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dc.contributor.authorHylton, Michael Ronnieen_US
dc.date.accessioned2014-03-14T20:41:20Z
dc.date.available2014-03-14T20:41:20Z
dc.date.issued2008-07-09en_US
dc.identifier.otheretd-07112008-182200en_US
dc.identifier.urihttp://hdl.handle.net/10919/33969
dc.description.abstractAn innovative experimental facility was developed for testing flush-mounted, diffusing serpentine inlets intended for use on blended-wing-body aircraft. The static ground test facility was able to simulate the boundary layer profile expected to be ingested by inlets mounted on the aft sections of these aircraft. It generated Mach numbers ranging from 0.19 to 0.4 and boundary layer thicknesses between 36% and 45%. The circumferential distortions at the aerodynamic interface plane of the serpentine inlet were also calculated, and ranged between 0.0042 for the lowest Mach number, to 0.0098 for the highest Mach number. Reynolds numbers for the tests ranged between 1.2 million and 2.4 million depending on engine speed and Mach number. The results of the experiment were compared to a previous NASA report, and showed close agreement in distortion patterns and pressure losses at a Mach number of 0.25.en_US
dc.publisherVirginia Techen_US
dc.relation.haspart19840005426_1984005426.pdfen_US
dc.relation.haspartPermission_Florea_UTRC.pdfen_US
dc.relation.haspartFS-1997-07-24-LaRC.pdfen_US
dc.relation.haspartHYLTON_THESIS.pdfen_US
dc.relation.haspart19940017118_1994017118-NP.pdfen_US
dc.rightsI hereby certify that, if appropriate, I have obtained and attached hereto a written permission statement from the owner(s) of each third party copyrighted matter to be included in my thesis, dissertation, or project report, allowing distribution as specified below. I certify that the version I submitted is the same as that approved by my advisory committee. I hereby grant to Virginia Tech or its agents the non-exclusive license to archive and make accessible, under the conditions specified below, my thesis, dissertation, or project report in whole or in part in all forms of media, now or hereafter known. I retain all other ownership rights to the copyright of the thesis, dissertation or project report. I also retain the right to use in future works (such as articles or books) all or part of this thesis, dissertation, or project report.en_US
dc.subjectBoundary-Layer-Ingestingen_US
dc.subjectBlended-Wing-Bodyen_US
dc.subjectAerodynamic Interface Planeen_US
dc.subjectSerpentine Inleten_US
dc.subjectDistortionen_US
dc.titleAssessment of an Innovative Experimental Facility for Testing Diffusing Serpentine Inlets with Large Amounts of Boundary Layer Ingestionen_US
dc.typeThesisen_US
dc.contributor.departmentMechanical Engineeringen_US
dc.description.degreeMaster of Scienceen_US
thesis.degree.nameMaster of Scienceen_US
thesis.degree.levelmastersen_US
thesis.degree.grantorVirginia Polytechnic Institute and State Universityen_US
thesis.degree.disciplineMechanical Engineeringen_US
dc.contributor.committeememberDancey, Clinton L.en_US
dc.identifier.sourceurlhttp://scholar.lib.vt.edu/theses/available/etd-07112008-182200/en_US
dc.contributor.committeecochairO'Brien, Walter F. Jr.en_US
dc.contributor.committeecochairNg, Faien_US
dc.date.sdate2008-07-11en_US
dc.date.rdate2010-12-22
dc.date.adate2008-08-04en_US


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