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Wind-Tunnel Investigation at Low Speed of the Pitching Stability Derivatives of a 1/9-Scale Powered Model of the Convair XFY-1 Vertically Rising Airplane, TED No. NACA DE 373An experimental investigation has been conducted in the Langley stability tunnel at low speed to determine the pitching stability derivatives of a 1/9-scale powered model of the Convair XFY-1 vertically rising airplane. Effects of thrust coefficient, control deflections, and propeller blade angle were investigated. The tests were made through an angle-of-attack range from about -4deg to 29deg, and the thrust coefficient range was from 0 to 0.7. In order to expedite distribution of these data, no analysis of the data has been prepared for this paper.
Document ID
20050029407
Acquisition Source
Langley Research Center
Document Type
Other - NACA Research Memorandum
Authors
Queijo, M. J. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Wolhart, Walter D. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Fletcher, H. S. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Date Acquired
August 22, 2013
Publication Date
July 13, 1953
Subject Category
Aircraft Stability And Control
Report/Patent Number
NACA-RM-SL53G27
Report Number: NACA-RM-SL53G27
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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