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Experimental study of flow about a stalled two-dimensional airfoilWind tunnel tests to determine the flow characteristics of a stalled wing are described. The advantages of the plane wing over the ring wing for wind tunnel investigations are presented. The general flow pattern for stalled ring airfoils is developed. Photographs of the test equipment and installation are provided.
Document ID
19730009293
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Coles, D. E. (California Inst. of Tech. Pasadena, CA, United States)
Wadcock, A. (California Inst. of Tech. Pasadena, CA, United States)
Cantwell, B. (California Inst. of Tech. Pasadena, CA, United States)
Date Acquired
September 2, 2013
Publication Date
January 1, 1973
Subject Category
Aircraft
Report/Patent Number
SASR-2
SASR-3
NASA-CR-130919
Report Number: SASR-2
Report Number: SASR-3
Report Number: NASA-CR-130919
Accession Number
73N18020
Funding Number(s)
CONTRACT_GRANT: NGL-05-002-229
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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