Accession Number : ADA137550

Title :   Determination of Boundary Layer Transition and Separation on Double Circular Arc Compressor Blades in a Large Subsonic Cascade.

Descriptive Note : Master's thesis,

Corporate Author : NAVAL POSTGRADUATE SCHOOL MONTEREY CA

Personal Author(s) : McGuire,A G

PDF Url : ADA137550

Report Date : Sep 1983

Pagination or Media Count : 73

Abstract : The china clay technique for flow visualization was used to determine the surface flow on a double circular arc (DCA) compressor blade in large rectilinear subsonic cascade wind tunnel. A calibration experiment using a large flat plate model is also reported which allowed the drying patterns on the DCA blading to be interpreted. Natural transition occured on the flat plate at a Reynolds Number based on transition location of 0.8 million and on the suction surface of the DCA blading at significant negative incidence angles at a Reynolds Number based on transition location of approximately 0.5 million. At incidence angles larger than -3 deg, the DCA blade showed a leading edge separation bubble with turbulent reattachment. (Author)

Descriptors :   *Boundary layer transition, *Compressor blades, *Flow separation, Surfaces, Leading edges, Flow visualization, Clay, Drying, Reynolds number, Angle of incidence, Turbulent flow, Attachment, Suction, Curved profiles, Flat plate models, Subsonic wind tunnels, Cascade structures, Theses

Subject Categories : Fluid Mechanics
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE