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dc.contributor.advisorMiller, J.A.
dc.contributor.authorKail, Karl Aurel IV
dc.dateSeptember 1977
dc.date.accessioned2012-11-16T19:17:07Z
dc.date.available2012-11-16T19:17:07Z
dc.date.issued1977-09
dc.identifier.urihttp://hdl.handle.net/10945/18320
dc.description.abstractThe large lift coefficient changes attainable with Circulation Control Airfoils through small changes in boundary layer blowing suggest rotary wing cyclic control can be obtained through modulation of the blowing. Static pressure distributions were obtained to assess the unsteady behavior of a Circulation Control Rotor in a two-dimensional flow. A constant-radius hotwire wake traversing mechanism was constructed to augment the pressure data and to study the flow phenomena occurring in the region of Coanda jet separation. Through correlation of turbulence intensity data with the pressure data, it was discovered that the point of Coanda jet separation could be located using the hotwire. The objective of these tests was accordingly expanded to include correlation of the location of separation with flow parameter variation. Although steady flow, steady blowing tests results were favorable, the unsteady blowing test was restricted in scope because of an inability of the injection air compressor to provide an adequate flow, and because the real-time acquisition system was not completed in time for these tests. From mean value and RMS data obtained during oscillatory blowing, no increase in average lift augmentation above that produced in equivalent steady blowing was discernible.
dc.description.urihttp://archive.org/details/unsteadysurfacep1094518320
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.lcshAeronauticsen_US
dc.titleUnsteady surface pressure and near-wake hot-wire measurements of a circulation control airfoil.en_US
dc.typeThesisen_US
dc.contributor.secondreaderSchmidt, Louis V.
dc.contributor.corporateNaval Postgraduate School (U.S.)
dc.contributor.departmentAeronautics
dc.subject.authorcirculation control airfoilen_US
dc.description.serviceLieutenant, United States Navy
etd.thesisdegree.nameDegree of Aeronautical Engineeren_US
etd.thesisdegree.levelProfessional Degreeen_US
etd.thesisdegree.disciplineAeronautical Engineeringen_US
etd.thesisdegree.grantorNaval Postgraduate Schoolen_US
dc.description.distributionstatementApproved for public release; distribution is unlimited.


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