Transition in hypersonic boundary layers

Zhang, Chuanhong; Zhu, Yiding; Chen, Xi; Yuan, Hongyong; Jiang, Wu; Chen, Shiyi; Lee, Cunbiao; Gad‐el‐Hak, Mohamed

doi:10.1063/1.4935019

Cited by 56 publications

(36 citation statements)

References 22 publications

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“…An important mechanism in the transition process, absent in low Mach number flows, is the instability of dilatational, longitudinal waves (Emanuel 1992;Gad-el-Hak 1995), such as second-and higher instability modes, which was first identified based on linear stability analysis of hypersonic boundary layers (Mack 1969). Those modes behave as acoustic waves reflecting between the solid wall and the sonic line in hypersonic boundary layers (Fedorov 2011), and play an increasingly important role as the Mach number increases -as demonstrated in previous studies (Stetson & Kimmel 1992;Bountin, Shiplyuk & Sidorenko 2000;Fujii 2006;Hofferth et al 2013;Zhang, Tang & Lee 2013;Casper, Beresh & Schneider 2014;Sivasubramanian & Fasel 2015;Zhang et al 2015;Zhu et al 2016). Recent investigations of hypersonic boundary layers have indicated the appearance of an additional peak in heat transfer (denoted herein as HS) within the transitional region, as well as a second rapid growth of heat transfer near the end of transition (HT).…”

Section: Introductionmentioning

confidence: 76%

“…The experiments are carried out in a Mach 6 wind tunnel (M6QT) at Peking University (Zhang et al 2013;Tang 2014;Zhang 2014;Zhang et al 2015;Zhu et al 2016), which at present is one of three operational hypersonic quiet wind tunnels in the world (Schneider 2013). The tunnel is of the open-jet configuration with nozzle exit diameter of 160 mm.…”

Section: Facility and Modelmentioning

confidence: 99%

“…2.2. Fast-response surface pressure measurements An array of surface-mounted PCB fast-response sensors is used to evaluate the evolution of instability waves in hypersonic wall-bounded flows (Fujii 2006;Zhang et al 2013Zhang et al , 2015Zhu et al 2016). In this work, PCB 132A31 sensors are flush-mounted along one ray of the model, which is defined as the zero circumferential angle.…”

Section: Facility and Modelmentioning

confidence: 99%

“…Very recently, Zhang et al (2015) and Zhu et al (2016) have conducted twodimensional PIV measurements, combined with PCB sensors, over a 0.26 m long, 5 • half-angle flared cone in the Mach 6 wind tunnel at Peking University. They found that the second-mode instability initially grew fast, reached its maximum and finally decayed to zero along the streamwise direction.…”

Section: Introductionmentioning

confidence: 99%

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Newly identified principle for aerodynamic heating in hypersonic flows

et al. 2018

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Instability evolution in a transitional hypersonic boundary layer and its effects on aerodynamic heating are investigated over a 260 mm long flared cone. Experiments are conducted in a Mach 6 wind tunnel using Rayleigh-scattering flow visualization, fast-response pressure sensors, fluorescent temperature-sensitive paint (TSP) and particle image velocimetry (PIV). Calculations are also performed based on both the parabolized stability equations (PSE) and direct numerical simulations (DNS). Four unit Reynolds numbers are studied, 5.4, 7.6, 9.7 and $11.7\times 10^{6}~\text{m}^{-1}$ . It is found that there exist two peaks of surface-temperature rise along the streamwise direction of the model. The first one (denoted as HS) is at the region where the second-mode instability reaches its maximum value. The second one (denoted as HT) is at the region where the transition is completed. Increasing the unit Reynolds number promotes the second-mode dissipation but increases the strength of local aerodynamic heating at HS. Furthermore, the heat generation rates induced by the dilatation and shear processes (respectively denoted as $w_{\unicode[STIX]{x1D703}}$ and $w_{\unicode[STIX]{x1D714}}$ ) were investigated. The former item includes both the pressure work $w_{\unicode[STIX]{x1D703}1}$ and dilatational viscous dissipation $w_{\unicode[STIX]{x1D703}2}$ . The aerodynamic heating in HS mainly arose from the high-frequency compression and expansion of fluid accompanying the second mode. The dilatation heating, especially $w_{\unicode[STIX]{x1D703}1}$ , was more than five times its shear counterpart. In a limited region, the underestimated $w_{\unicode[STIX]{x1D703}2}$ was also larger than $w_{\unicode[STIX]{x1D714}}$ . As the second-mode waves decay downstream, the low-frequency waves continue to grow, with the consequent shear-induced heating increasing. The latter brings about a second, weaker growth of surface-temperature HT. A theoretical analysis is provided to interpret the temperature distribution resulting from the aerodynamic heating.

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Section: Introductionmentioning

confidence: 76%

Section: Facility and Modelmentioning

confidence: 99%

Section: Facility and Modelmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Newly identified principle for aerodynamic heating in hypersonic flows

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“…A brief version of the present paper-focussing on the experimental observations-appeared in Ref. [69].…”

Section: Acknowledgmentsmentioning

confidence: 99%

Transition in Hypersonic Boundary Layers: Role of Dilatational Waves

et al. 2016

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Transition and turbulence production in a hypersonic boundary layer is investigated in the Mach 6 wind tunnel at Peking University, using Rayleigh-scattering visualization, fast-response pressure measurements, and particle image velocimetry. Detailed analysis of the experimental observations is provided. It is found that, although the second mode is primarily an acoustic wave, it causes the formation of high-frequency vortical waves. Moreover, the second mode interacts strongly with low-frequency waves, which leads to immediate transition to turbulence.freestream velocity, m∕s u = velocity vector, m∕s u = x component of the velocity, m∕s v = y component of the velocity, m∕s w = z component of the velocity, m∕s x = streamwise coordinate along the cone's surface, mm y = coordinate normal to the cone's surface, mm z = transverse coordinate normal to the x-y plane, mm= viscous normal stress, Pa ρ = density, kg∕m 3 τ f = flow time scale, s τ p = particle relaxation time, s Φ = viscous dissipation function per unit volume, kg∕m · s 3 ω = vorticity, 1∕s

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Introduction

Liu¹

2017

Unified Theoretical Foundations of Lift and Drag in Viscous and Compressible External Flows

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Transition in hypersonic boundary layers

Cited by 56 publications

References 22 publications

Newly identified principle for aerodynamic heating in hypersonic flows

Newly identified principle for aerodynamic heating in hypersonic flows

Transition in Hypersonic Boundary Layers: Role of Dilatational Waves

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