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Wind tunnel test data for wing trailing vortex flow surveyData are presented on velocity measurements made with hot wire anemometers in the wake of a model of the CV-990 aircraft and a rectangular wing in the NASA-Ames 2.14x3.05 meter (7- by 10-foot) wind tunnels. Variables included angle of attack, tunnel speed and axial distance up to 12 chord lengths downstream from the wing trailing edge. Effects of deflecting trailing edge flaps and small spoiler panels are shown.
Document ID
19720016344
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Chigier, N. A. (NASA Ames Research Center Moffett Field, CA, United States)
Corsiglia, V. R. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 6, 2013
Publication Date
May 1, 1972
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-X-62148
Accession Number
72N23994
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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