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Comparison of Theoretical and Experimental Unsteady Aerodynamics of Linear Oscillating Cascade With Supersonic Leading-Edge LocusAn experimental influence coefficient technique was used to obtain unsteady aerodynamic influence coefficients and, consequently, unsteady pressures for a cascade of symmetric airfoils oscillating in pitch about mid-chord. Stagger angles of 0 deg and 10 deg were investigated for a cascade with a gap-to-chord ratio of 0.417 operating at an axial Mach number of 1.9, resulting in a supersonic leading-edge locus. Reduced frequencies ranged from 0.056 to 0.2. The influence coefficients obtained determine the unsteady pressures for any interblade phase angle. The unsteady pressures were compared with those predicted by several algorithms for interblade phase angles of 0 deg and 180 deg.
Document ID
20040082334
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Ramsey, John K.
(NASA Glenn Research Center Cleveland, OH, United States)
Erwin, Dan
(Ohio State Univ. Columbus, OH, United States)
Date Acquired
September 7, 2013
Publication Date
June 1, 2004
Subject Category
Aerodynamics
Report/Patent Number
E-13512
NASA/TM-2004-211820
Funding Number(s)
WBS: WBS 22-297-10-06
PROJECT: RTOP 297-10-00
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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