Effect of Concave Wall Geometry on Heat Transfer in Hypersonic Boundary Layers

Flaherty, William; Austin, Joanna

doi:10.2514/6.2010-4986

Cited by 6 publications

(4 citation statements)

References 22 publications

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“…Flaherty and Austin [17] investigated the growth of the wall-heat transfer in laminar boundary layers over curved surfaces and ramps at 𝑀 ∞ = 5.1. The heat transfer increased more over the curved surfaces than on the ramps and the data collapsed well when plotted versus the turning angle of the plate.…”

Section: B Flows Over Simple Concave Wallsmentioning

confidence: 99%

Görtler Instability and Transition in Compressible Flows

Xu,

Ricco,

Duan

2024

AIAA Journal

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We present a discussion on theoretical, experimental, and computational research studies on Görtler instability and the related transition to turbulence occurring in compressible boundary layers over concave surfaces. We first examine the theoretical results on primary and secondary instabilities, emphasizing the role of receptivity, the mechanism by which external agents, such as freestream fluctuations or wall roughness, act on a boundary layer to trigger Görtler vortices. We review experimental findings obtained from measurements in supersonic and hypersonic wind tunnels and discuss studies employing numerical methods, focusing on the direct numerical simulation approach. The research in these two last sections is surveyed according to the geometrical configuration, from simple concave walls to more complex surfaces of hypersonic vehicles. The experimental investigations have been successful in the visualizations of Görtler vortices, in the measurement of the wall-heat transfer in the transitional region, and in the computation of the Görtler-vortex growth rates, although detailed boundary-layer velocity measurements are still missing. Direct numerical simulations have confirmed instability results emerging from stability theories and revealed nonlinear interactions between Görtler vortices and other disturbances. The established initial-boundary-value receptivity theory can certainly benefit from more advanced experimental measurements, and receptivity results should be used in combination with direct numerical simulations. A major conclusion of our review is therefore that the understanding of Görtler vortices should be pursued by a combined methodology including theoretical analysis based on the receptivity formalism, direct numerical simulation, and experiments. Highly desirable outcomes of such endeavor are the prediction of the location and extension of the transition region, and a model for the transition process. We finally highlight further prospects and challenges on fundamental and applied research on Görtler instability and transition in compressible flows.

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Section: B Flows Over Simple Concave Wallsmentioning

confidence: 99%

Görtler Instability and Transition in Compressible Flows

Xu,

Ricco,

Duan

2024

AIAA Journal

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“…The highest value of heat transfer coefficient for the sharp fin was 2.5 times higher, compared to nearby undisturbed region values, and 2.0 times higher for the blunt fin, also compared to nearby undisturbed region values. Flaherty and Austin [44] investigated effects of concave geometry within a Mach 5.2 flow, produced in a shock tube, using two curved models with 16 and 25 degree turning angles, as well as a flat plate and a linear ramp for baseline comparisons. Concave wall geometries were of interest in hypersonic flight because they were employed in inward turning inlets.…”

Section: Interactions Which Included Thermal Transport and Convectivementioning

confidence: 99%

Recent investigations of shock wave effects and interactions

et al. 2020

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Despite over fifty years of research on shock wave boundary layer effects and interactions, many related technical issues continue to be controversial and debated. The present survey provides an overview of the present state of knowledge on such effects and interactions, including discussions of: (i) general features of shock wave interactions, (ii) test section configurations for investigation of shock wave boundary layer interactions, (iii) origins and sources of unsteadiness associated with the interaction region, (iv) interactions which included thermal transport and convective heat transfer, and (v) shock wave interaction control investigations. Of particular interest are origins and sources of low-frequency, large-scale shock wave unsteadiness, flow physics of shock wave boundary layer interactions, and overall structure of different types of interactions. Information is also provided in regard to shock wave investigations, where heat transfer and thermal transport were important. Also considered are investigations of shock wave interaction control strategies, which overall, indicate that no single shock wave control strategy is available, which may be successfully applied to different shock wave arrangements, over a wide range of Mach numbers. Overall, the survey highlights the need for additional understanding of fundamental transport mechanisms, as related to shock waves, which are applicable to turbomachinery, aerospace, and aeronautical academic disciplines.

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“…After the gages were verified and the effect of three-dimensionality had been investigated, the study concentrated on obtaining comparative measurements between the models in the Air-4 condition [54,55]. The flat plate was chosen as the baseline for this comparison as it was a relatively simple flow field with the available analytical solutions already discussed.…”

Section: Laminar and Tripped Boundary Layers Over A Baseline Flat Plamentioning

confidence: 99%

Yip-08 Hypervelocity Boundary Layer Studies for Axisymmetric Engine Flowpaths

Austin¹,

Flaherty²

2011

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Effect of Concave Wall Geometry on Heat Transfer in Hypersonic Boundary Layers

Cited by 6 publications

References 22 publications

Görtler Instability and Transition in Compressible Flows

Görtler Instability and Transition in Compressible Flows

Recent investigations of shock wave effects and interactions

Yip-08 Hypervelocity Boundary Layer Studies for Axisymmetric Engine Flowpaths

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