Visualization of streamline tracing inlet-isolator flows using a planar laser Rayleigh scattering imaging technique

Giovanni DiCristina; Kyungrae Kang; Seung Jin Song; Jong Ho Choi; Hyungrok Do; Seong kyun Im

doi:10.1007/s12650-018-00541-6

Visualization of streamline tracing inlet-isolator flows using a planar laser Rayleigh scattering imaging technique

Giovanni DiCristina, Kyungrae Kang, Seung Jin Song, Jong Ho Choi, Hyungrok Do, Seong kyun Im

School of Mechanical Engineering

Research output: Contribution to journal › Article › peer-review

2 Citations (Scopus)

Abstract

Abstract: Isolator flows downstream of the scoop model inlet were visualized by using a planar laser Rayleigh scattering imaging technique. The scoop model was designed for a cruise Mach number of 6. The isolator flows were visualized for two contraction ratios of the scoop inlet (4 and 5) and various freestream Reynolds number conditions. Two freestream Mach numbers were tested to study the flows at the on-design (Mach number 6) and off-design (Mach number 4.5) conditions. Pseudo-cross-sectional flow structures of the isolator were constructed by using averaged planar images from multiple planar imaging planes. The flow visualization found that there exist curved shockwaves and localized flow separation, and three-dimensional shockwave–boundary layer interaction occurs locally affecting boundary layer growth. The visualization showed that Reynolds number determines the thickness of the boundary layer and the size of eddies. Similar overall flow and shockwave structures were observed for different freestream Mach number and Reynolds number conditions. Differences in shockwave angles, impinging shock location, the size of the core flow, and the size of the flow structure were discussed for various flow conditions. Graphical abstract: [Figure not available: see fulltext.].

Original language	English
Pages (from-to)	359-369
Number of pages	11
Journal	Journal of Visualization
Volume	22
Issue number	2
DOIs	https://doi.org/10.1007/s12650-018-00541-6
Publication status	Published - 2019 Apr 9

Bibliographical note

Funding Information:
Acknowledgements This work was supported by Basic Research Funding of Korean Agency for Defense Development (Project Number: 15-201-502-025), the Ministry of Education of the Republic of Korea and the National Research Foundation of Korea (2015R1C1A1A01052628, 2017R1A4A1015523 (Basic Research Laboratory)). The authors would like to thank Dr. Mark A. Cappelli at Stanford University for loaning equipment for flow visualization and Mr. Graham Johnson for his help on the preparation of the imaging system.

Publisher Copyright:
© 2019, The Visualization Society of Japan.

Keywords

Hypersonic flows
Planar laser Rayleigh scattering
Shockwaves
Streamline tracing inlets
Supersonic flow visualization

ASJC Scopus subject areas

Condensed Matter Physics
Electrical and Electronic Engineering

Access to Document

10.1007/s12650-018-00541-6

Cite this

@article{c71568753fb8447198d566d7902c9972,

title = "Visualization of streamline tracing inlet-isolator flows using a planar laser Rayleigh scattering imaging technique",

abstract = "Abstract: Isolator flows downstream of the scoop model inlet were visualized by using a planar laser Rayleigh scattering imaging technique. The scoop model was designed for a cruise Mach number of 6. The isolator flows were visualized for two contraction ratios of the scoop inlet (4 and 5) and various freestream Reynolds number conditions. Two freestream Mach numbers were tested to study the flows at the on-design (Mach number 6) and off-design (Mach number 4.5) conditions. Pseudo-cross-sectional flow structures of the isolator were constructed by using averaged planar images from multiple planar imaging planes. The flow visualization found that there exist curved shockwaves and localized flow separation, and three-dimensional shockwave–boundary layer interaction occurs locally affecting boundary layer growth. The visualization showed that Reynolds number determines the thickness of the boundary layer and the size of eddies. Similar overall flow and shockwave structures were observed for different freestream Mach number and Reynolds number conditions. Differences in shockwave angles, impinging shock location, the size of the core flow, and the size of the flow structure were discussed for various flow conditions. Graphical abstract: [Figure not available: see fulltext.].",

keywords = "Hypersonic flows, Planar laser Rayleigh scattering, Shockwaves, Streamline tracing inlets, Supersonic flow visualization",

author = "Giovanni DiCristina and Kyungrae Kang and Song, {Seung Jin} and Choi, {Jong Ho} and Hyungrok Do and Im, {Seong kyun}",

note = "Funding Information: Acknowledgements This work was supported by Basic Research Funding of Korean Agency for Defense Development (Project Number: 15-201-502-025), the Ministry of Education of the Republic of Korea and the National Research Foundation of Korea (2015R1C1A1A01052628, 2017R1A4A1015523 (Basic Research Laboratory)). The authors would like to thank Dr. Mark A. Cappelli at Stanford University for loaning equipment for flow visualization and Mr. Graham Johnson for his help on the preparation of the imaging system. Publisher Copyright: {\textcopyright} 2019, The Visualization Society of Japan.",

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doi = "10.1007/s12650-018-00541-6",

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AU - DiCristina, Giovanni

AU - Kang, Kyungrae

AU - Song, Seung Jin

AU - Choi, Jong Ho

AU - Do, Hyungrok

AU - Im, Seong kyun

N1 - Funding Information: Acknowledgements This work was supported by Basic Research Funding of Korean Agency for Defense Development (Project Number: 15-201-502-025), the Ministry of Education of the Republic of Korea and the National Research Foundation of Korea (2015R1C1A1A01052628, 2017R1A4A1015523 (Basic Research Laboratory)). The authors would like to thank Dr. Mark A. Cappelli at Stanford University for loaning equipment for flow visualization and Mr. Graham Johnson for his help on the preparation of the imaging system. Publisher Copyright: © 2019, The Visualization Society of Japan.

PY - 2019/4/9

Y1 - 2019/4/9

N2 - Abstract: Isolator flows downstream of the scoop model inlet were visualized by using a planar laser Rayleigh scattering imaging technique. The scoop model was designed for a cruise Mach number of 6. The isolator flows were visualized for two contraction ratios of the scoop inlet (4 and 5) and various freestream Reynolds number conditions. Two freestream Mach numbers were tested to study the flows at the on-design (Mach number 6) and off-design (Mach number 4.5) conditions. Pseudo-cross-sectional flow structures of the isolator were constructed by using averaged planar images from multiple planar imaging planes. The flow visualization found that there exist curved shockwaves and localized flow separation, and three-dimensional shockwave–boundary layer interaction occurs locally affecting boundary layer growth. The visualization showed that Reynolds number determines the thickness of the boundary layer and the size of eddies. Similar overall flow and shockwave structures were observed for different freestream Mach number and Reynolds number conditions. Differences in shockwave angles, impinging shock location, the size of the core flow, and the size of the flow structure were discussed for various flow conditions. Graphical abstract: [Figure not available: see fulltext.].

AB - Abstract: Isolator flows downstream of the scoop model inlet were visualized by using a planar laser Rayleigh scattering imaging technique. The scoop model was designed for a cruise Mach number of 6. The isolator flows were visualized for two contraction ratios of the scoop inlet (4 and 5) and various freestream Reynolds number conditions. Two freestream Mach numbers were tested to study the flows at the on-design (Mach number 6) and off-design (Mach number 4.5) conditions. Pseudo-cross-sectional flow structures of the isolator were constructed by using averaged planar images from multiple planar imaging planes. The flow visualization found that there exist curved shockwaves and localized flow separation, and three-dimensional shockwave–boundary layer interaction occurs locally affecting boundary layer growth. The visualization showed that Reynolds number determines the thickness of the boundary layer and the size of eddies. Similar overall flow and shockwave structures were observed for different freestream Mach number and Reynolds number conditions. Differences in shockwave angles, impinging shock location, the size of the core flow, and the size of the flow structure were discussed for various flow conditions. Graphical abstract: [Figure not available: see fulltext.].

KW - Hypersonic flows

KW - Planar laser Rayleigh scattering

KW - Shockwaves

KW - Streamline tracing inlets

KW - Supersonic flow visualization

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JF - Journal of Visualization

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ER -

Visualization of streamline tracing inlet-isolator flows using a planar laser Rayleigh scattering imaging technique

Abstract

Bibliographical note

Keywords

ASJC Scopus subject areas

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