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Overview of 6- X 6-foot wind tunnel aero-optics testsThe splitter-plate arrangement used in tests in the 6 x 6 foot wind tunnel and how it was configured to study boundary layers, both heated and unheated, shear layers over a cavity, separated flows behind spoilers, accelerated flows around a turret, and a turret wake are described. The flows are characterized by examples of the steady-state pressure and of velocity profiles through the various types of flow layers.
Document ID
19800017093
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Buell, D. A. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 10, 2013
Publication Date
April 1, 1980
Publication Information
Publication: Proc. of the Aero-Optics Symp. on Electromagnetic Wave Propagation from Aircraft
Subject Category
Fluid Mechanics And Heat Transfer
Accession Number
80N25590
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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IDRelationTitle19800017091Collected WorksProceedings of the Aero-Optics Symposium on Electromagnetic Wave Propagation from Aircraft
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