Nonlinear Instability Characterization of Hypersonic Laminar Boundary Layer

Xiong, Youde; Yu, Tao; Lin, Liquan; Zhao, Jiaquan; Wu, Jie

doi:10.2514/1.j059263

Cited by 28 publications

(6 citation statements)

References 46 publications

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“…The experiment was conducted in the Φ0.25 m double-throat Ludwieg tube wind tunnel at Huazhong University of Science and Technology. Detailed descriptions of wind tunnels can be found in [31].…”

Section: Experimental Methods and Designmentioning

confidence: 99%

Experimental study on surface arc plasma actuation-based hypersonic boundary layer transition flow control

Yang¹,

Liang²,

Guo³

et al. 2022

Plasma Sci. Technol.

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Effective control of hypersonic transition is essential. In order to avoid affecting the structural profile of the aircraft, reduce power consumption and electromagnetic interference, the experiment of low-frequency surface arc plasma disturbance to promote hypersonic transition was carried out in the Φ0.25m double-throat Ludwieg tube wind tunnel of Huazhong University of Science and Technology. The contacting PCB sensors and non-contact focused laser differential interferometry testing technology (FLDI) are used in combination. Experimental results show that the low-frequency surface arc plasma actuation has obvious stimulation effects on the second mode unstable wave and can promote boundary layer transition by changing the spectral characteristics of the second mode unstable wave. At the same time, the plasma actuation can promote the energy exchange between the second mode unstable wave and other unstable waves. Finally, the corresponding control mechanism is discussed preliminarily.

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Section: Experimental Methods and Designmentioning

confidence: 99%

Experimental study on surface arc plasma actuation-based hypersonic boundary layer transition flow control

Yang¹,

Liang²,

Guo³

et al. 2022

Plasma Sci. Technol.

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“…Most importantly, as a non-contact optical measurement method, FLDI can provide information on the development of disturbances within the wavy zone, where surface pressure sensors cannot be used. Recently, Xiong et al (2020) used FLDI to conduct a stability experiment for the boundary layer in a hypersonic wind tunnel of Mach 6. The results showed that FLDI captured successfully the second-mode instability wave and its harmonic wave.…”

Section: Experimental Apparatusmentioning

confidence: 99%

“…Recently, Xiong et al. (2020) used FLDI to conduct a stability experiment for the boundary layer in a hypersonic wind tunnel of Mach 6. The results showed that FLDI captured successfully the second-mode instability wave and its harmonic wave.…”

Section: Experimental Set-up and Numerical Settingmentioning

confidence: 99%

Instability evolution in the hypersonic boundary layer over a wavy wall

Zhu

Lee

et al. 2022

J. Fluid Mech.

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The effects of a wavy wall on the stability of a hypersonic boundary layer on a flared cone are investigated by detailed experimental measurements and direct numerical simulations. The non-contact optical measurement method of focused laser differential interferometry is used to measure the disturbance development within the wavy region. The measurement results show that the second mode for the wavy wall is suppressed significantly compared with the smooth wall, and that multiple disturbances at low frequencies appear within the wavy region. Numerical corroboration against experimental measurements reveals good quantitative agreement. It is found that the disturbances at $f=360$ kHz on the wavy wall are suppressed appreciably, which are very significant on the smooth wall. And the disturbances at $f=140$ kHz and $f=260$ kHz develop within the wavy region, and increase considerably. Also, the disturbances achieve a significant increase over the first half of a wavy trough and become more stable over the second half of a wavy trough. The physical mechanism is found to be due to the change in wall geometry and is attributed to the spatially modulated mean flow. The disturbance growth rate is closely related to the level of the mean-flow distortion.

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“…In addition to conventional ones such as the Görtler secondary instability (Ren & Fu 2015;Chen, Huang & Lee 2019) and first-mode oblique breakdown (Mayer, Wernz & Fasel 2007;Guo et al 2022b), new breakdown scenarios involving these low-frequency components are possible. For example, a 20-30 kHz component was pronounced and even dominant on a flared cone in the Peking University Mach 6 quiet wind tunnel (Zhu et al 2016;Xiong et al 2020). To address this problem, Chen, Zhu & Lee (2017) employed the nonlinear parabolised stability equation (NPSE) to revisit the interaction between the low-frequency and the second mode, and indicated the possibility of combination resonance.…”

Section: Introductionmentioning

confidence: 99%

“…2016; Xiong et al . 2020). To address this problem, Chen, Zhu & Lee (2017) employed the nonlinear parabolised stability equation (NPSE) to revisit the interaction between the low-frequency and the second mode, and indicated the possibility of combination resonance.…”

Section: Introductionmentioning

confidence: 99%

Interaction and breakdown induced by multiple optimal disturbances in hypersonic boundary layer

Guo,

Hao,

Wen

2023

J. Fluid Mech.

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The present paper finds that the coexistence of multiple primary instability waves may cause a non-trivial nonlinear interaction and breakdown process, which has not been reported before. In the considered Mach 6 flat-plate boundary layer, a global resolvent analysis reports three optimal disturbances (local maxima): a high-frequency planar wave, a low-frequency oblique wave and a stationary streak. For the dominant planar and oblique waves, a parabolised stability equation analysis identifies the initial non-modal transient growth and downstream modal growth. Initiated by these two optimal disturbances jointly, the complete linear and nonlinear instability processes until breakdown to turbulence are shown with direct numerical simulation. Owing to the transient growth, the oblique wave may be more significant than the planar wave in the breakdown. The oblique wave and scales of nonlinear interactions are pronounced in the outer layer, whose significance may not be comprehensively characterised by the wall pressure measurement. Fourier modes characterising the oblique-wave oblique breakdown, the planar-wave fundamental resonance, the planar-wave subharmonic resonance and the combination resonance related to a detuned mode are observed successively. The detuned mode seems to dominate the near-wall dynamics in the late nonlinear stage, characterised by $\varLambda$ -like structures. Meanwhile, the existence of this detuned mode is independent of the initial amplitude ratio and the absolute amplitude of the oblique and planar waves. Weakly nonlinear stability analyses demonstrate that the detuned mode is mainly a consequence of the secondary instability under the combination of planar and oblique primary waves. Wave vector plots reveal the resonant state of multiple triads. Energy budget and amplitude-correction analyses provide a clear physical image of energy transfer.

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Nonlinear Instability Characterization of Hypersonic Laminar Boundary Layer

Cited by 28 publications

References 46 publications

Experimental study on surface arc plasma actuation-based hypersonic boundary layer transition flow control

Experimental study on surface arc plasma actuation-based hypersonic boundary layer transition flow control

Instability evolution in the hypersonic boundary layer over a wavy wall

Interaction and breakdown induced by multiple optimal disturbances in hypersonic boundary layer

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