Determination of Boundary Layer Transition and Separation on Double Circular Arc Compressor Blades in a Large Subsonic Cascade.
NAVAL POSTGRADUATE SCHOOL MONTEREY CA
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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
- Fluid Mechanics
- Jet and Gas Turbine Engines