Report of tests of a compressor configuration of DCA blading.

dc.contributor.advisorShreeve, Raymond P.
dc.contributor.authorHimes, Stephen J.
dc.contributor.corporateNaval Postgraduate School (U.S.)
dc.contributor.departmentAeronautics
dc.dateJune 1983
dc.date.accessioned2012-11-19T23:59:52Z
dc.date.available2012-11-19T23:59:52Z
dc.date.issued1983-06
dc.description.abstractResults of an experimental program to measure the performance of a compressor stator cascade consisting of 20 DCA blades of chord 5.01 inches, aspect ratio 2.0 and solidity 1.67 under conditions of varying incidence angle and Reynolds number are reported. Flow quality and blade performance data were obtained using pneumatic probe surveys and surface pressure measurements. Changes in Reynolds number in the range of 500,000 to 770,000 did not measurably effect either flow quality or blade performance. Changes in incidence angle over the range -15 to 10 degrees produced generally well behaved blade performance parameters.
dc.description.distributionstatementApproved for public release; distribution is unlimited.
dc.description.funderNAen_US
dc.description.serviceLieutenant Commander, United States Navy
dc.description.urihttp://archive.org/details/reportoftestsofc1094519966
dc.identifier.urihttps://hdl.handle.net/10945/19966
dc.language.isoen_US
dc.publisherMonterey, California. Naval Postgraduate Schoolen_US
dc.rightsThis publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.
dc.subject.authorcascadeen_US
dc.subject.authorDCA bladingen_US
dc.subject.lcshAeronauticsen_US
dc.titleReport of tests of a compressor configuration of DCA blading.en_US
dc.typeThesisen_US
dspace.entity.typePublication
etd.thesisdegree.disciplineAeronautical Engineeringen_US
etd.thesisdegree.grantorNaval Postgraduate Schoolen_US
etd.thesisdegree.levelMastersen_US
etd.thesisdegree.nameM.S. in Aeronautical Engineeringen_US
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