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A method for the direct determination of wing-section dragIn order that the method may be more easily understood, we will first consider the simpler case when there is no lift, but only drag, and when the streamlines at the measuring point behind the obstacle are nearly parallel. Moreover, the flow is assumed not to deviate much from the two-dimensional flow.
Document ID
19930090720
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Betz, A
Date Acquired
September 6, 2013
Publication Date
November 1, 1925
Report/Patent Number
NACA-TM-337
Accession Number
93R20010
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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