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Summary of Results Obtained in Full-Scale Tunnel Investigation of the Ryan Flex-Wing AirplaneThe performance and static stability and control characteristics of the Ryan Flex-Wing airplane were determined in an investigation conducted in the Langley full-scale tunnel through an angle-of-attack range of the keel from about 14 to 44 deg. for power-on and -off conditions. Comparisons of the wind-tunnel data with flight-test data obtained with the same airplane by the Ryan Aeronautical Company were made in a number of cases.
Document ID
19980223582
Acquisition Source
Headquarters
Document Type
Technical Memorandum (TM)
Authors
Johnson, Joseph L., Jr. (NASA Langley Research Center Hampton, VA United States)
Hassell, James L., Jr. (NASA Langley Research Center Hampton, VA United States)
Date Acquired
September 6, 2013
Publication Date
August 14, 1962
Subject Category
Aerodynamics
Report/Patent Number
L-3093
NASA-TM-SX-727
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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