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dc.contributor.authorLeamon, Derek Glennen_US
dc.date.accessioned2013-03-20T19:14:16Z
dc.date.available2013-03-20T19:14:16Z
dc.date.issued2013-03-20
dc.date.submittedJanuary 2012en_US
dc.identifier.otherDISS-11737en_US
dc.identifier.urihttp://hdl.handle.net/10106/11668
dc.description.abstractCharacterization of a hypersonic shock tunnel was performed under low enthalpy conditions. A rake was designed and fabricated to measure pitot pressure and heat flux at three axial locations in the test section. Pitot pressures at three locations provided an indication of the inviscid core. Thin film RTD sensors with a fast response time were fabricated to measure the heat flux under these low enthalpy conditions. The Cook-Felderman algorithm was used to estimate the heat flux from the temperature history. Results for the first millisecond of test time showed a probe tip surface temperature increase of 15-20 K and a calculated heat flux in the inviscid core of 9.93 ± 0.56 W/cm2.en_US
dc.description.sponsorshipLu, Franken_US
dc.language.isoenen_US
dc.publisherAerospace Engineeringen_US
dc.titleCharacterization Of UTA Hypersonic Shock Tunnelen_US
dc.typeM.S.en_US
dc.contributor.committeeChairLu, Franken_US
dc.degree.departmentAerospace Engineeringen_US
dc.degree.disciplineAerospace Engineeringen_US
dc.degree.grantorUniversity of Texas at Arlingtonen_US
dc.degree.levelmastersen_US
dc.degree.nameM.S.en_US


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