Visualizing supersonic inlet duct unstart using planar laser Rayleigh scattering

Do, Hyungrok; Im, Seong Kyun; Mungal, M. G.; Cappelli, Mark A.

doi:10.1007/s00348-010-1028-4

Cited by 73 publications

(17 citation statements)

References 21 publications

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“…By raising a mechanical flap located downstream of the isolator, unstart was triggered in experiments [13] and [14]. Do et al [15] investigated the unstart phenomena initiated by jet injection downstream of an inlet/isolator in a Mach 5 wind-tunnel.…”

mentioning

confidence: 99%

Numerical investigation on shock train control and applications in a scramjet engine

Xing

Ruan

Huang

et al. 2017

Aerospace Science and Technology

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mentioning

confidence: 99%

Numerical investigation on shock train control and applications in a scramjet engine

Xing

Ruan

Huang

et al. 2017

Aerospace Science and Technology

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“…Their numerical results are in good agreement with the buzz oscillation frequency and amplitude in their own experimental results [16, 17]. Many studies have been performed on unstart problems for hypersonic inlet cases as well [19–24]. However, it is hard to find a numerical study that accurately predicts the oscillation frequency and amplitude in an unstarted hypersonic inlet [8–9, 21].…”

Section: Introductionmentioning

confidence: 74%

“…In a hypersonic inlet, the processes of the buzz phenomenon can be categorized into the generation of the high-pressure zone in the isolator, the existence of backflow due to the adverse pressure gradient, the reduction in the isolator pressure and the inlet restart [8, 19–20]. In the previous section, it was shown that the main cause of the discrepancy between the present results and the experimental results was the prevention of flow leakage and pressure reduction within the inlet due to the limited computational domain.…”

Section: Resultsmentioning

confidence: 99%

Numerical study on the start and unstart phenomena in a scramjet inlet-isolator model

Lee

Kang

2019

PLoS ONE

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Inlet unstart and buzz in scramjet engines must be prevented for the stable operation of the engines. In the present study, the characteristics of the inlet start, unstart and buzz phenomena in a scramjet engine inlet model are investigated using numerical analysis with the RANS-based OpenFOAM solver. The results for the inlet start case with a small computational domain that includes only the inlet-isolator part are in good agreement with existing numerical and experimental results. However, for the inlet unstart case, the computational domain must be wide enough to consider the interactions between the upstream of the inlet and the internal flow of the inlet to predict the inlet unstart and buzz phenomena in the inlet test model. The present results show fairly good agreement with existing experimental results with the buzz phenomenon. The effects of boundary layer profiles on the buzz oscillation frequency and amplitude are also addressed.

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“…Planar laser Rayleigh scattering (PLRS) of condensed CO 2 is a relatively simple but powerful technique capable of visualizing detailed supersonic flow structures in low temperature environments [30,31]. It offers several advantages when compared to the classical supersonic visualization techniques such as shadowgraph and schlieren.…”

Section: Planar Laser Rayleigh Scatteringmentioning

confidence: 99%

Development and testing of the ACT-1 experimental facility for hypersonic combustion research

Baccarella

Liu

Passaro

et al. 2016

Meas. Sci. Technol.

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PAPERDevelopment and testing of the ACT-1 experimental facility for hypersonic combustion research Manuscript version: Accepted Manuscript Accepted Manuscript is "the version of the article accepted for publication including all changes made as a result of the peer review process, and which may also include the addition to the article by IOP Publishing of a header, an article ID, a cover sheet and/or an 'Accepted Manuscript' watermark, but excluding any other editing, typesetting or other changes made by IOP Publishing and/or its licensors" This Accepted Manuscript is © © 2016 IOP Publishing Ltd.During the embargo period (the 12 month period from the publication of the Version of Record of this article), the Accepted Manuscript is fully protected by copyright and cannot be reused or reposted elsewhere. As the Version of Record of this article is going to be / has been published on a subscription basis, this Accepted Manuscript is available for reuse under a CC BY-NC-ND 3.0 licence after the 12 month embargo period.After the embargo period, everyone is permitted to use copy and redistribute this article for non-commercial purposes only, provided that they adhere to all the terms of the licence https://creativecommons.org/licences/by-nc-nd/3.0 Although reasonable endeavours have been taken to obtain all necessary permissions from third parties to include their copyrighted content within this article, their full citation and copyright line may not be present in this Accepted Manuscript version. Before using any content from this article, please refer to the Version of Record on IOPscience once published for full citation and copyright details, as permissions will likely be required. All third party content is fully copyright protected, unless specifically stated otherwise in the figure caption in the Version of Record.View the article online for updates and enhancements. Abstract.A new pulsed-arc-heated hypersonic wind tunnel facility, designated as ACT-1 (Arc-heated Combustion Test-rig 1), has been developed and built at the University of Notre Dame in collaboration with the University of Illinois at Urbana-Champaign and Alta S.p.A. The aim of the design is to provide a suitable test platform for experimental studies on supersonic and hypersonic turbulent combustion phenomena. ACT-1 is composed of a high temperature gas-generator system and a model scramjet combustor that is installed in an open-type vacuum test section of the wind tunnel facility. The gasgenerator is designed to produce high-enthalpy (stagnation temperature = 2,000 K -3,500 K) hypersonic flows for a run time up to 1 second. The supersonic combustor section is composed of a compression ramp (scramjet inlet), an internal flow channel of constant cross-section, a fuel jet nozzle, and a flame holder (wall cavity). The facility allows three-way optical accesses (top and sides) into the supersonic combustor to enable various advanced optical and laser diagnostics. In particular, planar laser Rayleigh scattering (PLRS), high-speed schlieren imaging and...

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Visualizing supersonic inlet duct unstart using planar laser Rayleigh scattering

Cited by 73 publications

References 21 publications

Numerical investigation on shock train control and applications in a scramjet engine

Numerical investigation on shock train control and applications in a scramjet engine

Numerical study on the start and unstart phenomena in a scramjet inlet-isolator model

Development and testing of the ACT-1 experimental facility for hypersonic combustion research

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