A relaxation method for the solution of rotational transonic nozzle flow

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dc.contributor.authorBrecht, Thoralfen
dc.contributor.committeechairBrown, Eugene F.en
dc.contributor.committeememberO'Brien, Walter F. Jr.en
dc.contributor.committeememberMoses, Hal L.en
dc.contributor.departmentMechanical Engineeringen
dc.date.accessioned2014-03-14T21:37:14Zen
dc.date.adate2010-06-08en
dc.date.available2014-03-14T21:37:14Zen
dc.date.issued1975-08-05en
dc.date.rdate2010-06-08en
dc.date.sdate2010-06-08en
dc.description.abstractThis work was successful in demonstrating the feasibility, accuracy, and importance of including the effects of total pressure gradients in evaluating propulsion nozzle performance. In fact, in the cases considered here inlet flow nonuniformities produced effects greater than those which resulted from a consideration of just the two-dimensionality of the flow. For the hyperbolic nozzle and the turbofan bypass nozzle, two-dimensional effects were found to produce a reduction in discharge coefficient of only 0.1 to 0.6%. Whereas, nonuniform inlet flow effects produced an additional decrease in the discharge coefficient of about 1%. Agreement with the solutions of Oswatitsch and Rothstein (18) and Wehofer and Moger (6) is good. However, available experimental data does not provide conclusive proof of the program's accuracy. It is expected that more test data will soon be available from tests conducted by Wehofer and Matz at the Arnold Engineering Development Center. Also, more experimental data is available for nozzles with subsonic exhausts and for convergent nozzles (2). When, as recommended in the next section, the capability of handling subsonic exit flow and convergent nozzles is incorporated into the program, further comparison to experimental data will be possible.en
dc.description.degreeMaster of Scienceen
dc.format.extent55 leavesen
dc.format.mediumBTDen
dc.format.mimetypeapplication/pdfen
dc.identifier.otheretd-06082010-020207en
dc.identifier.sourceurlhttp://scholar.lib.vt.edu/theses/available/etd-06082010-020207/en
dc.identifier.urihttp://hdl.handle.net/10919/42932en
dc.publisherVirginia Techen
dc.relation.haspartLD5655.V855_1975.B74.pdfen
dc.relation.isformatofOCLC# 39010860en
dc.rightsIn Copyrighten
dc.rights.urihttp://rightsstatements.org/vocab/InC/1.0/en
dc.subjecttotal pressure gradientsen
dc.subject.lccLD5655.V855 1975.B74en
dc.titleA relaxation method for the solution of rotational transonic nozzle flowen
dc.typeThesisen
dc.type.dcmitypeTexten
thesis.degree.disciplineMechanical Engineeringen
thesis.degree.grantorVirginia Polytechnic Institute and State Universityen
thesis.degree.levelmastersen
thesis.degree.nameMaster of Scienceen

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