Temperature factor effect on the structure of the separated flow within a supersonic gas stream

Neiland, V. Ya.; Sokolov, L. A.; Shvedchenko, Vladimir Viktorovich

doi:10.1134/s0015462808050049

Cited by 7 publications

(16 citation statements)

References 8 publications

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“…In recent years, in several investigations of supersonic and hypersonic shock wave/boundary layer interactions (SBLI) involving large separated regions, numerical studies have shown multiple vortex structures/eddies embedded in the main separation bubble (Smith & Khorrami 1991; Korolev, Gajjar & Ruban 2002; Neiland, Sokolov & Shvedchenko 2008; Shvedchenko 2009). The critical parameter governing the origin and existence of these eddies seems to be the geometric angle , which represents the strength of perturbation to the boundary layer such as a shock wave inducing separation at a compression corner or a shock wave from a wedge incident on a boundary layer growing over a surface such as a flat plate beneath the wedge.…”

Section: Introductionmentioning

confidence: 99%

“…(2002) and Neiland et al. (2008) have shown that large separated regions can be analysed by extending the triple-deck approach.…”

Section: Introductionmentioning

confidence: 99%

“…Further, dependence of such multiple eddies on wall temperature and Reynolds number has recently been investigated by Neiland et al. (2008) and Shvedchenko (2009), Egorov, Neiland & Shvedchenko (2011) and Khraibut et al. (2017) in the context of hypersonic SBLI.…”

Section: Introductionmentioning

confidence: 99%

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Hypersonic compression corner flow with large separated regions

Gai

Khraibut

2019

J. Fluid Mech.

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The structure of large-scale hypersonic boundary layer separation and reattachment is studied numerically using a flat plate/compression corner geometry. Apart from verifying the large scale separation characteristics in hypersonic flow, a detailed discussion of secondary separation and fragmentation into multiple vortices embedded within the main recirculation region is presented. The unique relation between the second minimum in shear stress and the scaled angle is highlighted in the context of the reverse flow singularity of Smith (Proc. R. Soc. Lond. A, vol. A420, 1988, pp. 21–52) and it appears that for a small wall temperature ratio, such a singularity is unlikely. It is shown that the size of the separation can be estimated in terms of Burggraf’s expression based on asymptotic theory.

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Section: Introductionmentioning

confidence: 99%

“…(2002) and Neiland et al. (2008) have shown that large separated regions can be analysed by extending the triple-deck approach.…”

Section: Introductionmentioning

confidence: 99%

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Hypersonic compression corner flow with large separated regions

Gai

Khraibut

2019

J. Fluid Mech.

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“…The nondimensional frequency spectrum at location 4.4 indicates the presence of dominant frequencies with increased magnitude, which could be attributed to the development of the acoustic instabilities. Based on the criteria described in [13,14],…”

Section: A Boundary-layer Transitionmentioning

confidence: 99%

“…The flowfield characteristics over supersonic and hypersonic compression ramps have been discussed in many studies [11][12][13][14][15] involving the evolution of boundary-layer perturbations over a flat plate. The presence of the first mode of instabilities (Tollmien-Schlichting waves) and, in this case especially, second-mode instabilities (of acoustic nature) are known to be dominant and grow in the hypersonic boundary-layer along a flat plate leading up to the corner separation zone [16].…”

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confidence: 99%

Measurement of Flow Perturbation Spectra in Mach 4.5 Corner Separation Zone

et al. 2018

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Characterization of the M 4.5 flow over a flat-plate model with a 30 deg compression ramp was performed with low-enthalpy (T 0 300 K) and high-enthalpy (T 0 800-1250 K) flow conditions for a wide range of unit Reynolds numbers (Re l 4 ⋅ 10 5 − 1 ⋅ 10 7 m −1). Three measurement techniques were employed to measure the frequency spectrum of flow perturbations: a high-frequency Shack-Hartmann wavefront sensor (aerooptical method), highfrequency PCB™ pressure sensors, and a laser differential interferometer. The magnitude and frequency of flow oscillations measured by all three methods provide comprehensive and complementary results in determining spectra of gas disturbances within the flow. Of these measurement methods, the Shack-Hartmann wavefront sensor is shown to be the most suitable tool for analysis of the high-speed flow. Aerooptical measurements detect modification to the flow structure when plasma actuation is employed or when Re l is varied. In this work, flow characterization by the Shack-Hartmann sensor at individual points over the ramp has shown three flow regimes depending on the unit Reynolds number: turbulent, transitional, and laminar. At higher Re l , the freestream disturbances become strong enough to significantly affect the perturbations in the boundary-layer and the separation zone on the compression ramp. Frequency spectrum measurements during high-frequency plasma actuation (F 100 kHz) indicate amplification of the perturbations from the natural state that occur over the separation region.

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Numerical investigation of a Mach 6 hypersonic laminar flow on two-dimensional cold-wall compression corners with controlled surface roughness

Giuseppe

Stemmer

2022

International Journal of Heat and Fluid Flow

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Temperature factor effect on the structure of the separated flow within a supersonic gas stream

Cited by 7 publications

References 8 publications

Hypersonic compression corner flow with large separated regions

Hypersonic compression corner flow with large separated regions

Measurement of Flow Perturbation Spectra in Mach 4.5 Corner Separation Zone

Numerical investigation of a Mach 6 hypersonic laminar flow on two-dimensional cold-wall compression corners with controlled surface roughness

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