Effect of the local wall cooling/heating on the hypersonic boundary layer stability and transition

Sidorenko, A. A.; Gromyko, Yu. V.; Bountin, D. A.; Polivanov, P. A.; Маслов, А. А.

doi:10.1051/eucass/201507549

Cited by 15 publications

(5 citation statements)

References 10 publications

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“…For supersonic boundary layers, Masad & Abid (1995) found by N-factor analysis that a heating strip upstream also stabilises by damping the first Mack mode. The experimental work (Sidorenko et al 2015) on a cone at higher Mach number showed that the second Mack mode instability is damped by localised wall cooling. To find the optimal location of a wall heating device, DNS simulations of supersonic flows were carried out.…”

Section: Introductionmentioning

confidence: 99%

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Adjoint-based linear sensitivity of a supersonic boundary layer to steady wall blowing–suction/heating–cooling

Poulain,

Content,

Rigas

et al. 2024

J. Fluid Mech.

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For a Mach $4.5$ flat-plate adiabatic boundary layer, we study the sensitivity of the first, second Mack modes and streaks to steady wall-normal blowing/suction and wall heat flux. The global instabilities are characterised in frequency space with resolvent gains and their gradients with respect to wall-boundary conditions are derived through a Lagrangian-based method. The implementation is performed in the open-source high-order finite-volume code BROADCAST and algorithmic differentiation is used to access the high-order state derivatives of the discretised governing equations. For the second Mack mode, the resolvent optimal gain decreases when suction is applied upstream of Fedorov's mode $S$ /mode $F$ synchronisation point, leading to stabilisation, and the converse when applied downstream. The largest suction gradient is in the region of branch I of mode $S$ neutral curve. For heat-flux control, strong heating at the leading edge stabilises both the first and second Mack modes, the former being more sensitive to wall-temperature control. Streaks are less sensitive to any boundary control in comparison with the Mack modes. Eventually, we show that an optimal actuator consisting of a single steady heating strip located close to the leading edge manages to damp the linear growth of all three instability mechanisms.

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Section: Introductionmentioning

confidence: 99%

“…The experimental work (Sidorenko et al. 2015) on a cone at higher Mach number showed that the second Mack mode instability is damped by localised wall cooling. To find the optimal location of a wall heating device, DNS simulations of supersonic flows were carried out.…”

Section: Introductionmentioning

confidence: 99%

Adjoint-based linear sensitivity of a supersonic boundary layer to steady wall blowing–suction/heating–cooling

Poulain,

Content,

Rigas

et al. 2024

J. Fluid Mech.

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“…The opposite effect was observed for a blunt cone, where heating inhibits the second mode, thus stabilizing the flow, and cooling has the opposite effect. Fedorov et al [24,25] conducted experimental and numerical investigations of a Mach-6 sharp cone boundary layer with local cooling and heating. They found that local cooling delayed the transition and local heating promoted the transition.…”

Section: Introductionmentioning

confidence: 99%

Effect of local wall temperature on hypersonic boundary layer stability and transition

Huang

2023

Chinese Phys. B

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Wall temperature significantly affects the stability and receptivity of the boundary layer. Changing the wall temperature locally may therefore be an effective laminar flow control technique. However, the situation is complicated when the wall temperature distribution is nonuniform, and previous experiments have found that local wall cooling may delay the onset of transition. In this paper, we attempt to clarify the physical mechanisms whereby the local wall temperature affects the transition and the stability of a hypersonic boundary layer. A numerical investigation of the disturbance evolution in a Mach-6 sharp cone boundary layer with local wall heating or cooling is conducted. Direct numerical simulations (DNS) are performed for the single-frequency and broadband disturbance evolution caused by random forcing. We vary the local wall temperature and the location of heating/cooling, and then use the eN method to estimate the transition onset. Our results show that local wall cooling amplifies high-frequency unstable waves while stabilizing low-frequency unstable waves, with local heating amplifying all unstable waves locally. The disturbance amplitude and second-mode peak frequency obtained by DNS agree well with previous experimental results. Local cooling/heating has a dual effect on the stability of the hypersonic boundary layer. For local cooling, while it effectively inhibits the growth of the low-frequency unstable waves that dominate the transition downstream, it also further destabilizes the downstream flow. In addition, while upstream cooling can delay the transition, excessive cooling may promote it; local heating always slightly promotes the transition. Finally, recommendations are given for practical engineering applications based on our results.

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“…The schlieren technique can be used to improve understanding of the laminar turbulent transition. In paper [1], the increase of the boundary layer thickness was used to recognize the turbulent spots. In paper [2], crosscorrelation image analysis was used to ¦nd periodic structures in the boundary layer.…”

Section: Introductionmentioning

confidence: 99%

Evolution of a wave packet to turbulent spot in a boundary layer at high speeds

Polivanov

Gromiko

Bountin

et al. 2017

Progress in Flight Physics

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Hypersonic boundary layer stability and transition were studied experimentally for the test case of 7 degree half-angle cone with various nose bluntness. The experiments were performed for M = 6. Wall pressure pulsations were recorded synchronously with the high-speed schlieren. The combined data processing algorithm for coupling of unsteady pressure sensors with high-speed schlieren images was proposed. Analysis of the wall pressure pulsations evolution reveals that the turbulent spot may arise in di¨erent ways. It was found that for the blunted model, the role of the second mode in origination of the turbulent spot is more evident.

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Effect of the local wall cooling/heating on the hypersonic boundary layer stability and transition

Cited by 15 publications

References 10 publications

Adjoint-based linear sensitivity of a supersonic boundary layer to steady wall blowing–suction/heating–cooling

Adjoint-based linear sensitivity of a supersonic boundary layer to steady wall blowing–suction/heating–cooling

Effect of local wall temperature on hypersonic boundary layer stability and transition

Evolution of a wave packet to turbulent spot in a boundary layer at high speeds

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