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Airfoil profile in a nonuniform flowA theory of airfoil section past two dimensional nonuniform flow is developed. The theory is based on representation of airfoil section by vortex and source distributions and it can be used for calculation of aircraft wings in homogeneous and inhomogeneous flow, as well as for calculation of straight and radial blade and vane-cascades.
Document ID
19780013105
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Polasek, J. (NASA Headquarters Washington, DC United States)
Date Acquired
September 3, 2013
Publication Date
March 1, 1978
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-75272
Report Number: NASA-TM-75272
Accession Number
78N21048
Funding Number(s)
CONTRACT_GRANT: NASW-2791
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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