High-Speed Pressure-Sensitive Paint Measurements of a Hypersonic Vehicle

dc.contributor.advisorCombs, Christopher S.
dc.contributor.authorElizondo, Valeria Delgado
dc.contributor.committeeMemberPineda, Daniel I.
dc.contributor.committeeMemberBasu, Debashis
dc.date.accessioned2024-02-09T20:50:34Z
dc.date.available2024-02-09T20:50:34Z
dc.date.issued2022
dc.descriptionThis item is available only to currently enrolled UTSA students, faculty or staff. To download, navigate to Log In in the top right-hand corner of this screen, then select Log in with my UTSA ID.
dc.description.abstractSurface pressure measurements are essential to evaluate aerodynamic loads on a vehicle during flight. Pressure-sensitive paint (PSP) is an optical experimental technique that is widely used in the aerodynamics field due to its capability to acquire pressure measurements with high spatial and temporal resolution . A fast-responding pressure sensitive paint (fast-PSP) was applied to a 5.7% scale, 3D printed model of the AFRL Initial Concept 3.X (IC3X) hypersonic vehicle at the UTSA Mach 7 Ludwieg Tube Wind Tunnel. A ruthenium-based Polymer/ceramic PSP (PC-PSP) was selected for this hypersonic application. Images of the model under steady conditions at M = 7.2 ± 0.2 flow were collected with a high-speed camera at 20k fps. A static calibration was performed to relate the luminescent emission of the paint to pressure over the range of 82.7 kPa to 0.386 kPa. An average surface pressure distribution of the model was obtained at both 0 and 2.5 AoA. Proper orthogonal decomposition (POD) analysis was done to characterize the structures that make up the pressure fields of this hypersonic vehicle. In addition, Schlieren images were collected to visualize flow structures and conical shock analysis was conducted to compare theoretical and experimental measurements. Other results such as power spectral density (PSD) and PSP derived pressures at various locations within the surface of the vehicle are presented. Details on the paint application methods and image processing techniques are provided. This work presents preliminary quantitative pressure measurements that will contribute as training data to aerothermodynamic machine learning models that are being developed as part of NASA's ULI Full Airframe Sensing Technology (FAST) project.
dc.description.departmentMechanical Engineering
dc.format.extent137 pages
dc.format.mimetypeapplication/pdf
dc.identifier.isbn9798358491441
dc.identifier.urihttps://hdl.handle.net/20.500.12588/3402
dc.languageen
dc.subjectFast PSP
dc.subjectHypersonic Research
dc.subjectHypersonic Wind Tunnel Testing
dc.subjectPC PSP
dc.subjectPorous PSP
dc.subjectPressure Sensitive Paint
dc.subject.classificationAerospace engineering
dc.subject.classificationMechanical engineering
dc.subject.classificationFluid mechanics
dc.titleHigh-Speed Pressure-Sensitive Paint Measurements of a Hypersonic Vehicle
dc.typeThesis
dc.type.dcmiText
dcterms.accessRightspq_closed
thesis.degree.departmentMechanical Engineering
thesis.degree.grantorUniversity of Texas at San Antonio
thesis.degree.levelMasters
thesis.degree.nameMaster of Science

Files

Original bundle

Now showing 1 - 1 of 1
No Thumbnail Available
Name:
DelgadoElizondo_utsa_1283M_13819.pdf
Size:
5.02 MB
Format:
Adobe Portable Document Format