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Computation of the transonic perturbation flow fields around two- and three-dimensional oscillating wingsAnalytical and empirical studies of a finite difference method for the solution of the transonic flow about an harmonically oscillating wing are presented along with a discussion of the development of a pilot program for three-dimensional flow. In addition, some two- and three-dimensional examples are presented.
Document ID
19760009984
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Weatherill, W. H. (Boeing Commercial Airplane Co. Seattle, WA, United States)
Ehlers, F. E. (Boeing Commercial Airplane Co. Seattle, WA, United States)
Sebastian, J. D. (Boeing Commercial Airplane Co. Seattle, WA, United States)
Date Acquired
September 3, 2013
Publication Date
December 1, 1975
Publication Information
Publisher: NASA
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-2599
D6-42536
Accession Number
76N17072
Funding Number(s)
CONTRACT_GRANT: NAS1-13002
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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