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Experimental unsteady pressures on an oscillating cascade with supersonic leading edge locusThe first experimental data for an oscillating cascade with a supersonic leading edge locus (SLEL) at zero stagger angle is presented which were obtained in the NASA/OSU supersonic oscillating cascade facility. Reduced frequencies from .093 to .146, based on half chord were investigated. An influence coefficient technique for a linear oscillating cascade with constant interblade phase angle has been extended to a cascade with a SLEL.
Document ID
19920074233
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Erwin, Daniel (NASA Lewis Research Center Cleveland, OH, United States)
Gregorek, G. M. (Ohio State University Columbus, United States)
Ramsey, John (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 15, 2013
Publication Date
July 1, 1992
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 92-4035
Accession Number
92A56857
Distribution Limits
Public
Copyright
Other

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