are also analyzed. Streamwise vortex is found to be away from the wall, thus leading to a lower friction drag.

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Flow structures and unsteadiness in hypersonic shock wave/turbulent boundary layer interaction subject to steady jet

Liu,

Xie,

Luo

et al. 2023

Acta Mech. Sin.

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Direct numerical simulations of a supersonic turbulent boundary layer subject to velocity-temperature coupled control

Cited by 8 publications

References 45 publications

On the enhancement of boundary layer skin friction by turbulence: an angular momentum approach

On the enhancement of boundary layer skin friction by turbulence: an angular momentum approach

On the drag reduction mechanism of hypersonic turbulent boundary layers subject to heated wall blowing

Flow structures and unsteadiness in hypersonic shock wave/turbulent boundary layer interaction subject to steady jet

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