Interaction of intersecting shocks with a flat-plate boundary layer in the presence of an entropy layer

Borovoy, V. Ya.; Егоров, И. В.; Mosharov, V. E.; Radchenko, Vladimir; Skuratov, A. S.; Struminskaya, I. V.

doi:10.1134/s0015462813050074

Cited by 3 publications

(2 citation statements)

References 16 publications

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“…At regular §ow, the St m value drops with an increase of bluntness radius r 2 . As noted in [33], the decrease of heat exchange occurs because of the admixture of high-entropy layer to the mixing layer formed on the external boundary of separation zone that leads to the thickening of the mixing layer and to the decrease of gas density in this layer.…”

Section: Influence Of Cowl Bluntness On Heat Transfer and Channel Blomentioning

confidence: 99%

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Influence of leading edge bluntness on hypersonic flow in a generic internal-compression inlet

Borovoy

Егоров

Mosharov

et al. 2015

Progress in Flight Physics – Volume 7

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Flow and heat transfer inside a generic inlet are investigated experimentally. The cross section of the inlet is rectangular. The inlet is installed on a §at plat at a signi¦cant distance from the leading edge. The experiments are performed in TsAGI wind tunnel UT-1M working in the Ludwieg tube mode at Mach number M ∞ = 5 and Reynolds numbers (based on the plate length L = 320 mm) Re ∞L = 23 · 10 6 and 13 · 10 6 . Steady §ow duration is 40 ms. Optical panoramic methods are used for investigation of §ow outside and inside the inlet as well. For this purpose, the cowl and one of two compressing wedges are made of a transparent material. Heat §ux distribution is measured by thin luminescent Temperature Sensitive Paint (TSP). Surface §ow and shear stress visualization is performed by viscous oil containing luminophor particles. The investigation shows that at high contraction ratio of the inlet, an increase of plate or cowl bluntness to some critical value leads to sudden change of the §ow structure.

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Section: Influence Of Cowl Bluntness On Heat Transfer and Channel Blomentioning

confidence: 99%

“…The §ow schemes are based on the experimental data presented below and on the results of [33]. At high area reduction of the inlet (for example, at η = W 0 /W t = 4), two §ow schemes are possible (Fig.…”

Section: Flow Schemesmentioning

confidence: 99%

Influence of leading edge bluntness on hypersonic flow in a generic internal-compression inlet

Borovoy

Егоров

Mosharov

et al. 2015

Progress in Flight Physics – Volume 7

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Leading edge bluntness effect on the flow in a model air-inlet

et al. 2014

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Flow in an idealized air-inlet with plane walls and a rectangular cross-section is experimentally investigated. The air-inlet is mounted on a plate, at a distance well removed from its leading edge. The experiments were conducted in a Ludwig tube at M ∞ = 5 and Re ∞L = 23 × 10 6 and 13 × 10 6 . A panoramic (optical) technique of measuring the heat transfer coefficient is for the first time applied to study the internal flow in an air-inlet. The data on the effect of the bluntness of the leading edges of the plate and the air-inlet cowl on the heat transfer coefficient distribution and the flow structure within the air-inlet are obtained. It is shown that in an air-inlet with large channel constriction an even small bluntness of the plate or the cowl can lead to global changes in the flow structure.

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Entropy Effect in Laminar-Turbulent Transition of the Supersonic Boundary Layer in the Wake of an Isolated Roughness

Chuvakhov

2020

Fluid Dyn

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Interaction of intersecting shocks with a flat-plate boundary layer in the presence of an entropy layer

Cited by 3 publications

References 16 publications

Influence of leading edge bluntness on hypersonic flow in a generic internal-compression inlet

Influence of leading edge bluntness on hypersonic flow in a generic internal-compression inlet

Leading edge bluntness effect on the flow in a model air-inlet

Entropy Effect in Laminar-Turbulent Transition of the Supersonic Boundary Layer in the Wake of an Isolated Roughness

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