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 | |
| Publication status | Published - 2019 Apr 9 |
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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
Cite this
Visualization of streamline tracing inlet-isolator flows using a planar laser Rayleigh scattering imaging technique. / DiCristina, Giovanni; Kang, Kyungrae; Song, Seung Jin; Choi, Jong Ho; Do, Hyungrok; Im, Seong Kyun.
In: Journal of Visualization, Vol. 22, No. 2, 09.04.2019, p. 359-369.Research output: Contribution to journal › Article
}
TY - JOUR
T1 - Visualization of streamline tracing inlet-isolator flows using a planar laser Rayleigh scattering imaging technique
AU - DiCristina, Giovanni
AU - Kang, Kyungrae
AU - Song, Seung Jin
AU - Choi, Jong Ho
AU - Do, Hyungrok
AU - Im, Seong Kyun
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
UR - http://www.scopus.com/inward/record.url?scp=85061314679&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=85061314679&partnerID=8YFLogxK
U2 - 10.1007/s12650-018-00541-6
DO - 10.1007/s12650-018-00541-6
M3 - Article
VL - 22
SP - 359
EP - 369
JO - Journal of Visualization
JF - Journal of Visualization
SN - 1343-8875
IS - 2
ER -