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dc.contributor.advisorShreeve, Raymond P.
dc.contributor.authorCollins, Christopher C.
dc.date.accessioned2013-02-15T23:33:24Z
dc.date.available2013-02-15T23:33:24Z
dc.date.issued1991-03
dc.identifier.urihttp://hdl.handle.net/10945/28460
dc.descriptionApproved for public release; distribution is unlimiteden_US
dc.description.abstractA two-dimensional, two-passage simulation of the relative flow through a transonic fan at M = 1.4 was designed with a view to providing an apparatus in which to assess the effectiveness of passive vortex generator techniques in alleviating shock-boundary layer interaction effects. The design of the model and the results of six tests in the transonic cascade blowdown wind tunnel are described. Schlieren photographs of the shock structure were obtained at back pressures lower than the design value. The back-pressure control valve was identified as being critical to completing the experimental simulation. The flow through the cascade geometry was computed at design pressure ratio using an Euler code. Modifications to the grid are recommended before thin-layer Navier-Stokes calculations are performed.en_US
dc.description.urihttp://archive.org/details/preliminaryinves00coll
dc.format.extent117 p.;28 cm.en_US
dc.language.isoen_US
dc.publisherMonterey, California. Naval Postgraduate Schoolen_US
dc.titlePreliminary investigation of the shock-boundary layer interaction in a simulated fan passage.en_US
dc.typeThesisen_US
dc.contributor.secondreaderHobson, Garth
dc.contributor.secondreaderEkaterinaris, John
dc.contributor.corporateNaval Postgraduate School
dc.contributor.schoolNaval Postgraduate School
dc.description.serviceLieutenant , United States Navyen_US
etd.thesisdegree.nameDegree of Aeronautical and Astronautical Engineeren_US
etd.thesisdegree.grantorNaval Postgraduate Schoolen_US


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