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Investigation of Downwash, Sidewash, and Mach Number Distribution Behind a Rectangular Wing at a Mach Number of 2.41An investigation of the nature of the flow field behind a rectangular wing of circular arc cross section has been conducted in the Langley 9-inch supersonic tunnel. Pitot- and static-pressure surveys covering a region of flow behind the wing have been made together with detailed pitot surveys throughout the region of the wake. In addition, the flow direction has been measured by means of a weathercocking vane. Theoretical calculations have been made to obtain the variation of both downwash and sidewash with angle of attack by using the superposition method of Lagerstrom, Graham, and Grosslight. In addition, the effect of wing thickness on the sidewash with the wing at 0 degree angle of attack has been evaluated.
Document ID
19930092328
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Adamson, David
Boatright, William B
Date Acquired
September 6, 2013
Publication Date
January 1, 1957
Report/Patent Number
NACA-TR-1340
Accession Number
93R21618
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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