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dc.contributor.authorBello, Raheem Temitopeen_US
dc.date.accessioned2014-03-10T21:17:29Z
dc.date.available2014-03-10T21:17:29Z
dc.date.issued2014-03-10
dc.date.submittedJanuary 2012en_US
dc.identifier.otherDISS-12035en_US
dc.identifier.urihttp://hdl.handle.net/10106/24046
dc.description.abstractIn hypersonic wind tunnel testing, matching the flow enthalpy conditions for the hypersonic air-breathing corridor is of great importance in order to assure the validity of experimental results. The flow enthalpy of the UTA hypersonic shock tunnel is increased by a shock induced detonation driver. The detonation mixture consist of hydrogen and oxygen in stoichiometric quantities ( 2H2+O2  2H2O). Experimental variations of pressure and the volume of the detonation section were performed to characterize the enthalpy limits, and overall performance of the UTA hypersonic shock tunnel. The UTA HST test section is designed for a nominal Mach number of 10. Force balance experiments were performed in the test section during the high enthalpy characterization. Enthalpy measurements were also performed using a type K thermocouple placed in a Fay-Riddell probe within the test section. High enthalpy flows with maximum total temperature of 4393oK, maximum total pressure of 373 atm, and maximum total enthalpy of 5.1 MJ/Kg are achieved in the driven section, with Mach numbers of 8.75 0.25 measured in the test section.en_US
dc.description.sponsorshipWilson, Donald R.en_US
dc.language.isoenen_US
dc.publisherAerospace Engineeringen_US
dc.titleHigh Enthalpy Characterization Of The UTA Hypersonic Shock Tunnelen_US
dc.typeM.Engr.en_US
dc.contributor.committeeChairWilson, Donald R.en_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.Engr.en_US


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