Interference heating due to shock wave impingement on laminar boundary layers

Hung, F. T.

doi:10.2514/6.1973-678

Cited by 11 publications

(4 citation statements)

References 4 publications

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“…11, the separation and attachment states both satisfy Eq.9, and the exponent b Sep ≈ b Att ≈ 0.7 are indicated by the tendency. The exponent is in accordance with the laminar/laminar interference of Hung 29 , while the coefficient a Sep = 1.4 > a Att = 1.05 > 1.0. The discrepancy of coefficient may result from the lower estimate of St re f by Eckert's method 45 than measured values, which can be found in Ref.…”

Section: St Pksupporting

confidence: 60%

“…The discrepancy of coefficient may result from the lower estimate of St re f by Eckert's method 45 than measured values, which can be found in Ref. 29 . Larger coefficient of separation states indicates higher peak heat fluxes than that of the attachment states with the same pressure rise.…”

Section: St Pkmentioning

confidence: 93%

“…Thermal protection design requires the severe peak heat flux in the reattachment region of separation states. There are several methods for predicting the peak heat flux 1,2,[27][28][29][42][43][44] , and the peak heat flux is generally correlated with peak pressure rise in these methods. One simple correlation is expressed in the following form 28,29…”

Section: A Wall Shear Stress In the Reversed-flow Regionmentioning

confidence: 99%

“…The peak heat flux in the reattachment region is an important feature of separated flow. Most empirical methods to predict the peak heat flux always correlate it with peak pressure rise 1,2,[27][28][29] . Studies on wall pressure distributions are abundant.…”

Section: Introductionmentioning

confidence: 99%

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Hypersonic curved compression ramp flows with bistable states

Tang,

Wang,

et al. 2021

Preprint

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The bistable states and separation hysteresis in curved compression ramp (CCR) flows, and the corresponding aerothermal characteristics (including wall friction C f , pressure and heat flux St), are studied numerically and theoretically. Direct numerical simulations of separation hysteresis induced by variation of turning angle φ , as well as the influence of inflow Mach number and wall temperature on hysteresis loops, are carried out. Distributions of wall friction, pressure and heat flux are analyzed. Further, emergence of C f 's first and second minima in the separation bubble is interpreted, revealing it is dominated by the adverse pressure gradient (APG) induced by separation and reattachment shocks. The present results and analysis indicate that the reversed-flow singularity of Smith (Proceedings of the Royal Society of London. A. Mathematical and Physical Sciences, 1988, 420: 21-52) is less likely to occur in CCR flows. The prediction of peak pressure p pk of separation states confirms the model based on the minimum viscous dissipation theorem (Physics of Fluids, 2020, 32(10):101702). While the pressure overshoot p os can be analyzed by shock-polars with pressure match of compression and expansion process. The correlation between peak heat flux and peak pressure rise of both separation and attachment states is also discussed in terms of the classical power relations.

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Section: St Pksupporting

confidence: 60%

Section: St Pkmentioning

confidence: 93%

Section: A Wall Shear Stress In the Reversed-flow Regionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Hypersonic curved compression ramp flows with bistable states

Tang,

Wang,

et al. 2021

Preprint

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Heating enhancement caused by a transverse control jet in hypersonic flow

1998

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Reattaching Flow Visualization by Means of Glow Spark in Hypersonic Shock-Wave/Boundary-Layer Interaction

Itoh¹,

Honda²

2010

JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCE

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:The purpose of this study was to examine the structure of reattaching boundary layers downstream of a quasi-two-dimensional compression corner in a gun tunnel at Mach number 10 using a glow spark technique. An analytical model predicted well a location of a high aerodynamic heating region in laminar reattaching boundary layers. An indication of presence of Görtler vortices was found; the vortices may play an important role in the transition. Furthermore, the flow was unsteady and accompanied by a shock wave rippling. The rippling was probably not caused by the vortices, since characteristic length scales of the two phenomena were completely different. A slip line generated due to shock/shock interaction had little effect on the transition, because it was apart from the boundary layer.

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Interference heating due to shock wave impingement on laminar boundary layers

Cited by 11 publications

References 4 publications

Hypersonic curved compression ramp flows with bistable states

Hypersonic curved compression ramp flows with bistable states

Heating enhancement caused by a transverse control jet in hypersonic flow

Reattaching Flow Visualization by Means of Glow Spark in Hypersonic Shock-Wave/Boundary-Layer Interaction

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