INFLUENCE OF FREESTREAM REYNOLDS NUMBER ON UNSTEADY REFLECTED NORMAL SHOCKWAVE-BOUNDARY LAYER INTERACTIONS IN SHOCK TUBE EXPERIMENTS

Simple item page
dc.contributor.advisorOzawa, Hiroshi
dc.contributor.authorBicak, Adam
dc.contributor.committeeMemberParthasarathy, Ramkumar
dc.contributor.committeeMemberVedula, Prakash
dc.date.accessioned2024-07-31T19:04:17Z
dc.date.available2024-07-31T19:04:17Z
dc.date.issued2024-08-01
dc.date.manuscript2024-07-23
dc.description.abstractShockwaves can sharply increase the temperature and pressure of a gas in a reliable and near-instantaneous manner, leading to their utility of producing desirable conditions for the study of chemical combustion and high-speed gas dynamics. Shock tubes effectively produce regions of high-pressure, high-temperature gas by generating shockwaves that reflect off of the end of the driven section and form a reflected shockwave. Though the flow conditions after this sequence are typically assumed to be steady, phenomena such as the growth and interaction of the boundary layer with the reflected shockwave cause non-ideal fluctuations in these parameters. The effect of the Reynolds number of the flow behind the incident shockwave on these flow phenomena was studied using a newly built test section added to the shock tube facility of the High-Speed Aerothermodynamics Laboratory at the University of Oklahoma. High-speed schlieren imaging and pointwise pressure measurements were used to assess the reflected normal shockwave/boundary layer interaction (SBLI) and pressure fluctuations present in the flow. It was found that increasing the freestream Reynolds number helped decrease the size of the shockwave bifurcation formed from the SBLI while also reducing the amount of pressure fluctuations in the region behind the reflected shockwave. These trends persisted across experiments performed at three distinct shock Mach numbers.en_US
dc.identifier.urihttps://hdl.handle.net/11244/340547
dc.languageen_USen_US
dc.rightsAttribution 4.0 International*
dc.rights.urihttp://creativecommons.org/licenses/by/4.0/*
dc.subjectEngineering, Aerospace.en_US
dc.subjectshockwaveen_US
dc.subjectboundary layeren_US
dc.subjectshock tubeen_US
dc.thesis.degreeMaster of Scienceen_US
dc.titleINFLUENCE OF FREESTREAM REYNOLDS NUMBER ON UNSTEADY REFLECTED NORMAL SHOCKWAVE-BOUNDARY LAYER INTERACTIONS IN SHOCK TUBE EXPERIMENTSen_US
ou.groupGallogly College of Engineering::School of Aerospace and Mechanical Engineeringen_US
shareok.orcid0009-0009-0266-8948en_US

Files

Original bundle
Now showing 1 - 2 of 2
Thumbnail Image
Name:
2024_Bicak_Adam_Thesis.pdf
Size:
7.19 MB
Format:
Adobe Portable Document Format
Description:
Download
No Thumbnail Available
Name:
2024_Bicak_Adam_Thesis.docx
Size:
12.52 MB
Format:
Microsoft Word XML
Description:
Download
License bundle
Now showing 1 - 1 of 1
No Thumbnail Available
Name:
license.txt
Size:
1.71 KB
Format:
Item-specific license agreed upon to submission
Description:
Download

Collections

OU - Theses