Experimental Investigation of Impinging Shock – Cavity Interactions with Upstream Transverse Jet Injection

Zare‐Behtash, Hossein; Lo, Kin Hing; Ukai, Takahiro; Kontis, Konstantinos; Obayashi, Shigeru

doi:10.2322/tastj.12.pe_57

Cited by 4 publications

(4 citation statements)

References 22 publications

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“…The same wind tunnel was also employed in a wide range of supersonic flow related studies [15,23,24,25,27,28,29,30,31,32,33]. The test section of the wind tunnel has dimensions of 485.5 mm (length) × 150 mm (width) × 216.5 mm (height).…”

Section: Methodsmentioning

confidence: 99%

Static and Wind-on Performance of Polymer-Based Pressure-Sensitive Paints Using Platinum and Ruthenium as the Luminophore

Kontis

2016

Sensors

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An experimental study has been conducted to investigate the static and wind-on performance of two in-house-developed polymer-based pressure-sensitive paints. Platinum tetrakis (pentafluorophenyl) porphyrin and tris-bathophenanthroline ruthenium II are used as the luminophores of these two polymer-based pressure-sensitive paints. The pressure and temperature sensitivity and the photo-degradation rate of these two pressure-sensitive paints have been investigated. In the wind tunnel test, it was observed that the normalised intensity ratio of both polymer-based pressure-sensitive paints being studied decreases with increasing the number of wind tunnel runs. The exact reason that leads to the occurrence of this phenomenon is unclear, but it is deduced that the luminophore is either removed or deactivated by the incoming flow during a wind tunnel test.

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Section: Methodsmentioning

confidence: 99%

Static and Wind-on Performance of Polymer-Based Pressure-Sensitive Paints Using Platinum and Ruthenium as the Luminophore

Kontis

2016

Sensors

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“…A Topler’s z-type Schlieren photography setup was employed. It should be noted that the same setup was also employed by Yang et al ( 2012b ), Lo ( 2014 ), Lo and Kontis ( 2015 ), Lo et al ( 2013 , 2015 , 2016 ), and Ukai et al ( 2014a , b ). Illumination was provided by a 450 W arc-lamp light source.…”

Section: Experimental Setup and Flow Diagnosticsmentioning

confidence: 93%

“…The same wind tunnel was previously employed in a wide range of transonic and supersonic aerodynamic related studies. The details of this wind tunnel can be found in Lo ( 2014 ), Lo and Kontis ( 2015 , 2016 ), Lo et al ( 2013 , 2015 , 2016 ), Zare-behtash et al ( 2014 , 2015 , 2016 ), and Ukai et al ( 2014a , b ). Therefore, only a brief description on this wind tunnel facility is provided here.…”

Section: Experimental Setup and Flow Diagnosticsmentioning

confidence: 99%

“…All of these windows are made of quartz. The wind tunnel has a stable runtime of 6 s (Lo and Kontis 2016 ; Lo et al 2013 , 2015 , 2016 ; Zare-Behtash et al 2014 , 2015 , 2016 ; Ukai et al 2014a , b ). Under the same initial conditions, the variation of the free-stream Mach number ( M ∞ ) is about M ∞ = 1.3 ± 0.1.…”

Section: Experimental Setup and Flow Diagnosticsmentioning

confidence: 99%

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Flow visualisation of a normal shock impinging over a rounded contour bump in a Mach 1.3 free-stream

Kontis

2016

J Vis

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An experimental study has been conducted to visualise the instantaneous streamwise and spanwise flow patterns of a normal shock wave impinging over a rounded contour bump in a Mach 1.3 free-stream. A quartz-made transparent shock generator was used, so that instantaneous images could be captured during the oil-flow visualisation experiments. Fluorescent oil with three different colours was used in the surface oil-flow visualisation experiment to enhance the visualisation of flow mixing and complicated flow features that present in the flow field. Experimental data showed that the rounded contour bump could split the impinging normal shock wave into a or a series of lambda-shaped shock wave structure(s). In addition, it was found that the flow pattern and the shock wave structures that appeared over the rounded contour bump depended highly on the impinging location of the normal shock wave. The flow pattern shown in this study agreed with the findings documented in literature. Moreover, it was observed from the instantaneous oil streaks that the normal shock impinging location also affected the size and the formation location of the spanwise counter-rotating vortices downstream of the bump crest. Finally, it was concluded that the terminating shock could distort the oil streaks that left over the surface of the contour bump. Therefore, the use of the transparent normal shock wave generator is recommended when conducting experiments with normal shock wave impingement involved.Graphical abstract

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Spray characteristics of a liquid fuel jet in a tandem backward-facing step cavity in supersonic flow

Zhou

Cai

et al. 2023

Aerospace Science and Technology

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Experimental Investigation of Impinging Shock – Cavity Interactions with Upstream Transverse Jet Injection

Cited by 4 publications

References 22 publications

Static and Wind-on Performance of Polymer-Based Pressure-Sensitive Paints Using Platinum and Ruthenium as the Luminophore

Static and Wind-on Performance of Polymer-Based Pressure-Sensitive Paints Using Platinum and Ruthenium as the Luminophore

Flow visualisation of a normal shock impinging over a rounded contour bump in a Mach 1.3 free-stream

Spray characteristics of a liquid fuel jet in a tandem backward-facing step cavity in supersonic flow

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