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Interactive-Boundary-Layer Computations For Oscillating AirfoilInteractive-boundary-layer method developed for computations of steady flow, extended under assumption of quasi-steady flow, to computations of evolution of two-dimensional flow about oscillating airfoil under light-dynamic-stall conditions. Represents advance toward ability to compute unsteady flows at even greater angles of attack with solutions of equations normally used for description of boundary-layer flows on airfoils prior to stall. Important in practical studies of flow on blades of helicopter rotors, axial compressors, and turbines.
Document ID
19930000093
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Tech Brief
Authors
Carr, L. W.
(NASA Ames Research Center, Moffett Field, CA.)
Cebeci, T.
(Douglas Aircraft Co.)
Jang, Hong-Ming
(Michigan Univ.)
Date Acquired
August 16, 2013
Publication Date
February 1, 1993
Publication Information
Publication: NASA Tech Briefs
Volume: 17
Issue: 2
ISSN: 0145-319X
Subject Category
Mechanics
Report/Patent Number
ARC-12466
Accession Number
93B10093
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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